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Merge pull request #137 from PX4/fixedwing 

Add latest fixed wing control bits, multi rotors supported.
This commit is contained in:
px4dev 2013-01-10 23:38:13 -08:00
parent 0cb2a508b2 31ca806958
commit 40dfbf0d97
64 changed files with 3089 additions and 1991 deletions
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8
ROMFS/scripts/rcS
View File

@ -46,8 +46,12 @@ if [ -f /fs/microsd/etc/rc ]
then
echo "[init] reading /fs/microsd/etc/rc"
sh /fs/microsd/etc/rc
else
echo "[init] script /fs/microsd/etc/rc not present"
fi
# Also consider rc.txt files
if [ -f /fs/microsd/etc/rc.txt ]
then
echo "[init] reading /fs/microsd/etc/rc.txt"
sh /fs/microsd/etc/rc.txt
fi
#

78
apps/attitude_estimator_ekf/attitude_estimator_ekf_main.c
View File

@ -35,7 +35,7 @@
/*
* @file attitude_estimator_ekf_main.c
*
*
* Extended Kalman Filter for Attitude Estimation.
*/
@ -79,18 +79,18 @@ static float dt = 0.005f;
static float z_k[9] = {0.0f, 0.0f, 0.0f, 0.0f, 0.0f, 9.81f, 0.2f, -0.2f, 0.2f}; /**< Measurement vector */
static float x_aposteriori_k[12]; /**< states */
static float P_aposteriori_k[144] = {100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 100.0f, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 100.0f, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 0, 100.0f,
}; /**< init: diagonal matrix with big values */
0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 100.0f, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 100.0f, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 0, 100.0f,
}; /**< init: diagonal matrix with big values */
static float x_aposteriori[12];
static float P_aposteriori[144];
@ -99,9 +99,9 @@ static float P_aposteriori[144];
static float euler[3] = {0.0f, 0.0f, 0.0f};
static float Rot_matrix[9] = {1.f, 0, 0,
0, 1.f, 0,
0, 0, 1.f
}; /**< init: identity matrix */
0, 1.f, 0,
0, 0, 1.f
}; /**< init: identity matrix */
static bool thread_should_exit = false; /**< Deamon exit flag */
@ -123,6 +123,7 @@ usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: attitude_estimator_ekf {start|stop|status} [-p <additional params>]\n\n");
exit(1);
}
@ -131,7 +132,7 @@ usage(const char *reason)
* The attitude_estimator_ekf app only briefly exists to start
* the background job. The stack size assigned in the
* Makefile does only apply to this management task.
*
*
* The actual stack size should be set in the call
* to task_create().
*/
@ -150,11 +151,11 @@ int attitude_estimator_ekf_main(int argc, char *argv[])
thread_should_exit = false;
attitude_estimator_ekf_task = task_spawn("attitude_estimator_ekf",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 5,
12000,
attitude_estimator_ekf_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 5,
12000,
attitude_estimator_ekf_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
exit(0);
}
@ -166,9 +167,11 @@ int attitude_estimator_ekf_main(int argc, char *argv[])
if (!strcmp(argv[1], "status")) {
if (thread_running) {
printf("\tattitude_estimator_ekf app is running\n");
} else {
printf("\tattitude_estimator_ekf app not started\n");
}
exit(0);
}
@ -235,7 +238,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
/* advertise debug value */
// struct debug_key_value_s dbg = { .key = "", .value = 0.0f };
// orb_advert_t pub_dbg = -1;
float sensor_update_hz[3] = {0.0f, 0.0f, 0.0f};
// XXX write this out to perf regs
@ -263,8 +266,8 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
while (!thread_should_exit) {
struct pollfd fds[2] = {
{ .fd = sub_raw, .events = POLLIN },
{ .fd = sub_params, .events = POLLIN }
{ .fd = sub_raw, .events = POLLIN },
{ .fd = sub_params, .events = POLLIN }
};
int ret = poll(fds, 2, 1000);
@ -273,10 +276,12 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
} else if (ret == 0) {
/* check if we're in HIL - not getting sensor data is fine then */
orb_copy(ORB_ID(vehicle_status), sub_state, &state);
if (!state.flag_hil_enabled) {
fprintf(stderr,
fprintf(stderr,
"[att ekf] WARNING: Not getting sensors - sensor app running?\n");
}
} else {
/* only update parameters if they changed */
@ -308,6 +313,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
gyro_offsets[1] /= offset_count;
gyro_offsets[2] /= offset_count;
}
} else {
perf_begin(ekf_loop_perf);
@ -336,6 +342,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
sensor_update_hz[1] = 1e6f / (raw.timestamp - sensor_last_timestamp[1]);
sensor_last_timestamp[1] = raw.timestamp;
}
z_k[3] = raw.accelerometer_m_s2[0];
z_k[4] = raw.accelerometer_m_s2[1];
z_k[5] = raw.accelerometer_m_s2[2];
@ -347,6 +354,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
sensor_update_hz[2] = 1e6f / (raw.timestamp - sensor_last_timestamp[2]);
sensor_last_timestamp[2] = raw.timestamp;
}
z_k[6] = raw.magnetometer_ga[0];
z_k[7] = raw.magnetometer_ga[1];
z_k[8] = raw.magnetometer_ga[2];
@ -368,8 +376,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
static bool const_initialized = false;
/* initialize with good values once we have a reasonable dt estimate */
if (!const_initialized && dt < 0.05f && dt > 0.005f)
{
if (!const_initialized && dt < 0.05f && dt > 0.005f) {
dt = 0.005f;
parameters_update(&ekf_param_handles, &ekf_params);
@ -395,13 +402,15 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
}
uint64_t timing_start = hrt_absolute_time();
attitudeKalmanfilter(update_vect, dt, z_k, x_aposteriori_k, P_aposteriori_k, ekf_params.q, ekf_params.r,
euler, Rot_matrix, x_aposteriori, P_aposteriori);
euler, Rot_matrix, x_aposteriori, P_aposteriori);
/* swap values for next iteration, check for fatal inputs */
if (isfinite(euler[0]) && isfinite(euler[1]) && isfinite(euler[2])) {
memcpy(P_aposteriori_k, P_aposteriori, sizeof(P_aposteriori_k));
memcpy(x_aposteriori_k, x_aposteriori, sizeof(x_aposteriori_k));
} else {
/* due to inputs or numerical failure the output is invalid, skip it */
continue;
@ -413,9 +422,11 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
/* send out */
att.timestamp = raw.timestamp;
att.roll = euler[0];
att.pitch = euler[1];
att.yaw = euler[2];
// XXX Apply the same transformation to the rotation matrix
att.roll = euler[0] - ekf_params.roll_off;
att.pitch = euler[1] - ekf_params.pitch_off;
att.yaw = euler[2] - ekf_params.yaw_off;
att.rollspeed = x_aposteriori[0];
att.pitchspeed = x_aposteriori[1];
@ -431,6 +442,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
if (isfinite(att.roll) && isfinite(att.pitch) && isfinite(att.yaw)) {
// Broadcast
orb_publish(ORB_ID(vehicle_attitude), pub_att, &att);
} else {
warnx("NaN in roll/pitch/yaw estimate!");
}

20
apps/attitude_estimator_ekf/attitude_estimator_ekf_params.c
View File

@ -35,7 +35,7 @@
/*
* @file attitude_estimator_ekf_params.c
*
*
* Parameters for EKF filter
*/
@ -65,13 +65,17 @@ PARAM_DEFINE_FLOAT(EKF_ATT_R0, 0.01f);
PARAM_DEFINE_FLOAT(EKF_ATT_R1, 0.01f);
PARAM_DEFINE_FLOAT(EKF_ATT_R2, 0.01f);
/* accelerometer measurement noise */
PARAM_DEFINE_FLOAT(EKF_ATT_R3, 1e1f);
PARAM_DEFINE_FLOAT(EKF_ATT_R4, 1e1f);
PARAM_DEFINE_FLOAT(EKF_ATT_R5, 1e1f);
PARAM_DEFINE_FLOAT(EKF_ATT_R3, 1e2f);
PARAM_DEFINE_FLOAT(EKF_ATT_R4, 1e2f);
PARAM_DEFINE_FLOAT(EKF_ATT_R5, 1e2f);
/* magnetometer measurement noise */
PARAM_DEFINE_FLOAT(EKF_ATT_R6, 1e-1f);
PARAM_DEFINE_FLOAT(EKF_ATT_R7, 1e-1f);
PARAM_DEFINE_FLOAT(EKF_ATT_R8, 1e-1f);
/* offsets in roll, pitch and yaw of sensor plane and body */
PARAM_DEFINE_FLOAT(ATT_ROLL_OFFS, 0.0f);
PARAM_DEFINE_FLOAT(ATT_PITCH_OFFS, 0.0f);
PARAM_DEFINE_FLOAT(ATT_YAW_OFFS, 0.0f);
int parameters_init(struct attitude_estimator_ekf_param_handles *h)
{
@ -99,6 +103,10 @@ int parameters_init(struct attitude_estimator_ekf_param_handles *h)
h->r7 = param_find("EKF_ATT_R7");
h->r8 = param_find("EKF_ATT_R8");
h->roll_off = param_find("ATT_ROLL_OFFS");
h->pitch_off = param_find("ATT_PITCH_OFFS");
h->yaw_off = param_find("ATT_YAW_OFFS");
return OK;
}
@ -127,5 +135,9 @@ int parameters_update(const struct attitude_estimator_ekf_param_handles *h, stru
param_get(h->r7, &(p->r[7]));
param_get(h->r8, &(p->r[8]));
param_get(h->roll_off, &(p->roll_off));
param_get(h->pitch_off, &(p->pitch_off));
param_get(h->yaw_off, &(p->yaw_off));
return OK;
}

6
apps/attitude_estimator_ekf/attitude_estimator_ekf_params.h
View File

@ -35,7 +35,7 @@
/*
* @file attitude_estimator_ekf_params.h
*
*
* Parameters for EKF filter
*/
@ -44,11 +44,15 @@
struct attitude_estimator_ekf_params {
float r[9];
float q[12];
float roll_off;
float pitch_off;
float yaw_off;
};
struct attitude_estimator_ekf_param_handles {
param_t r0, r1, r2, r3, r4, r5, r6, r7, r8;
param_t q0, q1, q2, q3, q4, q5, q6, q7, q8, q9, q10, q11;
param_t roll_off, pitch_off, yaw_off;
};
/**

283
apps/commander/calibration_routines.c
View File

@ -45,172 +45,175 @@
int sphere_fit_least_squares(const float x[], const float y[], const float z[],
unsigned int size, unsigned int max_iterations, float delta, float *sphere_x, float *sphere_y, float *sphere_z, float *sphere_radius) {
unsigned int size, unsigned int max_iterations, float delta, float *sphere_x, float *sphere_y, float *sphere_z, float *sphere_radius)
{
float x_sumplain = 0.0f;
float x_sumsq = 0.0f;
float x_sumcube = 0.0f;
float x_sumplain = 0.0f;
float x_sumsq = 0.0f;
float x_sumcube = 0.0f;
float y_sumplain = 0.0f;
float y_sumsq = 0.0f;
float y_sumcube = 0.0f;
float y_sumplain = 0.0f;
float y_sumsq = 0.0f;
float y_sumcube = 0.0f;
float z_sumplain = 0.0f;
float z_sumsq = 0.0f;
float z_sumcube = 0.0f;
float z_sumplain = 0.0f;
float z_sumsq = 0.0f;
float z_sumcube = 0.0f;
float xy_sum = 0.0f;
float xz_sum = 0.0f;
float yz_sum = 0.0f;
float xy_sum = 0.0f;
float xz_sum = 0.0f;
float yz_sum = 0.0f;
float x2y_sum = 0.0f;
float x2z_sum = 0.0f;
float y2x_sum = 0.0f;
float y2z_sum = 0.0f;
float z2x_sum = 0.0f;
float z2y_sum = 0.0f;
float x2y_sum = 0.0f;
float x2z_sum = 0.0f;
float y2x_sum = 0.0f;
float y2z_sum = 0.0f;
float z2x_sum = 0.0f;
float z2y_sum = 0.0f;
for (unsigned int i = 0; i < size; i++) {
for (unsigned int i = 0; i < size; i++) {
float x2 = x[i] * x[i];
float y2 = y[i] * y[i];
float z2 = z[i] * z[i];
float x2 = x[i] * x[i];
float y2 = y[i] * y[i];
float z2 = z[i] * z[i];
x_sumplain += x[i];
x_sumsq += x2;
x_sumcube += x2 * x[i];
x_sumplain += x[i];
x_sumsq += x2;
x_sumcube += x2 * x[i];
y_sumplain += y[i];
y_sumsq += y2;
y_sumcube += y2 * y[i];
y_sumplain += y[i];
y_sumsq += y2;
y_sumcube += y2 * y[i];
z_sumplain += z[i];
z_sumsq += z2;
z_sumcube += z2 * z[i];
z_sumplain += z[i];
z_sumsq += z2;
z_sumcube += z2 * z[i];
xy_sum += x[i] * y[i];
xz_sum += x[i] * z[i];
yz_sum += y[i] * z[i];
xy_sum += x[i] * y[i];
xz_sum += x[i] * z[i];
yz_sum += y[i] * z[i];
x2y_sum += x2 * y[i];
x2z_sum += x2 * z[i];
x2y_sum += x2 * y[i];
x2z_sum += x2 * z[i];
y2x_sum += y2 * x[i];
y2z_sum += y2 * z[i];
y2x_sum += y2 * x[i];
y2z_sum += y2 * z[i];
z2x_sum += z2 * x[i];
z2y_sum += z2 * y[i];
}
z2x_sum += z2 * x[i];
z2y_sum += z2 * y[i];
}
//
//Least Squares Fit a sphere A,B,C with radius squared Rsq to 3D data
//
// P is a structure that has been computed with the data earlier.
// P.npoints is the number of elements; the length of X,Y,Z are identical.
// P's members are logically named.
//
// X[n] is the x component of point n
// Y[n] is the y component of point n
// Z[n] is the z component of point n
//
// A is the x coordiante of the sphere
// B is the y coordiante of the sphere
// C is the z coordiante of the sphere
// Rsq is the radius squared of the sphere.
//
//This method should converge; maybe 5-100 iterations or more.
//
float x_sum = x_sumplain / size; //sum( X[n] )
float x_sum2 = x_sumsq / size; //sum( X[n]^2 )
float x_sum3 = x_sumcube / size; //sum( X[n]^3 )
float y_sum = y_sumplain / size; //sum( Y[n] )
float y_sum2 = y_sumsq / size; //sum( Y[n]^2 )
float y_sum3 = y_sumcube / size; //sum( Y[n]^3 )
float z_sum = z_sumplain / size; //sum( Z[n] )
float z_sum2 = z_sumsq / size; //sum( Z[n]^2 )
float z_sum3 = z_sumcube / size; //sum( Z[n]^3 )
//
//Least Squares Fit a sphere A,B,C with radius squared Rsq to 3D data
//
// P is a structure that has been computed with the data earlier.
// P.npoints is the number of elements; the length of X,Y,Z are identical.
// P's members are logically named.
//
// X[n] is the x component of point n
// Y[n] is the y component of point n
// Z[n] is the z component of point n
//
// A is the x coordiante of the sphere
// B is the y coordiante of the sphere
// C is the z coordiante of the sphere
// Rsq is the radius squared of the sphere.
//
//This method should converge; maybe 5-100 iterations or more.
//
float x_sum = x_sumplain / size; //sum( X[n] )
float x_sum2 = x_sumsq / size; //sum( X[n]^2 )
float x_sum3 = x_sumcube / size; //sum( X[n]^3 )
float y_sum = y_sumplain / size; //sum( Y[n] )
float y_sum2 = y_sumsq / size; //sum( Y[n]^2 )
float y_sum3 = y_sumcube / size; //sum( Y[n]^3 )
float z_sum = z_sumplain / size; //sum( Z[n] )
float z_sum2 = z_sumsq / size; //sum( Z[n]^2 )
float z_sum3 = z_sumcube / size; //sum( Z[n]^3 )
float XY = xy_sum / size; //sum( X[n] * Y[n] )
float XZ = xz_sum / size; //sum( X[n] * Z[n] )
float YZ = yz_sum / size; //sum( Y[n] * Z[n] )
float X2Y = x2y_sum / size; //sum( X[n]^2 * Y[n] )
float X2Z = x2z_sum / size; //sum( X[n]^2 * Z[n] )
float Y2X = y2x_sum / size; //sum( Y[n]^2 * X[n] )
float Y2Z = y2z_sum / size; //sum( Y[n]^2 * Z[n] )
float Z2X = z2x_sum / size; //sum( Z[n]^2 * X[n] )
float Z2Y = z2y_sum / size; //sum( Z[n]^2 * Y[n] )
float XY = xy_sum / size; //sum( X[n] * Y[n] )
float XZ = xz_sum / size; //sum( X[n] * Z[n] )
float YZ = yz_sum / size; //sum( Y[n] * Z[n] )
float X2Y = x2y_sum / size; //sum( X[n]^2 * Y[n] )
float X2Z = x2z_sum / size; //sum( X[n]^2 * Z[n] )
float Y2X = y2x_sum / size; //sum( Y[n]^2 * X[n] )
float Y2Z = y2z_sum / size; //sum( Y[n]^2 * Z[n] )
float Z2X = z2x_sum / size; //sum( Z[n]^2 * X[n] )
float Z2Y = z2y_sum / size; //sum( Z[n]^2 * Y[n] )
//Reduction of multiplications
float F0 = x_sum2 + y_sum2 + z_sum2;
float F1 = 0.5f * F0;
float F2 = -8.0f * (x_sum3 + Y2X + Z2X);
float F3 = -8.0f * (X2Y + y_sum3 + Z2Y);
float F4 = -8.0f * (X2Z + Y2Z + z_sum3);
//Reduction of multiplications
float F0 = x_sum2 + y_sum2 + z_sum2;
float F1 = 0.5f * F0;
float F2 = -8.0f * (x_sum3 + Y2X + Z2X);
float F3 = -8.0f * (X2Y + y_sum3 + Z2Y);
float F4 = -8.0f * (X2Z + Y2Z + z_sum3);
//Set initial conditions:
float A = x_sum;
float B = y_sum;
float C = z_sum;
//Set initial conditions:
float A = x_sum;
float B = y_sum;
float C = z_sum;
//First iteration computation:
float A2 = A*A;
float B2 = B*B;
float C2 = C*C;
float QS = A2 + B2 + C2;
float QB = -2.0f * (A*x_sum + B*y_sum + C*z_sum);
//First iteration computation:
float A2 = A * A;
float B2 = B * B;
float C2 = C * C;
float QS = A2 + B2 + C2;
float QB = -2.0f * (A * x_sum + B * y_sum + C * z_sum);
//Set initial conditions:
float Rsq = F0 + QB + QS;
//Set initial conditions:
float Rsq = F0 + QB + QS;
//First iteration computation:
float Q0 = 0.5f * (QS - Rsq);
float Q1 = F1 + Q0;
float Q2 = 8.0f * ( QS - Rsq + QB + F0 );
float aA,aB,aC,nA,nB,nC,dA,dB,dC;
//First iteration computation:
float Q0 = 0.5f * (QS - Rsq);
float Q1 = F1 + Q0;
float Q2 = 8.0f * (QS - Rsq + QB + F0);
float aA, aB, aC, nA, nB, nC, dA, dB, dC;
//Iterate N times, ignore stop condition.
int n = 0;
while( n < max_iterations ){
n++;
//Iterate N times, ignore stop condition.
int n = 0;
//Compute denominator:
aA = Q2 + 16.0f * (A2 - 2.0f * A*x_sum + x_sum2);
aB = Q2 + 16.0f *(B2 - 2.0f * B*y_sum + y_sum2);
aC = Q2 + 16.0f *(C2 - 2.0f * C*z_sum + z_sum2);
aA = (aA == 0.0f) ? 1.0f : aA;
aB = (aB == 0.0f) ? 1.0f : aB;
aC = (aC == 0.0f) ? 1.0f : aC;
while (n < max_iterations) {
n++;
//Compute next iteration
nA = A - ((F2 + 16.0f * ( B*XY + C*XZ + x_sum*(-A2 - Q0) + A*(x_sum2 + Q1 - C*z_sum - B*y_sum) ) )/aA);
nB = B - ((F3 + 16.0f * ( A*XY + C*YZ + y_sum*(-B2 - Q0) + B*(y_sum2 + Q1 - A*x_sum - C*z_sum) ) )/aB);
nC = C - ((F4 + 16.0f * ( A*XZ + B*YZ + z_sum*(-C2 - Q0) + C*(z_sum2 + Q1 - A*x_sum - B*y_sum) ) )/aC);
//Compute denominator:
aA = Q2 + 16.0f * (A2 - 2.0f * A * x_sum + x_sum2);
aB = Q2 + 16.0f * (B2 - 2.0f * B * y_sum + y_sum2);
aC = Q2 + 16.0f * (C2 - 2.0f * C * z_sum + z_sum2);
aA = (aA == 0.0f) ? 1.0f : aA;
aB = (aB == 0.0f) ? 1.0f : aB;
aC = (aC == 0.0f) ? 1.0f : aC;
//Check for stop condition
dA = (nA - A);
dB = (nB - B);
dC = (nC - C);
if( (dA*dA + dB*dB + dC*dC) <= delta ){ break; }
//Compute next iteration
nA = A - ((F2 + 16.0f * (B * XY + C * XZ + x_sum * (-A2 - Q0) + A * (x_sum2 + Q1 - C * z_sum - B * y_sum))) / aA);
nB = B - ((F3 + 16.0f * (A * XY + C * YZ + y_sum * (-B2 - Q0) + B * (y_sum2 + Q1 - A * x_sum - C * z_sum))) / aB);
nC = C - ((F4 + 16.0f * (A * XZ + B * YZ + z_sum * (-C2 - Q0) + C * (z_sum2 + Q1 - A * x_sum - B * y_sum))) / aC);
//Compute next iteration's values
A = nA;
B = nB;
C = nC;
A2 = A*A;
B2 = B*B;
C2 = C*C;
QS = A2 + B2 + C2;
QB = -2.0f * (A*x_sum + B*y_sum + C*z_sum);
Rsq = F0 + QB + QS;
Q0 = 0.5f * (QS - Rsq);
Q1 = F1 + Q0;
Q2 = 8.0f * ( QS - Rsq + QB + F0 );
}
//Check for stop condition
dA = (nA - A);
dB = (nB - B);
dC = (nC - C);
*sphere_x = A;
*sphere_y = B;
*sphere_z = C;
*sphere_radius = sqrtf(Rsq);
if ((dA * dA + dB * dB + dC * dC) <= delta) { break; }
return 0;
//Compute next iteration's values
A = nA;
B = nB;
C = nC;
A2 = A * A;
B2 = B * B;
C2 = C * C;
QS = A2 + B2 + C2;
QB = -2.0f * (A * x_sum + B * y_sum + C * z_sum);
Rsq = F0 + QB + QS;
Q0 = 0.5f * (QS - Rsq);
Q1 = F1 + Q0;
Q2 = 8.0f * (QS - Rsq + QB + F0);
}
*sphere_x = A;
*sphere_y = B;
*sphere_z = C;
*sphere_radius = sqrtf(Rsq);
return 0;
}

2
apps/commander/calibration_routines.h
View File

@ -58,4 +58,4 @@
* @return 0 on success, 1 on failure
*/
int sphere_fit_least_squares(const float x[], const float y[], const float z[],
unsigned int size, unsigned int max_iterations, float delta, float *sphere_x, float *sphere_y, float *sphere_z, float *sphere_radius);
unsigned int size, unsigned int max_iterations, float delta, float *sphere_x, float *sphere_y, float *sphere_z, float *sphere_radius);

767
apps/commander/commander.c
View File

File diff suppressed because it is too large Load Diff

3
apps/commander/commander.h
View File

@ -52,4 +52,7 @@
#define LOW_VOLTAGE_BATTERY_HYSTERESIS_TIME_MS 1000.0f
#define CRITICAL_VOLTAGE_BATTERY_HYSTERESIS_TIME_MS 100.0f
void tune_confirm(void);
void tune_error(void);
#endif /* COMMANDER_H_ */

216
apps/commander/state_machine_helper.c
View File

@ -50,7 +50,7 @@
#include "state_machine_helper.h"
static const char* system_state_txt[] = {
static const char *system_state_txt[] = {
"SYSTEM_STATE_PREFLIGHT",
"SYSTEM_STATE_STANDBY",
"SYSTEM_STATE_GROUND_READY",
@ -79,7 +79,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
case SYSTEM_STATE_MISSION_ABORT: {
/* Indoor or outdoor */
// if (flight_environment_parameter == PX4_FLIGHT_ENVIRONMENT_OUTDOOR) {
ret = do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_EMCY_LANDING);
ret = do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_EMCY_LANDING);
// } else {
// ret = do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_EMCY_CUTOFF);
@ -93,8 +93,8 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* set system flags according to state */
current_status->flag_system_armed = true;
fprintf(stderr, "[commander] EMERGENCY LANDING!\n");
mavlink_log_critical(mavlink_fd, "[commander] EMERGENCY LANDING!");
warnx("EMERGENCY LANDING!\n");
mavlink_log_critical(mavlink_fd, "EMERGENCY LANDING!");
break;
case SYSTEM_STATE_EMCY_CUTOFF:
@ -103,8 +103,8 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* set system flags according to state */
current_status->flag_system_armed = false;
fprintf(stderr, "[commander] EMERGENCY MOTOR CUTOFF!\n");
mavlink_log_critical(mavlink_fd, "[commander] EMERGENCY MOTOR CUTOFF!");
warnx("EMERGENCY MOTOR CUTOFF!\n");
mavlink_log_critical(mavlink_fd, "EMERGENCY MOTOR CUTOFF!");
break;
case SYSTEM_STATE_GROUND_ERROR:
@ -114,36 +114,40 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* prevent actuators from arming */
current_status->flag_system_armed = false;
fprintf(stderr, "[commander] GROUND ERROR, locking down propulsion system\n");
mavlink_log_critical(mavlink_fd, "[commander] GROUND ERROR, locking down propulsion system");
warnx("GROUND ERROR, locking down propulsion system\n");
mavlink_log_critical(mavlink_fd, "GROUND ERROR, locking down system");
break;
case SYSTEM_STATE_PREFLIGHT:
if (current_status->state_machine == SYSTEM_STATE_STANDBY
|| current_status->state_machine == SYSTEM_STATE_PREFLIGHT) {
|| current_status->state_machine == SYSTEM_STATE_PREFLIGHT) {
/* set system flags according to state */
current_status->flag_system_armed = false;
mavlink_log_critical(mavlink_fd, "[commander] Switched to PREFLIGHT state");
mavlink_log_critical(mavlink_fd, "Switched to PREFLIGHT state");
} else {
invalid_state = true;
mavlink_log_critical(mavlink_fd, "[commander] REFUSED to switch to PREFLIGHT state");
mavlink_log_critical(mavlink_fd, "REFUSED to switch to PREFLIGHT state");
}
break;
case SYSTEM_STATE_REBOOT:
if (current_status->state_machine == SYSTEM_STATE_STANDBY
|| current_status->state_machine == SYSTEM_STATE_PREFLIGHT) {
|| current_status->state_machine == SYSTEM_STATE_PREFLIGHT) {
invalid_state = false;
/* set system flags according to state */
current_status->flag_system_armed = false;
mavlink_log_critical(mavlink_fd, "[commander] REBOOTING SYSTEM");
mavlink_log_critical(mavlink_fd, "REBOOTING SYSTEM");
usleep(500000);
up_systemreset();
/* SPECIAL CASE: NEVER RETURNS FROM THIS FUNCTION CALL */
} else {
invalid_state = true;
mavlink_log_critical(mavlink_fd, "[commander] REFUSED to REBOOT");
mavlink_log_critical(mavlink_fd, "REFUSED to REBOOT");
}
break;
case SYSTEM_STATE_STANDBY:
@ -152,7 +156,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* standby enforces disarmed */
current_status->flag_system_armed = false;
mavlink_log_critical(mavlink_fd, "[commander] Switched to STANDBY state");
mavlink_log_critical(mavlink_fd, "Switched to STANDBY state");
break;
case SYSTEM_STATE_GROUND_READY:
@ -162,7 +166,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* ground ready has motors / actuators armed */
current_status->flag_system_armed = true;
mavlink_log_critical(mavlink_fd, "[commander] Switched to GROUND READY state");
mavlink_log_critical(mavlink_fd, "Switched to GROUND READY state");
break;
case SYSTEM_STATE_AUTO:
@ -172,7 +176,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* auto is airborne and in auto mode, motors armed */
current_status->flag_system_armed = true;
mavlink_log_critical(mavlink_fd, "[commander] Switched to FLYING / AUTO mode");
mavlink_log_critical(mavlink_fd, "Switched to FLYING / AUTO mode");
break;
case SYSTEM_STATE_STABILIZED:
@ -180,7 +184,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* set system flags according to state */
current_status->flag_system_armed = true;
mavlink_log_critical(mavlink_fd, "[commander] Switched to FLYING / STABILIZED mode");
mavlink_log_critical(mavlink_fd, "Switched to FLYING / STABILIZED mode");
break;
case SYSTEM_STATE_MANUAL:
@ -188,7 +192,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
/* set system flags according to state */
current_status->flag_system_armed = true;
mavlink_log_critical(mavlink_fd, "[commander] Switched to FLYING / MANUAL mode");
mavlink_log_critical(mavlink_fd, "Switched to FLYING / MANUAL mode");
break;
default:
@ -202,14 +206,17 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
publish_armed_status(current_status);
ret = OK;
}
if (invalid_state) {
mavlink_log_critical(mavlink_fd, "[commander] REJECTING invalid state transition");
mavlink_log_critical(mavlink_fd, "REJECTING invalid state transition");
ret = ERROR;
}
return ret;
}
void state_machine_publish(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd) {
void state_machine_publish(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
/* publish the new state */
current_status->counter++;
current_status->timestamp = hrt_absolute_time();
@ -217,9 +224,11 @@ void state_machine_publish(int status_pub, struct vehicle_status_s *current_stat
/* assemble state vector based on flag values */
if (current_status->flag_control_rates_enabled) {
current_status->onboard_control_sensors_present |= 0x400;
} else {
current_status->onboard_control_sensors_present &= ~0x400;
}
current_status->onboard_control_sensors_present |= (current_status->flag_control_attitude_enabled) ? 0x800 : 0;
current_status->onboard_control_sensors_present |= (current_status->flag_control_attitude_enabled) ? 0x1000 : 0;
current_status->onboard_control_sensors_present |= (current_status->flag_control_velocity_enabled || current_status->flag_control_position_enabled) ? 0x2000 : 0;
@ -232,10 +241,11 @@ void state_machine_publish(int status_pub, struct vehicle_status_s *current_stat
current_status->onboard_control_sensors_enabled |= (current_status->flag_control_velocity_enabled || current_status->flag_control_position_enabled) ? 0x4000 : 0;
orb_publish(ORB_ID(vehicle_status), status_pub, current_status);
printf("[commander] new state: %s\n", system_state_txt[current_status->state_machine]);
printf("[cmd] new state: %s\n", system_state_txt[current_status->state_machine]);
}
void publish_armed_status(const struct vehicle_status_s *current_status) {
void publish_armed_status(const struct vehicle_status_s *current_status)
{
struct actuator_armed_s armed;
armed.armed = current_status->flag_system_armed;
/* lock down actuators if required, only in HIL */
@ -250,19 +260,19 @@ void publish_armed_status(const struct vehicle_status_s *current_status) {
*/
void state_machine_emergency_always_critical(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
fprintf(stderr, "[commander] EMERGENCY HANDLER\n");
warnx("EMERGENCY HANDLER\n");
/* Depending on the current state go to one of the error states */
if (current_status->state_machine == SYSTEM_STATE_PREFLIGHT || current_status->state_machine == SYSTEM_STATE_STANDBY || current_status->state_machine == SYSTEM_STATE_GROUND_READY) {
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_GROUND_ERROR);
} else if (current_status->state_machine == SYSTEM_STATE_AUTO || current_status->state_machine == SYSTEM_STATE_MANUAL) {
// DO NOT abort mission
//do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_MISSION_ABORT);
} else {
fprintf(stderr, "[commander] Unknown system state: #%d\n", current_status->state_machine);
warnx("Unknown system state: #%d\n", current_status->state_machine);
}
}
@ -272,7 +282,7 @@ void state_machine_emergency(int status_pub, struct vehicle_status_s *current_st
state_machine_emergency_always_critical(status_pub, current_status, mavlink_fd);
} else {
//global_data_send_mavlink_statustext_message_out("[commander] ERROR: take action immediately! (did not switch to error state because the system is in manual mode)", MAV_SEVERITY_CRITICAL);
//global_data_send_mavlink_statustext_message_out("[cmd] ERROR: take action immediately! (did not switch to error state because the system is in manual mode)", MAV_SEVERITY_CRITICAL);
}
}
@ -497,7 +507,7 @@ void update_state_machine_no_position_fix(int status_pub, struct vehicle_status_
void update_state_machine_arm(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
if (current_status->state_machine == SYSTEM_STATE_STANDBY) {
printf("[commander] arming\n");
printf("[cmd] arming\n");
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_GROUND_READY);
}
}
@ -505,11 +515,11 @@ void update_state_machine_arm(int status_pub, struct vehicle_status_s *current_s
void update_state_machine_disarm(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
if (current_status->state_machine == SYSTEM_STATE_GROUND_READY || current_status->state_machine == SYSTEM_STATE_MANUAL || current_status->state_machine == SYSTEM_STATE_PREFLIGHT) {
printf("[commander] going standby\n");
printf("[cmd] going standby\n");
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_STANDBY);
} else if (current_status->state_machine == SYSTEM_STATE_STABILIZED || current_status->state_machine == SYSTEM_STATE_AUTO) {
printf("[commander] MISSION ABORT!\n");
printf("[cmd] MISSION ABORT!\n");
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_STANDBY);
}
}
@ -518,54 +528,139 @@ void update_state_machine_mode_manual(int status_pub, struct vehicle_status_s *c
{
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_MANUAL;
current_status->flag_control_manual_enabled = true;
/* enable attitude control per default */
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
/* set behaviour based on airframe */
if ((current_status->system_type == VEHICLE_TYPE_QUADROTOR) ||
(current_status->system_type == VEHICLE_TYPE_HEXAROTOR) ||
(current_status->system_type == VEHICLE_TYPE_OCTOROTOR)) {
/* assuming a rotary wing, set to SAS */
current_status->manual_control_mode = VEHICLE_MANUAL_CONTROL_MODE_SAS;
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
} else {
/* assuming a fixed wing, set to direct pass-through */
current_status->manual_control_mode = VEHICLE_MANUAL_CONTROL_MODE_DIRECT;
current_status->flag_control_attitude_enabled = false;
current_status->flag_control_rates_enabled = false;
}
if (old_mode != current_status->flight_mode) state_machine_publish(status_pub, current_status, mavlink_fd);
if (current_status->state_machine == SYSTEM_STATE_GROUND_READY || current_status->state_machine == SYSTEM_STATE_STABILIZED || current_status->state_machine == SYSTEM_STATE_AUTO) {
printf("[commander] manual mode\n");
printf("[cmd] manual mode\n");
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_MANUAL);
}
}
void update_state_machine_mode_stabilized(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_STABILIZED;
current_status->flag_control_manual_enabled = true;
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
if (old_mode != current_status->flight_mode) state_machine_publish(status_pub, current_status, mavlink_fd);
if (current_status->state_machine == SYSTEM_STATE_GROUND_READY || current_status->state_machine == SYSTEM_STATE_STABILIZED || current_status->state_machine == SYSTEM_STATE_MANUAL || current_status->state_machine == SYSTEM_STATE_AUTO) {
int old_mode = current_status->flight_mode;
int old_manual_control_mode = current_status->manual_control_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_MANUAL;
current_status->manual_control_mode = VEHICLE_MANUAL_CONTROL_MODE_SAS;
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
current_status->flag_control_manual_enabled = true;
if (old_mode != current_status->flight_mode ||
old_manual_control_mode != current_status->manual_control_mode) {
printf("[cmd] att stabilized mode\n");
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_MANUAL);
state_machine_publish(status_pub, current_status, mavlink_fd);
}
}
}
void update_state_machine_mode_guided(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
if (!current_status->flag_vector_flight_mode_ok) {
mavlink_log_critical(mavlink_fd, "NO POS LOCK, REJ. GUIDED MODE");
tune_error();
return;
}
if (current_status->state_machine == SYSTEM_STATE_GROUND_READY || current_status->state_machine == SYSTEM_STATE_MANUAL || current_status->state_machine == SYSTEM_STATE_AUTO) {
printf("[commander] stabilized mode\n");
printf("[cmd] position guided mode\n");
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_STAB;
current_status->flag_control_manual_enabled = false;
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_STABILIZED);
if (old_mode != current_status->flight_mode) state_machine_publish(status_pub, current_status, mavlink_fd);
}
}
void update_state_machine_mode_auto(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_AUTO;
current_status->flag_control_manual_enabled = true;
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
if (old_mode != current_status->flight_mode) state_machine_publish(status_pub, current_status, mavlink_fd);
if (!current_status->flag_vector_flight_mode_ok) {
mavlink_log_critical(mavlink_fd, "NO POS LOCK, REJ. AUTO MODE");
return;
}
if (current_status->state_machine == SYSTEM_STATE_GROUND_READY || current_status->state_machine == SYSTEM_STATE_MANUAL || current_status->state_machine == SYSTEM_STATE_STABILIZED) {
printf("[commander] auto mode\n");
printf("[cmd] auto mode\n");
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_AUTO;
current_status->flag_control_manual_enabled = false;
current_status->flag_control_attitude_enabled = true;
current_status->flag_control_rates_enabled = true;
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_AUTO);
if (old_mode != current_status->flight_mode) state_machine_publish(status_pub, current_status, mavlink_fd);
}
}
uint8_t update_state_machine_mode_request(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd, uint8_t mode)
{
printf("[commander] Requested new mode: %d\n", (int)mode);
uint8_t ret = 1;
/* Switch on HIL if in standby and not already in HIL mode */
if ((mode & VEHICLE_MODE_FLAG_HIL_ENABLED)
&& !current_status->flag_hil_enabled) {
if ((current_status->state_machine == SYSTEM_STATE_STANDBY)) {
/* Enable HIL on request */
current_status->flag_hil_enabled = true;
ret = OK;
state_machine_publish(status_pub, current_status, mavlink_fd);
publish_armed_status(current_status);
printf("[cmd] Enabling HIL, locking down all actuators for safety.\n\t(Arming the system will not activate them while in HIL mode)\n");
} else if (current_status->state_machine != SYSTEM_STATE_STANDBY &&
current_status->flag_system_armed) {
mavlink_log_critical(mavlink_fd, "REJECTING HIL, disarm first!")
} else {
mavlink_log_critical(mavlink_fd, "REJECTING HIL, not in standby.")
}
}
/* switch manual / auto */
if (mode & VEHICLE_MODE_FLAG_AUTO_ENABLED) {
update_state_machine_mode_auto(status_pub, current_status, mavlink_fd);
} else if (mode & VEHICLE_MODE_FLAG_STABILIZED_ENABLED) {
update_state_machine_mode_stabilized(status_pub, current_status, mavlink_fd);
} else if (mode & VEHICLE_MODE_FLAG_GUIDED_ENABLED) {
update_state_machine_mode_guided(status_pub, current_status, mavlink_fd);
} else if (mode & VEHICLE_MODE_FLAG_MANUAL_INPUT_ENABLED) {
update_state_machine_mode_manual(status_pub, current_status, mavlink_fd);
}
/* vehicle is disarmed, mode requests arming */
if (!(current_status->flag_system_armed) && (mode & VEHICLE_MODE_FLAG_SAFETY_ARMED)) {
/* only arm in standby state */
@ -573,7 +668,7 @@ uint8_t update_state_machine_mode_request(int status_pub, struct vehicle_status_
if (current_status->state_machine == SYSTEM_STATE_STANDBY || current_status->state_machine == SYSTEM_STATE_PREFLIGHT) {
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_GROUND_READY);
ret = OK;
printf("[commander] arming due to command request\n");
printf("[cmd] arming due to command request\n");
}
}
@ -583,26 +678,14 @@ uint8_t update_state_machine_mode_request(int status_pub, struct vehicle_status_
if (current_status->state_machine == SYSTEM_STATE_GROUND_READY) {
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_STANDBY);
ret = OK;
printf("[commander] disarming due to command request\n");
printf("[cmd] disarming due to command request\n");
}
}
/* Switch on HIL if in standby and not already in HIL mode */
if ((current_status->state_machine == SYSTEM_STATE_STANDBY) && (mode & VEHICLE_MODE_FLAG_HIL_ENABLED)
&& !current_status->flag_hil_enabled) {
/* Enable HIL on request */
current_status->flag_hil_enabled = true;
ret = OK;
state_machine_publish(status_pub, current_status, mavlink_fd);
publish_armed_status(current_status);
printf("[commander] Enabling HIL, locking down all actuators for safety.\n\t(Arming the system will not activate them while in HIL mode)\n");
} else if (current_status->state_machine != SYSTEM_STATE_STANDBY) {
mavlink_log_critical(mavlink_fd, "[commander] REJECTING switch to HIL, not in standby.")
}
/* NEVER actually switch off HIL without reboot */
if (current_status->flag_hil_enabled && !(mode & VEHICLE_MODE_FLAG_HIL_ENABLED)) {
fprintf(stderr, "[commander] DENYING request to switch of HIL. Please power cycle (safety reasons)\n");
warnx("DENYING request to switch off HIL. Please power cycle (safety reasons)\n");
mavlink_log_critical(mavlink_fd, "Power-cycle to exit HIL");
ret = ERROR;
}
@ -627,7 +710,8 @@ uint8_t update_state_machine_custom_mode_request(int status_pub, struct vehicle_
if (current_system_state == SYSTEM_STATE_STANDBY || current_system_state == SYSTEM_STATE_PREFLIGHT) {
printf("system will reboot\n");
//global_data_send_mavlink_statustext_message_out("Rebooting autopilot.. ", MAV_SEVERITY_INFO);
mavlink_log_critical(mavlink_fd, "Rebooting..");
usleep(200000);
do_state_update(status_pub, current_status, mavlink_fd, (commander_state_machine_t)SYSTEM_STATE_REBOOT);
ret = 0;
}

9
apps/commander/state_machine_helper.h
View File

@ -127,6 +127,15 @@ void update_state_machine_mode_manual(int status_pub, struct vehicle_status_s *c
*/
void update_state_machine_mode_stabilized(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd);
/**
* Handle state machine if mode switch is guided
*
* @param status_pub file descriptor for state update topic publication
* @param current_status pointer to the current state machine to operate on
* @param mavlink_fd file descriptor for MAVLink statustext messages
*/
void update_state_machine_mode_guided(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd);
/**
* Handle state machine if mode switch is auto
*

44
apps/controllib/fixedwing.cpp
View File

@ -293,17 +293,20 @@ void BlockMultiModeBacksideAutopilot::update()
for (unsigned i = 4; i < NUM_ACTUATOR_CONTROLS; i++)
_actuators.control[i] = 0.0f;
// handle autopilot modes
if (_status.state_machine == SYSTEM_STATE_STABILIZED) {
_stabilization.update(
_ratesCmd.roll, _ratesCmd.pitch, _ratesCmd.yaw,
_att.rollspeed, _att.pitchspeed, _att.yawspeed);
_actuators.control[CH_AIL] = _stabilization.getAileron();
_actuators.control[CH_ELV] = _stabilization.getElevator();
_actuators.control[CH_RDR] = _stabilization.getRudder();
_actuators.control[CH_THR] = _manual.throttle;
// only update guidance in auto mode
if (_status.state_machine == SYSTEM_STATE_AUTO) {
// update guidance
_guide.update(_pos, _att, _posCmd, _lastPosCmd);
}
// XXX handle STABILIZED (loiter on spot) as well
// once the system switches from manual or auto to stabilized
// the setpoint should update to loitering around this position
// handle autopilot modes
if (_status.state_machine == SYSTEM_STATE_AUTO ||
_status.state_machine == SYSTEM_STATE_STABILIZED) {
} else if (_status.state_machine == SYSTEM_STATE_AUTO) {
// update guidance
_guide.update(_pos, _att, _posCmd, _lastPosCmd);
@ -325,10 +328,23 @@ void BlockMultiModeBacksideAutopilot::update()
_actuators.control[CH_THR] = _backsideAutopilot.getThrottle();
} else if (_status.state_machine == SYSTEM_STATE_MANUAL) {
_actuators.control[CH_AIL] = _manual.roll;
_actuators.control[CH_ELV] = _manual.pitch;
_actuators.control[CH_RDR] = _manual.yaw;
_actuators.control[CH_THR] = _manual.throttle;
if (_status.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_DIRECT) {
_actuators.control[CH_AIL] = _manual.roll;
_actuators.control[CH_ELV] = _manual.pitch;
_actuators.control[CH_RDR] = _manual.yaw;
_actuators.control[CH_THR] = _manual.throttle;
} else if (_status.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS) {
_stabilization.update(
_ratesCmd.roll, _ratesCmd.pitch, _ratesCmd.yaw,
_att.rollspeed, _att.pitchspeed, _att.yawspeed);
_actuators.control[CH_AIL] = _stabilization.getAileron();
_actuators.control[CH_ELV] = _stabilization.getElevator();
_actuators.control[CH_RDR] = _stabilization.getRudder();
_actuators.control[CH_THR] = _manual.throttle;
}
}
// update all publications

36
apps/drivers/boards/px4fmu/px4fmu_init.c
View File

@ -148,9 +148,7 @@ __EXPORT int nsh_archinitialize(void)
int result;
/* configure the high-resolution time/callout interface */
#ifdef CONFIG_HRT_TIMER
hrt_init();
#endif
/* configure CPU load estimation */
#ifdef CONFIG_SCHED_INSTRUMENTATION
@ -158,27 +156,21 @@ __EXPORT int nsh_archinitialize(void)
#endif
/* set up the serial DMA polling */
#ifdef SERIAL_HAVE_DMA
{
static struct hrt_call serial_dma_call;
struct timespec ts;
static struct hrt_call serial_dma_call;
struct timespec ts;
/*
* Poll at 1ms intervals for received bytes that have not triggered
* a DMA event.
*/
ts.tv_sec = 0;
ts.tv_nsec = 1000000;
/*
* Poll at 1ms intervals for received bytes that have not triggered
* a DMA event.
*/
ts.tv_sec = 0;
ts.tv_nsec = 1000000;
hrt_call_every(&serial_dma_call,
ts_to_abstime(&ts),
ts_to_abstime(&ts),
(hrt_callout)stm32_serial_dma_poll,
NULL);
}
#endif
message("\r\n");
hrt_call_every(&serial_dma_call,
ts_to_abstime(&ts),
ts_to_abstime(&ts),
(hrt_callout)stm32_serial_dma_poll,
NULL);
// initial LED state
drv_led_start();
@ -233,7 +225,7 @@ __EXPORT int nsh_archinitialize(void)
stm32_configgpio(GPIO_ADC1_IN10);
stm32_configgpio(GPIO_ADC1_IN11);
//stm32_configgpio(GPIO_ADC1_IN12); // XXX is this available?
stm32_configgpio(GPIO_ADC1_IN12);
//stm32_configgpio(GPIO_ADC1_IN13); // jumperable to MPU6000 DRDY on some boards
return OK;

31
apps/drivers/hil/hil.cpp
View File

@ -68,11 +68,11 @@
#include <drivers/device/device.h>
#include <drivers/drv_pwm_output.h>
#include <drivers/drv_gpio.h>
// #include <drivers/boards/HIL/HIL_internal.h>
#include <drivers/drv_hrt.h>
#include <drivers/drv_mixer.h>
#include <systemlib/systemlib.h>
#include <systemlib/mixer/mixer.h>
#include <drivers/drv_mixer.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/actuator_outputs.h>
@ -382,7 +382,6 @@ HIL::task_main()
/* this would be bad... */
if (ret < 0) {
log("poll error %d", errno);
usleep(1000000);
continue;
}
@ -396,16 +395,27 @@ HIL::task_main()
if (_mixers != nullptr) {
/* do mixing */
_mixers->mix(&outputs.output[0], num_outputs);
outputs.noutputs = _mixers->mix(&outputs.output[0], num_outputs);
outputs.timestamp = hrt_absolute_time();
/* iterate actuators */
for (unsigned i = 0; i < num_outputs; i++) {
/* scale for PWM output 900 - 2100us */
outputs.output[i] = 1500 + (600 * outputs.output[i]);
/* output to the servo */
// up_pwm_servo_set(i, outputs.output[i]);
/* last resort: catch NaN, INF and out-of-band errors */
if (i < (unsigned)outputs.noutputs &&
isfinite(outputs.output[i]) &&
outputs.output[i] >= -1.0f &&
outputs.output[i] <= 1.0f) {
/* scale for PWM output 900 - 2100us */
outputs.output[i] = 1500 + (600 * outputs.output[i]);
} else {
/*
* Value is NaN, INF or out of band - set to the minimum value.
* This will be clearly visible on the servo status and will limit the risk of accidentally
* spinning motors. It would be deadly in flight.
*/
outputs.output[i] = 900;
}
}
/* and publish for anyone that cares to see */
@ -419,9 +429,6 @@ HIL::task_main()
/* get new value */
orb_copy(ORB_ID(actuator_armed), _t_armed, &aa);
/* update PWM servo armed status */
// up_pwm_servo_arm(aa.armed);
}
}

49
apps/drivers/px4fmu/fmu.cpp
View File

@ -58,6 +58,7 @@
#include <drivers/drv_pwm_output.h>
#include <drivers/drv_gpio.h>
#include <drivers/boards/px4fmu/px4fmu_internal.h>
#include <drivers/drv_hrt.h>
#include <systemlib/systemlib.h>
#include <systemlib/err.h>
@ -65,6 +66,7 @@
#include <drivers/drv_mixer.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/actuator_controls_effective.h>
#include <uORB/topics/actuator_outputs.h>
#include <systemlib/err.h>
@ -97,6 +99,7 @@ private:
int _t_actuators;
int _t_armed;
orb_advert_t _t_outputs;
orb_advert_t _t_actuators_effective;
unsigned _num_outputs;
bool _primary_pwm_device;
@ -162,6 +165,7 @@ PX4FMU::PX4FMU() :
_t_actuators(-1),
_t_armed(-1),
_t_outputs(0),
_t_actuators_effective(0),
_num_outputs(0),
_primary_pwm_device(false),
_task_should_exit(false),
@ -319,6 +323,13 @@ PX4FMU::task_main()
_t_outputs = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1),
&outputs);
/* advertise the effective control inputs */
actuator_controls_effective_s controls_effective;
memset(&controls_effective, 0, sizeof(controls_effective));
/* advertise the effective control inputs */
_t_actuators_effective = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE : ORB_ID(actuator_controls_effective_1),
&controls_effective);
pollfd fds[2];
fds[0].fd = _t_actuators;
fds[0].events = POLLIN;
@ -336,8 +347,16 @@ PX4FMU::task_main()
if (_current_update_rate != _update_rate) {
int update_rate_in_ms = int(1000 / _update_rate);
if (update_rate_in_ms < 2)
/* reject faster than 500 Hz updates */
if (update_rate_in_ms < 2) {
update_rate_in_ms = 2;
_update_rate = 500;
}
/* reject slower than 50 Hz updates */
if (update_rate_in_ms > 20) {
update_rate_in_ms = 20;
_update_rate = 50;
}
orb_set_interval(_t_actuators, update_rate_in_ms);
up_pwm_servo_set_rate(_update_rate);
@ -364,20 +383,39 @@ PX4FMU::task_main()
if (_mixers != nullptr) {
/* do mixing */
_mixers->mix(&outputs.output[0], num_outputs);
outputs.noutputs = _mixers->mix(&outputs.output[0], num_outputs);
outputs.timestamp = hrt_absolute_time();
// XXX output actual limited values
memcpy(&controls_effective, &_controls, sizeof(controls_effective));
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE : ORB_ID(actuator_controls_effective_1), _t_actuators_effective, &controls_effective);
/* iterate actuators */
for (unsigned i = 0; i < num_outputs; i++) {
/* scale for PWM output 900 - 2100us */
outputs.output[i] = 1500 + (600 * outputs.output[i]);
/* last resort: catch NaN, INF and out-of-band errors */
if (i < outputs.noutputs &&
isfinite(outputs.output[i]) &&
outputs.output[i] >= -1.0f &&
outputs.output[i] <= 1.0f) {
/* scale for PWM output 900 - 2100us */
outputs.output[i] = 1500 + (600 * outputs.output[i]);
} else {
/*
* Value is NaN, INF or out of band - set to the minimum value.
* This will be clearly visible on the servo status and will limit the risk of accidentally
* spinning motors. It would be deadly in flight.
*/
outputs.output[i] = 900;
}
/* output to the servo */
up_pwm_servo_set(i, outputs.output[i]);
}
/* and publish for anyone that cares to see */
orb_publish(ORB_ID_VEHICLE_CONTROLS, _t_outputs, &outputs);
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), _t_outputs, &outputs);
}
}
@ -394,6 +432,7 @@ PX4FMU::task_main()
}
::close(_t_actuators);
::close(_t_actuators_effective);
::close(_t_armed);
/* make sure servos are off */

141
apps/drivers/px4io/px4io.cpp
View File

@ -55,6 +55,7 @@
#include <unistd.h>
#include <termios.h>
#include <fcntl.h>
#include <math.h>
#include <arch/board/board.h>
@ -70,9 +71,13 @@
#include <systemlib/hx_stream.h>
#include <systemlib/err.h>
#include <systemlib/systemlib.h>
#include <systemlib/scheduling_priorities.h>
#include <systemlib/param/param.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/actuator_controls_effective.h>
#include <uORB/topics/actuator_outputs.h>
#include <uORB/topics/vehicle_status.h>
#include <uORB/topics/rc_channels.h>
#include <uORB/topics/battery_status.h>
@ -90,10 +95,18 @@ public:
virtual int ioctl(file *filp, int cmd, unsigned long arg);
/**
* Set the PWM via serial update rate
* @warning this directly affects CPU load
*/
int set_pwm_rate(int hz);
bool dump_one;
private:
// XXX
static const unsigned _max_actuators = PX4IO_CONTROL_CHANNELS;
unsigned _update_rate; ///< serial send rate in Hz
int _serial_fd; ///< serial interface to PX4IO
hx_stream_t _io_stream; ///< HX protocol stream
@ -105,8 +118,13 @@ private:
int _t_actuators; ///< actuator output topic
actuator_controls_s _controls; ///< actuator outputs
orb_advert_t _t_actuators_effective; ///< effective actuator controls topic
actuator_controls_effective_s _controls_effective; ///< effective controls
int _t_armed; ///< system armed control topic
actuator_armed_s _armed; ///< system armed state
int _t_vstatus; ///< system / vehicle status
vehicle_status_s _vstatus; ///< overall system state
orb_advert_t _to_input_rc; ///< rc inputs from io
rc_input_values _input_rc; ///< rc input values
@ -191,13 +209,16 @@ PX4IO *g_dev;
PX4IO::PX4IO() :
CDev("px4io", "/dev/px4io"),
dump_one(false),
_update_rate(50),
_serial_fd(-1),
_io_stream(nullptr),
_task(-1),
_task_should_exit(false),
_connected(false),
_t_actuators(-1),
_t_actuators_effective(-1),
_t_armed(-1),
_t_vstatus(-1),
_t_outputs(-1),
_mix_buf(nullptr),
_mix_buf_len(0),
@ -205,7 +226,7 @@ PX4IO::PX4IO() :
_relays(0),
_switch_armed(false),
_send_needed(false),
_config_needed(false)
_config_needed(true)
{
/* we need this potentially before it could be set in task_main */
g_dev = this;
@ -253,7 +274,7 @@ PX4IO::init()
}
/* start the IO interface task */
_task = task_create("px4io", SCHED_PRIORITY_DEFAULT, 4096, (main_t)&PX4IO::task_main_trampoline, nullptr);
_task = task_create("px4io", SCHED_PRIORITY_ACTUATOR_OUTPUTS, 4096, (main_t)&PX4IO::task_main_trampoline, nullptr);
if (_task < 0) {
debug("task start failed: %d", errno);
@ -279,6 +300,17 @@ PX4IO::init()
return OK;
}
int
PX4IO::set_pwm_rate(int hz)
{
if (hz > 0 && hz <= 400) {
_update_rate = hz;
return OK;
} else {
return -EINVAL;
}
}
void
PX4IO::task_main_trampoline(int argc, char *argv[])
{
@ -288,7 +320,8 @@ PX4IO::task_main_trampoline(int argc, char *argv[])
void
PX4IO::task_main()
{
debug("starting");
log("starting");
unsigned update_rate_in_ms;
/* open the serial port */
_serial_fd = ::open("/dev/ttyS2", O_RDWR);
@ -328,12 +361,20 @@ PX4IO::task_main()
_t_actuators = orb_subscribe(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS :
ORB_ID(actuator_controls_1));
/* convert the update rate in hz to milliseconds, rounding down if necessary */
//int update_rate_in_ms = int(1000 / _update_rate);
orb_set_interval(_t_actuators, 20); /* XXX 50Hz hardcoded for now */
update_rate_in_ms = 1000 / _update_rate;
orb_set_interval(_t_actuators, update_rate_in_ms);
_t_armed = orb_subscribe(ORB_ID(actuator_armed));
orb_set_interval(_t_armed, 200); /* 5Hz update rate */
_t_vstatus = orb_subscribe(ORB_ID(vehicle_status));
orb_set_interval(_t_vstatus, 200); /* 5Hz update rate max. */
/* advertise the limited control inputs */
memset(&_controls_effective, 0, sizeof(_controls_effective));
_t_actuators_effective = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE : ORB_ID(actuator_controls_1),
&_controls_effective);
/* advertise the mixed control outputs */
memset(&_outputs, 0, sizeof(_outputs));
_t_outputs = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1),
@ -348,13 +389,15 @@ PX4IO::task_main()
_to_battery = -1;
/* poll descriptor */
pollfd fds[3];
pollfd fds[4];
fds[0].fd = _serial_fd;
fds[0].events = POLLIN;
fds[1].fd = _t_actuators;
fds[1].events = POLLIN;
fds[2].fd = _t_armed;
fds[2].events = POLLIN;
fds[3].fd = _t_vstatus;
fds[3].events = POLLIN;
debug("ready");
@ -405,12 +448,11 @@ PX4IO::task_main()
orb_copy(ORB_ID(actuator_armed), _t_armed, &_armed);
_send_needed = true;
}
}
/* send an update to IO if required */
if (_send_needed) {
_send_needed = false;
io_send();
if (fds[3].revents & POLLIN) {
orb_copy(ORB_ID(vehicle_status), _t_vstatus, &_vstatus);
_send_needed = true;
}
}
/* send a config packet to IO if required */
@ -427,6 +469,12 @@ PX4IO::task_main()
_mix_buf = nullptr;
_mix_buf_len = 0;
}
/* send an update to IO if required */
if (_send_needed) {
_send_needed = false;
io_send();
}
}
unlock();
@ -565,20 +613,27 @@ PX4IO::io_send()
cmd.f2i_magic = F2I_MAGIC;
/* set outputs */
for (unsigned i = 0; i < _max_actuators; i++)
for (unsigned i = 0; i < _max_actuators; i++) {
cmd.output_control[i] = _outputs.output[i];
}
/* publish as we send */
_outputs.timestamp = hrt_absolute_time();
/* XXX needs to be based off post-mix values from the IO side */
orb_publish(ORB_ID_VEHICLE_CONTROLS, _t_outputs, &_outputs);
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), _t_outputs, &_outputs);
/* update relays */
for (unsigned i = 0; i < PX4IO_RELAY_CHANNELS; i++)
cmd.relay_state[i] = (_relays & (1<< i)) ? true : false;
/* armed and not locked down */
/* armed and not locked down -> arming ok */
cmd.arm_ok = (_armed.armed && !_armed.lockdown);
/* indicate that full autonomous position control / vector flight mode is available */
cmd.vector_flight_mode_ok = _vstatus.flag_vector_flight_mode_ok;
/* allow manual override on IO (not allowed for multirotors or other systems with SAS) */
cmd.manual_override_ok = _vstatus.flag_external_manual_override_ok;
/* set desired PWM output rate */
cmd.servo_rate = _update_rate;
ret = hx_stream_send(_io_stream, &cmd, sizeof(cmd));
if (ret)
@ -593,6 +648,47 @@ PX4IO::config_send()
cfg.f2i_config_magic = F2I_CONFIG_MAGIC;
int val;
/* maintaing the standard order of Roll, Pitch, Yaw, Throttle */
param_get(param_find("RC_MAP_ROLL"), &val);
cfg.rc_map[0] = val;
param_get(param_find("RC_MAP_PITCH"), &val);
cfg.rc_map[1] = val;
param_get(param_find("RC_MAP_YAW"), &val);
cfg.rc_map[2] = val;
param_get(param_find("RC_MAP_THROTTLE"), &val);
cfg.rc_map[3] = val;
/* set the individual channel properties */
char nbuf[16];
float float_val;
for (unsigned i = 0; i < 4; i++) {
sprintf(nbuf, "RC%d_MIN", i + 1);
param_get(param_find(nbuf), &float_val);
cfg.rc_min[i] = float_val;
}
for (unsigned i = 0; i < 4; i++) {
sprintf(nbuf, "RC%d_TRIM", i + 1);
param_get(param_find(nbuf), &float_val);
cfg.rc_trim[i] = float_val;
}
for (unsigned i = 0; i < 4; i++) {
sprintf(nbuf, "RC%d_MAX", i + 1);
param_get(param_find(nbuf), &float_val);
cfg.rc_max[i] = float_val;
}
for (unsigned i = 0; i < 4; i++) {
sprintf(nbuf, "RC%d_REV", i + 1);
param_get(param_find(nbuf), &float_val);
cfg.rc_rev[i] = float_val;
}
for (unsigned i = 0; i < 4; i++) {
sprintf(nbuf, "RC%d_DZ", i + 1);
param_get(param_find(nbuf), &float_val);
cfg.rc_dz[i] = float_val;
}
ret = hx_stream_send(_io_stream, &cfg, sizeof(cfg));
if (ret)
@ -779,7 +875,7 @@ test(void)
void
monitor(void)
{
unsigned cancels = 4;
unsigned cancels = 3;
printf("Hit <enter> three times to exit monitor mode\n");
for (;;) {
@ -801,6 +897,7 @@ monitor(void)
g_dev->dump_one = true;
}
}
}
int
@ -822,6 +919,16 @@ px4io_main(int argc, char *argv[])
errx(1, "driver init failed");
}
/* look for the optional pwm update rate for the supported modes */
if (strcmp(argv[2], "-u") == 0 || strcmp(argv[2], "--update-rate") == 0) {
if (argc > 2 + 1) {
g_dev->set_pwm_rate(atoi(argv[2 + 1]));
} else {
fprintf(stderr, "missing argument for pwm update rate (-u)\n");
return 1;
}
}
exit(0);
}

23
apps/fixedwing_att_control/fixedwing_att_control_att.c
View File

@ -112,8 +112,9 @@ static int parameters_update(const struct fw_pos_control_param_handles *h, struc
}
int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att,
struct vehicle_rates_setpoint_s *rates_sp)
const struct vehicle_attitude_s *att,
const float speed_body[],
struct vehicle_rates_setpoint_s *rates_sp)
{
static int counter = 0;
static bool initialized = false;
@ -125,8 +126,7 @@ int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att
static PID_t pitch_controller;
if(!initialized)
{
if (!initialized) {
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim, PID_MODE_DERIVATIV_NONE); //P Controller
@ -145,12 +145,21 @@ int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att
/* Roll (P) */
rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body, att->roll, 0, 0);
/* Pitch (P) */
float pitch_sp_rollcompensation = att_sp->pitch_body + p.pitch_roll_compensation_p * att_sp->roll_body;
rates_sp->pitch = pid_calculate(&pitch_controller, pitch_sp_rollcompensation, att->pitch, 0, 0);
/* compensate feedforward for loss of lift due to non-horizontal angle of wing */
float pitch_sp_rollcompensation = p.pitch_roll_compensation_p * fabsf(sinf(att_sp->roll_body));
/* set pitch plus feedforward roll compensation */
rates_sp->pitch = pid_calculate(&pitch_controller,
att_sp->pitch_body + pitch_sp_rollcompensation,
att->pitch, 0, 0);
/* Yaw (from coordinated turn constraint or lateral force) */
//TODO
rates_sp->yaw = (att->rollspeed * rates_sp->roll + 9.81f * sinf(att->roll) * cosf(att->pitch) + speed_body[0] * rates_sp->pitch * sinf(att->roll))
/ (speed_body[0] * cosf(att->roll) * cosf(att->pitch) + speed_body[2] * sinf(att->pitch));
// printf("rates_sp->yaw %.4f \n", (double)rates_sp->yaw);
counter++;

6
apps/fixedwing_att_control/fixedwing_att_control_att.h
View File

@ -41,9 +41,11 @@
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_global_position.h>
int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att,
struct vehicle_rates_setpoint_s *rates_sp);
const struct vehicle_attitude_s *att,
const float speed_body[],
struct vehicle_rates_setpoint_s *rates_sp);
#endif /* FIXEDWING_ATT_CONTROL_ATT_H_ */

278
apps/fixedwing_att_control/fixedwing_att_control_main.c
View File

@ -58,40 +58,16 @@
#include <uORB/topics/manual_control_setpoint.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/debug_key_value.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
#include <fixedwing_att_control_rate.h>
#include <fixedwing_att_control_att.h>
/*
* Controller parameters, accessible via MAVLink
*
*/
// Roll control parameters
PARAM_DEFINE_FLOAT(FW_ROLLR_P, 0.9f);
PARAM_DEFINE_FLOAT(FW_ROLLR_I, 0.2f);
PARAM_DEFINE_FLOAT(FW_ROLLR_AWU, 0.9f);
PARAM_DEFINE_FLOAT(FW_ROLLR_LIM, 0.7f); // Roll rate limit in radians/sec, applies to the roll controller
PARAM_DEFINE_FLOAT(FW_ROLL_P, 4.0f);
PARAM_DEFINE_FLOAT(FW_PITCH_RCOMP, 0.1f);
//Pitch control parameters
PARAM_DEFINE_FLOAT(FW_PITCHR_P, 0.8f);
PARAM_DEFINE_FLOAT(FW_PITCHR_I, 0.2f);
PARAM_DEFINE_FLOAT(FW_PITCHR_AWU, 0.8f);
PARAM_DEFINE_FLOAT(FW_PITCHR_LIM, 0.35f); // Pitch rate limit in radians/sec, applies to the pitch controller
PARAM_DEFINE_FLOAT(FW_PITCH_P, 8.0f);
//Yaw control parameters //XXX TODO this is copy paste, asign correct values
PARAM_DEFINE_FLOAT(FW_YAWR_P, 0.3f);
PARAM_DEFINE_FLOAT(FW_YAWR_I, 0.0f);
PARAM_DEFINE_FLOAT(FW_YAWR_AWU, 0.0f);
PARAM_DEFINE_FLOAT(FW_YAWR_LIM, 0.35f); // Yaw rate limit in radians/sec
/* Prototypes */
/**
* Deamon management function.
@ -117,118 +93,211 @@ static int deamon_task; /**< Handle of deamon task / thread */
int fixedwing_att_control_thread_main(int argc, char *argv[])
{
/* read arguments */
bool verbose = false;
bool verbose = false;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
}
/* welcome user */
printf("[fixedwing att control] started\n");
/* declare and safely initialize all structs */
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_attitude_setpoint_s att_sp;
memset(&att_sp, 0, sizeof(att_sp));
struct vehicle_rates_setpoint_s rates_sp;
memset(&rates_sp, 0, sizeof(rates_sp));
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct manual_control_setpoint_s manual_sp;
memset(&manual_sp, 0, sizeof(manual_sp));
struct vehicle_status_s vstatus;
memset(&vstatus, 0, sizeof(vstatus));
/* output structs */
struct actuator_controls_s actuators;
memset(&actuators, 0, sizeof(actuators));
/* publish actuator controls */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++) {
actuators.control[i] = 0.0f;
}
orb_advert_t actuator_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &actuators);
orb_advert_t rates_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint), &rates_sp);
/* subscribe */
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
int manual_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
int vstatus_sub = orb_subscribe(ORB_ID(vehicle_status));
/* Setup of loop */
float gyro[3] = {0.0f, 0.0f, 0.0f};
float speed_body[3] = {0.0f, 0.0f, 0.0f};
struct pollfd fds = { .fd = att_sub, .events = POLLIN };
while (!thread_should_exit) {
/* wait for a sensor update, check for exit condition every 500 ms */
poll(&fds, 1, 500);
/* Check if there is a new position measurement or attitude setpoint */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool att_sp_updated;
orb_check(att_sp_sub, &att_sp_updated);
/* get a local copy of attitude */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
if (att_sp_updated)
orb_copy(ORB_ID(vehicle_attitude_setpoint), att_sp_sub, &att_sp);
if (pos_updated) {
orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
if (att.R_valid) {
speed_body[0] = att.R[0][0] * global_pos.vx + att.R[0][1] * global_pos.vy + att.R[0][2] * global_pos.vz;
speed_body[1] = att.R[1][0] * global_pos.vx + att.R[1][1] * global_pos.vy + att.R[1][2] * global_pos.vz;
speed_body[2] = att.R[2][0] * global_pos.vx + att.R[2][1] * global_pos.vy + att.R[2][2] * global_pos.vz;
} else {
speed_body[0] = 0;
speed_body[1] = 0;
speed_body[2] = 0;
printf("FW ATT CONTROL: Did not get a valid R\n");
}
}
/* welcome user */
printf("[fixedwing att_control] started\n");
orb_copy(ORB_ID(manual_control_setpoint), manual_sp_sub, &manual_sp);
orb_copy(ORB_ID(vehicle_status), vstatus_sub, &vstatus);
/* declare and safely initialize all structs */
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_attitude_setpoint_s att_sp;
memset(&att_sp, 0, sizeof(att_sp));
struct vehicle_rates_setpoint_s rates_sp;
memset(&rates_sp, 0, sizeof(rates_sp));
struct manual_control_setpoint_s manual_sp;
memset(&manual_sp, 0, sizeof(manual_sp));
struct vehicle_status_s vstatus;
memset(&vstatus, 0, sizeof(vstatus));
gyro[0] = att.rollspeed;
gyro[1] = att.pitchspeed;
gyro[2] = att.yawspeed;
// static struct debug_key_value_s debug_output;
// memset(&debug_output, 0, sizeof(debug_output));
/* control */
/* output structs */
struct actuator_controls_s actuators;
memset(&actuators, 0, sizeof(actuators));
if (vstatus.state_machine == SYSTEM_STATE_AUTO ||
vstatus.state_machine == SYSTEM_STATE_STABILIZED) {
/* attitude control */
fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
/* angular rate control */
fixedwing_att_control_rates(&rates_sp, gyro, &actuators);
/* publish actuator controls */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++) {
actuators.control[i] = 0.0f;
}
orb_advert_t actuator_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &actuators);
// orb_advert_t debug_pub = orb_advertise(ORB_ID(debug_key_value), &debug_output);
// debug_output.key[0] = '1';
/* pass through throttle */
actuators.control[3] = att_sp.thrust;
/* set flaps to zero */
actuators.control[4] = 0.0f;
/* subscribe */
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
int manual_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
int vstatus_sub = orb_subscribe(ORB_ID(vehicle_status));
} else if (vstatus.state_machine == SYSTEM_STATE_MANUAL) {
if (vstatus.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS) {
/* Setup of loop */
float gyro[3] = {0.0f, 0.0f, 0.0f};
struct pollfd fds = { .fd = att_sub, .events = POLLIN };
/* if the RC signal is lost, try to stay level and go slowly back down to ground */
if (vstatus.rc_signal_lost) {
while(!thread_should_exit)
{
/* wait for a sensor update, check for exit condition every 500 ms */
poll(&fds, 1, 500);
/* put plane into loiter */
att_sp.roll_body = 0.3f;
att_sp.pitch_body = 0.0f;
/* get a local copy of attitude */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
orb_copy(ORB_ID(vehicle_attitude_setpoint), att_sp_sub, &att_sp);
orb_copy(ORB_ID(manual_control_setpoint), manual_sp_sub, &manual_sp);
orb_copy(ORB_ID(vehicle_status), vstatus_sub, &vstatus);
/* limit throttle to 60 % of last value if sane */
if (isfinite(manual_sp.throttle) &&
(manual_sp.throttle >= 0.0f) &&
(manual_sp.throttle <= 1.0f)) {
att_sp.thrust = 0.6f * manual_sp.throttle;
gyro[0] = att.rollspeed;
gyro[1] = att.pitchspeed;
gyro[2] = att.yawspeed;
} else {
att_sp.thrust = 0.0f;
}
/* Control */
att_sp.yaw_body = 0;
if (vstatus.state_machine == SYSTEM_STATE_AUTO) {
/* Attitude Control */
fixedwing_att_control_attitude(&att_sp,
&att,
&rates_sp);
// XXX disable yaw control, loiter
/* Attitude Rate Control */
} else {
att_sp.roll_body = manual_sp.roll;
att_sp.pitch_body = manual_sp.pitch;
att_sp.yaw_body = 0;
att_sp.thrust = manual_sp.throttle;
}
att_sp.timestamp = hrt_absolute_time();
/* attitude control */
fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
/* angular rate control */
fixedwing_att_control_rates(&rates_sp, gyro, &actuators);
//REMOVEME XXX
actuators.control[3] = 0.7f;
/* pass through throttle */
actuators.control[3] = att_sp.thrust;
// debug_output.value = rates_sp.pitch;
// orb_publish(ORB_ID(debug_key_value), debug_pub, &debug_output);
} else if (vstatus.state_machine == SYSTEM_STATE_MANUAL) {
/* pass through flaps */
if (isfinite(manual_sp.flaps)) {
actuators.control[4] = manual_sp.flaps;
} else {
actuators.control[4] = 0.0f;
}
} else if (vstatus.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_DIRECT) {
/* directly pass through values */
actuators.control[0] = manual_sp.roll;
/* positive pitch means negative actuator -> pull up */
actuators.control[1] = -manual_sp.pitch;
actuators.control[1] = manual_sp.pitch;
actuators.control[2] = manual_sp.yaw;
actuators.control[3] = manual_sp.throttle;
}
/* publish output */
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
if (isfinite(manual_sp.flaps)) {
actuators.control[4] = manual_sp.flaps;
} else {
actuators.control[4] = 0.0f;
}
}
}
printf("[fixedwing_att_control] exiting, stopping all motors.\n");
thread_running = false;
/* publish rates */
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_pub, &rates_sp);
/* kill all outputs */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++)
actuators.control[i] = 0.0f;
/* sanity check and publish actuator outputs */
if (isfinite(actuators.control[0]) &&
isfinite(actuators.control[1]) &&
isfinite(actuators.control[2]) &&
isfinite(actuators.control[3])) {
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
}
}
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
printf("[fixedwing_att_control] exiting, stopping all motors.\n");
thread_running = false;
/* kill all outputs */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++)
actuators.control[i] = 0.0f;
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
close(att_sub);
close(actuator_pub);
close(att_sub);
close(actuator_pub);
close(rates_pub);
fflush(stdout);
exit(0);
fflush(stdout);
exit(0);
return 0;
return 0;
}
@ -239,6 +308,7 @@ usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: fixedwing_att_control {start|stop|status}\n\n");
exit(1);
}
@ -268,7 +338,7 @@ int fixedwing_att_control_main(int argc, char *argv[])
deamon_task = task_spawn("fixedwing_att_control",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 20,
4096,
2048,
fixedwing_att_control_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
thread_running = true;
@ -283,9 +353,11 @@ int fixedwing_att_control_main(int argc, char *argv[])
if (!strcmp(argv[1], "status")) {
if (thread_running) {
printf("\tfixedwing_att_control is running\n");
} else {
printf("\tfixedwing_att_control not started\n");
}
exit(0);
}

72
apps/fixedwing_att_control/fixedwing_att_control_rate.c
View File

@ -1,7 +1,7 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Thomas Gubler <thomasgubler@student.ethz.ch>
* Author: Thomas Gubler <thomasgubler@student.ethz.ch>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
@ -34,6 +34,8 @@
/**
* @file fixedwing_att_control_rate.c
* Implementation of a fixed wing attitude controller.
*
* @author Thomas Gubler <thomasgubler@student.ethz.ch>
*/
#include <fixedwing_att_control_rate.h>
@ -59,9 +61,33 @@
#include <systemlib/geo/geo.h>
#include <systemlib/systemlib.h>
/*
* Controller parameters, accessible via MAVLink
*
*/
// Roll control parameters
PARAM_DEFINE_FLOAT(FW_ROLLR_P, 0.9f);
PARAM_DEFINE_FLOAT(FW_ROLLR_I, 0.2f);
PARAM_DEFINE_FLOAT(FW_ROLLR_AWU, 0.9f);
PARAM_DEFINE_FLOAT(FW_ROLLR_LIM, 0.7f); // Roll rate limit in radians/sec, applies to the roll controller
PARAM_DEFINE_FLOAT(FW_ROLL_P, 4.0f);
PARAM_DEFINE_FLOAT(FW_PITCH_RCOMP, 0.1f);
//Pitch control parameters
PARAM_DEFINE_FLOAT(FW_PITCHR_P, 0.8f);
PARAM_DEFINE_FLOAT(FW_PITCHR_I, 0.2f);
PARAM_DEFINE_FLOAT(FW_PITCHR_AWU, 0.8f);
PARAM_DEFINE_FLOAT(FW_PITCHR_LIM, 0.35f); // Pitch rate limit in radians/sec, applies to the pitch controller
PARAM_DEFINE_FLOAT(FW_PITCH_P, 8.0f);
//Yaw control parameters //XXX TODO this is copy paste, asign correct values
PARAM_DEFINE_FLOAT(FW_YAWR_P, 0.3f);
PARAM_DEFINE_FLOAT(FW_YAWR_I, 0.0f);
PARAM_DEFINE_FLOAT(FW_YAWR_AWU, 0.0f);
PARAM_DEFINE_FLOAT(FW_YAWR_LIM, 0.35f); // Yaw rate limit in radians/sec
/* feedforward compensation */
PARAM_DEFINE_FLOAT(FW_PITCH_THR_P, 0.1f); /**< throttle to pitch coupling feedforward */
struct fw_rate_control_params {
float rollrate_p;
@ -73,7 +99,7 @@ struct fw_rate_control_params {
float yawrate_p;
float yawrate_i;
float yawrate_awu;
float pitch_thr_ff;
};
struct fw_rate_control_param_handles {
@ -86,7 +112,7 @@ struct fw_rate_control_param_handles {
param_t yawrate_p;
param_t yawrate_i;
param_t yawrate_awu;
param_t pitch_thr_ff;
};
@ -98,17 +124,18 @@ static int parameters_update(const struct fw_rate_control_param_handles *h, stru
static int parameters_init(struct fw_rate_control_param_handles *h)
{
/* PID parameters */
h->rollrate_p = param_find("FW_ROLLR_P"); //TODO define rate params for fixed wing
h->rollrate_i = param_find("FW_ROLLR_I");
h->rollrate_awu = param_find("FW_ROLLR_AWU");
h->rollrate_p = param_find("FW_ROLLR_P"); //TODO define rate params for fixed wing
h->rollrate_i = param_find("FW_ROLLR_I");
h->rollrate_awu = param_find("FW_ROLLR_AWU");
h->pitchrate_p = param_find("FW_PITCHR_P");
h->pitchrate_i = param_find("FW_PITCHR_I");
h->pitchrate_p = param_find("FW_PITCHR_P");
h->pitchrate_i = param_find("FW_PITCHR_I");
h->pitchrate_awu = param_find("FW_PITCHR_AWU");
h->yawrate_p = param_find("FW_YAWR_P");
h->yawrate_i = param_find("FW_YAWR_I");
h->yawrate_awu = param_find("FW_YAWR_AWU");
h->yawrate_p = param_find("FW_YAWR_P");
h->yawrate_i = param_find("FW_YAWR_I");
h->yawrate_awu = param_find("FW_YAWR_AWU");
h->pitch_thr_ff = param_find("FW_PITCH_THR_P");
return OK;
}
@ -124,14 +151,14 @@ static int parameters_update(const struct fw_rate_control_param_handles *h, stru
param_get(h->yawrate_p, &(p->yawrate_p));
param_get(h->yawrate_i, &(p->yawrate_i));
param_get(h->yawrate_awu, &(p->yawrate_awu));
param_get(h->pitch_thr_ff, &(p->pitch_thr_ff));
return OK;
}
int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[],
struct actuator_controls_s *actuators)
const float rates[],
struct actuator_controls_s *actuators)
{
static int counter = 0;
static bool initialized = false;
@ -147,8 +174,7 @@ int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
if(!initialized)
{
if (!initialized) {
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the controller layout is with a PI rate controller
@ -167,12 +193,14 @@ int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
}
/* Roll Rate (PI) */
actuators->control[0] = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0, deltaT);
actuators->control[1] = pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0, deltaT); //TODO: (-) sign comes from the elevator (positive --> deflection downwards), this has to be moved to the mixer...
actuators->control[2] = 0;//pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0, deltaT); //XXX TODO disabled for now
/* roll rate (PI) */
actuators->control[0] = pid_calculate(&roll_rate_controller, rate_sp->roll, rates[0], 0.0f, deltaT);
/* pitch rate (PI) */
actuators->control[1] = pid_calculate(&pitch_rate_controller, rate_sp->pitch, rates[1], 0.0f, deltaT);
/* set pitch minus feedforward throttle compensation (nose pitches up from throttle */
actuators->control[1] += (-1.0f) * p.pitch_thr_ff * rate_sp->thrust;
/* yaw rate (PI) */
actuators->control[2] = pid_calculate(&yaw_rate_controller, rate_sp->yaw, rates[2], 0.0f, deltaT);
counter++;

4
apps/fixedwing_att_control/fixedwing_att_control_rate.h
View File

@ -42,7 +42,7 @@
#include <uORB/topics/actuator_controls.h>
int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[],
struct actuator_controls_s *actuators);
const float rates[],
struct actuator_controls_s *actuators);
#endif /* FIXEDWING_ATT_CONTROL_RATE_H_ */

44
apps/fixedwing_control/Makefile
View File

@ -1,44 +0,0 @@
############################################################################
#
# Copyright (C) 2012 PX4 Development Team. All rights reserved.
#
# Redistribution and use in source and binary forms, with or without
# modification, are permitted provided that the following conditions
# are met:
#
# 1. Redistributions of source code must retain the above copyright
# notice, this list of conditions and the following disclaimer.
# 2. Redistributions in binary form must reproduce the above copyright
# notice, this list of conditions and the following disclaimer in
# the documentation and/or other materials provided with the
# distribution.
# 3. Neither the name PX4 nor the names of its contributors may be
# used to endorse or promote products derived from this software
# without specific prior written permission.
#
# THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
# "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
# LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
# FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
# COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
# INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
# BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
# OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
# AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
# LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
# ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
# POSSIBILITY OF SUCH DAMAGE.
#
############################################################################
#
# fixedwing_control Application
#
APPNAME = fixedwing_control
PRIORITY = SCHED_PRIORITY_MAX - 1
STACKSIZE = 4096
CSRCS = fixedwing_control.c
include $(APPDIR)/mk/app.mk

566
apps/fixedwing_control/fixedwing_control.c
View File

@ -1,566 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Author: @author Ivan Ovinnikov <oivan@ethz.ch>
* Modifications: Doug Weibel <douglas.weibel@colorado.edu>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file fixedwing_control.c
* Implementation of a fixed wing attitude and position controller.
*/
#include <nuttx/config.h>
#include <stdio.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <fcntl.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <time.h>
#include <drivers/drv_hrt.h>
#include <arch/board/board.h>
#include <uORB/uORB.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_global_position_setpoint.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_status.h>
#include <uORB/topics/vehicle_attitude_setpoint.h>
#include <uORB/topics/manual_control_setpoint.h>
#include <uORB/topics/actuator_controls.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/systemlib.h>
#include <uORB/topics/debug_key_value.h>
static bool thread_should_exit = false; /**< Deamon exit flag */
static bool thread_running = false; /**< Deamon status flag */
static int deamon_task; /**< Handle of deamon task / thread */
/**
* Deamon management function.
*/
__EXPORT int fixedwing_control_main(int argc, char *argv[]);
/**
* Mainloop of deamon.
*/
int fixedwing_control_thread_main(int argc, char *argv[]);
/**
* Print the correct usage.
*/
static void usage(const char *reason);
/*
* Controller parameters, accessible via MAVLink
*
*/
// Roll control parameters
PARAM_DEFINE_FLOAT(FW_ROLLRATE_P, 0.3f);
// Need to add functionality to suppress integrator windup while on the ground
// Suggested value of FW_ROLLRATE_I is 0.0 till this is in place
PARAM_DEFINE_FLOAT(FW_ROLLRATE_I, 0.0f);
PARAM_DEFINE_FLOAT(FW_ROLLRATE_AWU, 0.0f);
PARAM_DEFINE_FLOAT(FW_ROLLRATE_LIM, 0.7f); // Roll rate limit in radians/sec
PARAM_DEFINE_FLOAT(FW_ROLL_P, 0.3f);
PARAM_DEFINE_FLOAT(FW_ROLL_LIM, 0.7f); // Roll angle limit in radians
//Pitch control parameters
PARAM_DEFINE_FLOAT(FW_PITCHRATE_P, 0.3f);
// Need to add functionality to suppress integrator windup while on the ground
// Suggested value of FW_PITCHRATE_I is 0.0 till this is in place
PARAM_DEFINE_FLOAT(FW_PITCHRATE_I, 0.0f);
PARAM_DEFINE_FLOAT(FW_PITCHRATE_AWU, 0.0f);
PARAM_DEFINE_FLOAT(FW_PITCHRATE_LIM, 0.35f); // Pitch rate limit in radians/sec
PARAM_DEFINE_FLOAT(FW_PITCH_P, 0.3f);
PARAM_DEFINE_FLOAT(FW_PITCH_LIM, 0.35f); // Pitch angle limit in radians
struct fw_att_control_params {
float rollrate_p;
float rollrate_i;
float rollrate_awu;
float rollrate_lim;
float roll_p;
float roll_lim;
float pitchrate_p;
float pitchrate_i;
float pitchrate_awu;
float pitchrate_lim;
float pitch_p;
float pitch_lim;
};
struct fw_att_control_param_handles {
param_t rollrate_p;
param_t rollrate_i;
param_t rollrate_awu;
param_t rollrate_lim;
param_t roll_p;
param_t roll_lim;
param_t pitchrate_p;
param_t pitchrate_i;
param_t pitchrate_awu;
param_t pitchrate_lim;
param_t pitch_p;
param_t pitch_lim;
};
// TO_DO - Navigation control will be moved to a separate app
// Attitude control will just handle the inner angle and rate loops
// to control pitch and roll, and turn coordination via rudder and
// possibly throttle compensation for battery voltage sag.
PARAM_DEFINE_FLOAT(FW_HEADING_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_HEADING_LIM, 0.15f);
struct fw_pos_control_params {
float heading_p;
float heading_lim;
};
struct fw_pos_control_param_handles {
param_t heading_p;
param_t heading_lim;
};
/**
* Initialize all parameter handles and values
*
*/
static int att_parameters_init(struct fw_att_control_param_handles *h);
/**
* Update all parameters
*
*/
static int att_parameters_update(const struct fw_att_control_param_handles *h, struct fw_att_control_params *p);
/**
* Initialize all parameter handles and values
*
*/
static int pos_parameters_init(struct fw_pos_control_param_handles *h);
/**
* Update all parameters
*
*/
static int pos_parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p);
/**
* The fixed wing control main thread.
*
* The main loop executes continously and calculates the control
* response.
*
* @param argc number of arguments
* @param argv argument array
*
* @return 0
*
*/
int fixedwing_control_thread_main(int argc, char *argv[])
{
/* read arguments */
bool verbose = false;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
}
/* welcome user */
printf("[fixedwing control] started\n");
/* output structs */
struct actuator_controls_s actuators;
struct vehicle_attitude_setpoint_s att_sp;
memset(&att_sp, 0, sizeof(att_sp));
/* publish actuator controls */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++)
actuators.control[i] = 0.0f;
orb_advert_t actuator_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &actuators);
orb_advert_t att_sp_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &att_sp);
/* Subscribe to global position, attitude and rc */
/* declare and safely initialize all structs */
struct vehicle_status_s state;
memset(&state, 0, sizeof(state));
struct vehicle_attitude_s att;
memset(&att_sp, 0, sizeof(att_sp));
struct manual_control_setpoint_s manual;
memset(&manual, 0, sizeof(manual));
/* subscribe to attitude, motor setpoints and system state */
struct vehicle_global_position_s global_pos;
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
struct vehicle_global_position_setpoint_s global_setpoint;
int global_setpoint_sub = orb_subscribe(ORB_ID(vehicle_global_position_setpoint));
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int att_setpoint_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
int state_sub = orb_subscribe(ORB_ID(vehicle_status));
int manual_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
/* Mainloop setup */
unsigned int loopcounter = 0;
uint64_t last_run = 0;
uint64_t last_run_pos = 0;
bool global_sp_updated_set_once = false;
struct fw_att_control_params p;
struct fw_att_control_param_handles h;
struct fw_pos_control_params ppos;
struct fw_pos_control_param_handles hpos;
/* initialize the pid controllers */
att_parameters_init(&h);
att_parameters_update(&h, &p);
pos_parameters_init(&hpos);
pos_parameters_update(&hpos, &ppos);
// TO_DO Fix output limit functionallity of PID controller or add that function elsewhere
PID_t roll_rate_controller;
pid_init(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0.0f, p.rollrate_awu,
p.rollrate_lim,PID_MODE_DERIVATIV_NONE);
PID_t roll_angle_controller;
pid_init(&roll_angle_controller, p.roll_p, 0.0f, 0.0f, 0.0f,
p.roll_lim,PID_MODE_DERIVATIV_NONE);
PID_t pitch_rate_controller;
pid_init(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0.0f, p.pitchrate_awu,
p.pitchrate_lim,PID_MODE_DERIVATIV_NONE);
PID_t pitch_angle_controller;
pid_init(&pitch_angle_controller, p.pitch_p, 0.0f, 0.0f, 0.0f,
p.pitch_lim,PID_MODE_DERIVATIV_NONE);
PID_t heading_controller;
pid_init(&heading_controller, ppos.heading_p, 0.0f, 0.0f, 0.0f,
100.0f,PID_MODE_DERIVATIV_SET); // Temporary arbitrarily large limit
// XXX remove in production
/* advertise debug value */
struct debug_key_value_s dbg = { .key = "", .value = 0.0f };
orb_advert_t pub_dbg = orb_advertise(ORB_ID(debug_key_value), &dbg);
// This is the top of the main loop
while(!thread_should_exit) {
struct pollfd fds[1] = {
{ .fd = att_sub, .events = POLLIN },
};
int ret = poll(fds, 1, 1000);
if (ret < 0) {
/* XXX this is seriously bad - should be an emergency */
} else if (ret == 0) {
/* XXX this means no sensor data - should be critical or emergency */
printf("[fixedwing control] WARNING: Not getting attitude - estimator running?\n");
} else {
// FIXME SUBSCRIBE
if (loopcounter % 100 == 0) {
att_parameters_update(&h, &p);
pos_parameters_update(&hpos, &ppos);
pid_set_parameters(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0.0f,
p.rollrate_awu, p.rollrate_lim);
pid_set_parameters(&roll_angle_controller, p.roll_p, 0.0f, 0.0f,
0.0f, p.roll_lim);
pid_set_parameters(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0.0f,
p.pitchrate_awu, p.pitchrate_lim);
pid_set_parameters(&pitch_angle_controller, p.pitch_p, 0.0f, 0.0f,
0.0f, p.pitch_lim);
pid_set_parameters(&heading_controller, ppos.heading_p, 0.0f, 0.0f, 0.0f, 90.0f);
//printf("[fixedwing control debug] p: %8.4f, i: %8.4f, limit: %8.4f \n",
//p.rollrate_p, p.rollrate_i, p.rollrate_lim);
}
/* if position updated, run position control loop */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool global_sp_updated;
orb_check(global_setpoint_sub, &global_sp_updated);
if (global_sp_updated) {
global_sp_updated_set_once = true;
}
/* checking has to happen before the read, as the read clears the changed flag */
/* get a local copy of system state */
orb_copy(ORB_ID(vehicle_status), state_sub, &state);
/* get a local copy of manual setpoint */
orb_copy(ORB_ID(manual_control_setpoint), manual_sub, &manual);
/* get a local copy of attitude */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
/* get a local copy of attitude setpoint */
//orb_copy(ORB_ID(vehicle_attitude_setpoint), att_setpoint_sub, &att_sp);
// XXX update to switch between external attitude reference and the
// attitude calculated here
char name[10];
if (pos_updated) {
/* get position */
orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
if (global_sp_updated_set_once) {
orb_copy(ORB_ID(vehicle_global_position_setpoint), global_setpoint_sub, &global_setpoint);
/* calculate delta T */
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* calculate bearing error */
float target_bearing = get_bearing_to_next_waypoint(global_pos.lat / (double)1e7d, global_pos.lon / (double)1e7d,
global_setpoint.lat / (double)1e7d, global_setpoint.lon / (double)1e7d);
/* shift error to prevent wrapping issues */
float bearing_error = target_bearing - att.yaw;
if (loopcounter % 2 == 0) {
sprintf(name, "hdng err1");
memcpy(dbg.key, name, sizeof(name));
dbg.value = bearing_error;
orb_publish(ORB_ID(debug_key_value), pub_dbg, &dbg);
}
if (bearing_error < M_PI_F) {
bearing_error += 2.0f * M_PI_F;
}
if (bearing_error > M_PI_F) {
bearing_error -= 2.0f * M_PI_F;
}
if (loopcounter % 2 != 0) {
sprintf(name, "hdng err2");
memcpy(dbg.key, name, sizeof(name));
dbg.value = bearing_error;
orb_publish(ORB_ID(debug_key_value), pub_dbg, &dbg);
}
/* calculate roll setpoint, do this artificially around zero */
att_sp.roll_body = pid_calculate(&heading_controller, bearing_error,
0.0f, att.yawspeed, deltaT);
/* limit roll angle output */
if (att_sp.roll_body > ppos.heading_lim) {
att_sp.roll_body = ppos.heading_lim;
heading_controller.saturated = 1;
}
if (att_sp.roll_body < -ppos.heading_lim) {
att_sp.roll_body = -ppos.heading_lim;
heading_controller.saturated = 1;
}
att_sp.pitch_body = 0.0f;
att_sp.yaw_body = 0.0f;
} else {
/* no setpoint, maintain level flight */
att_sp.roll_body = 0.0f;
att_sp.pitch_body = 0.0f;
att_sp.yaw_body = 0.0f;
}
att_sp.thrust = 0.7f;
}
/* calculate delta T */
const float deltaTpos = (hrt_absolute_time() - last_run_pos) / 1000000.0f;
last_run_pos = hrt_absolute_time();
if (verbose && (loopcounter % 20 == 0)) {
printf("[fixedwing control] roll sp: %8.4f, \n", att_sp.roll_body);
}
// actuator control[0] is aileron (or elevon roll control)
// Commanded roll rate from P controller on roll angle
float roll_rate_command = pid_calculate(&roll_angle_controller, att_sp.roll_body,
att.roll, 0.0f, deltaTpos);
// actuator control from PI controller on roll rate
actuators.control[0] = pid_calculate(&roll_rate_controller, roll_rate_command,
att.rollspeed, 0.0f, deltaTpos);
// actuator control[1] is elevator (or elevon pitch control)
// Commanded pitch rate from P controller on pitch angle
float pitch_rate_command = pid_calculate(&pitch_angle_controller, att_sp.pitch_body,
att.pitch, 0.0f, deltaTpos);
// actuator control from PI controller on pitch rate
actuators.control[1] = pid_calculate(&pitch_rate_controller, pitch_rate_command,
att.pitchspeed, 0.0f, deltaTpos);
// actuator control[3] is throttle
actuators.control[3] = att_sp.thrust;
/* publish attitude setpoint (for MAVLink) */
orb_publish(ORB_ID(vehicle_attitude_setpoint), att_sp_pub, &att_sp);
/* publish actuator setpoints (for mixer) */
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
loopcounter++;
}
}
printf("[fixedwing_control] exiting.\n");
thread_running = false;
return 0;
}
static void
usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: fixedwing_control {start|stop|status}\n\n");
exit(1);
}
/**
* The deamon app only briefly exists to start
* the background job. The stack size assigned in the
* Makefile does only apply to this management task.
*
* The actual stack size should be set in the call
* to task_create().
*/
int fixedwing_control_main(int argc, char *argv[])
{
if (argc < 1)
usage("missing command");
if (!strcmp(argv[1], "start")) {
if (thread_running) {
printf("fixedwing_control already running\n");
/* this is not an error */
exit(0);
}
thread_should_exit = false;
deamon_task = task_spawn("fixedwing_control",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 20,
4096,
fixedwing_control_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
thread_running = true;
exit(0);
}
if (!strcmp(argv[1], "stop")) {
thread_should_exit = true;
exit(0);
}
if (!strcmp(argv[1], "status")) {
if (thread_running) {
printf("\tfixedwing_control is running\n");
} else {
printf("\tfixedwing_control not started\n");
}
exit(0);
}
usage("unrecognized command");
exit(1);
}
static int att_parameters_init(struct fw_att_control_param_handles *h)
{
/* PID parameters */
h->rollrate_p = param_find("FW_ROLLRATE_P");
h->rollrate_i = param_find("FW_ROLLRATE_I");
h->rollrate_awu = param_find("FW_ROLLRATE_AWU");
h->rollrate_lim = param_find("FW_ROLLRATE_LIM");
h->roll_p = param_find("FW_ROLL_P");
h->roll_lim = param_find("FW_ROLL_LIM");
h->pitchrate_p = param_find("FW_PITCHRATE_P");
h->pitchrate_i = param_find("FW_PITCHRATE_I");
h->pitchrate_awu = param_find("FW_PITCHRATE_AWU");
h->pitchrate_lim = param_find("FW_PITCHRATE_LIM");
h->pitch_p = param_find("FW_PITCH_P");
h->pitch_lim = param_find("FW_PITCH_LIM");
return OK;
}
static int att_parameters_update(const struct fw_att_control_param_handles *h, struct fw_att_control_params *p)
{
param_get(h->rollrate_p, &(p->rollrate_p));
param_get(h->rollrate_i, &(p->rollrate_i));
param_get(h->rollrate_awu, &(p->rollrate_awu));
param_get(h->rollrate_lim, &(p->rollrate_lim));
param_get(h->roll_p, &(p->roll_p));
param_get(h->roll_lim, &(p->roll_lim));
param_get(h->pitchrate_p, &(p->pitchrate_p));
param_get(h->pitchrate_i, &(p->pitchrate_i));
param_get(h->pitchrate_awu, &(p->pitchrate_awu));
param_get(h->pitchrate_lim, &(p->pitchrate_lim));
param_get(h->pitch_p, &(p->pitch_p));
param_get(h->pitch_lim, &(p->pitch_lim));
return OK;
}
static int pos_parameters_init(struct fw_pos_control_param_handles *h)
{
/* PID parameters */
h->heading_p = param_find("FW_HEADING_P");
h->heading_lim = param_find("FW_HEADING_LIM");
return OK;
}
static int pos_parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p)
{
param_get(h->heading_p, &(p->heading_p));
param_get(h->heading_lim, &(p->heading_lim));
return OK;
}

378
apps/fixedwing_pos_control/fixedwing_pos_control_main.c
View File

@ -57,24 +57,31 @@
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/parameter_update.h>
#include <systemlib/param/param.h>
#include <systemlib/pid/pid.h>
#include <systemlib/geo/geo.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
/*
* Controller parameters, accessible via MAVLink
*
*/
PARAM_DEFINE_FLOAT(FW_HEADING_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_HEAD_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_HEADR_I, 0.1f);
PARAM_DEFINE_FLOAT(FW_HEADR_LIM, 1.5f); //TODO: think about reasonable value
PARAM_DEFINE_FLOAT(FW_XTRACK_P, 0.01745f); // Radians per meter off track
PARAM_DEFINE_FLOAT(FW_ALT_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_ROLL_LIM, 0.7f); // Roll angle limit in radians
PARAM_DEFINE_FLOAT(FW_PITCH_LIM, 0.35f); // Pitch angle limit in radians
PARAM_DEFINE_FLOAT(FW_HEADR_P, 0.1f);
PARAM_DEFINE_FLOAT(FW_PITCH_LIM, 0.35f); /**< Pitch angle limit in radians per second */
struct fw_pos_control_params {
float heading_p;
float headingr_p;
float headingr_i;
float headingr_lim;
float xtrack_p;
float altitude_p;
float roll_lim;
@ -83,11 +90,13 @@ struct fw_pos_control_params {
struct fw_pos_control_param_handles {
param_t heading_p;
param_t headingr_p;
param_t headingr_i;
param_t headingr_lim;
param_t xtrack_p;
param_t altitude_p;
param_t roll_lim;
param_t pitch_lim;
};
@ -99,8 +108,8 @@ struct planned_path_segments_s {
double end_lon;
float radius; // Radius of arc
float arc_start_bearing; // Bearing from center to start of arc
float arc_sweep; // Angle (radians) swept out by arc around center.
// Positive for clockwise, negative for counter-clockwise
float arc_sweep; // Angle (radians) swept out by arc around center.
// Positive for clockwise, negative for counter-clockwise
};
@ -136,12 +145,14 @@ static int deamon_task; /**< Handle of deamon task / thread */
static int parameters_init(struct fw_pos_control_param_handles *h)
{
/* PID parameters */
h->heading_p = param_find("FW_HEADING_P");
h->xtrack_p = param_find("FW_XTRACK_P");
h->altitude_p = param_find("FW_ALT_P");
h->roll_lim = param_find("FW_ROLL_LIM");
h->pitch_lim = param_find("FW_PITCH_LIM");
h->heading_p = param_find("FW_HEAD_P");
h->headingr_p = param_find("FW_HEADR_P");
h->headingr_i = param_find("FW_HEADR_I");
h->headingr_lim = param_find("FW_HEADR_LIM");
h->xtrack_p = param_find("FW_XTRACK_P");
h->altitude_p = param_find("FW_ALT_P");
h->roll_lim = param_find("FW_ROLL_LIM");
h->pitch_lim = param_find("FW_PITCH_LIM");
return OK;
}
@ -149,6 +160,9 @@ static int parameters_init(struct fw_pos_control_param_handles *h)
static int parameters_update(const struct fw_pos_control_param_handles *h, struct fw_pos_control_params *p)
{
param_get(h->heading_p, &(p->heading_p));
param_get(h->headingr_p, &(p->headingr_p));
param_get(h->headingr_i, &(p->headingr_i));
param_get(h->headingr_lim, &(p->headingr_lim));
param_get(h->xtrack_p, &(p->xtrack_p));
param_get(h->altitude_p, &(p->altitude_p));
param_get(h->roll_lim, &(p->roll_lim));
@ -162,172 +176,241 @@ static int parameters_update(const struct fw_pos_control_param_handles *h, struc
int fixedwing_pos_control_thread_main(int argc, char *argv[])
{
/* read arguments */
bool verbose = false;
bool verbose = false;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
}
/* welcome user */
printf("[fixedwing att_control] started\n");
/* welcome user */
printf("[fixedwing pos control] started\n");
/* declare and safely initialize all structs */
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct vehicle_global_position_s start_pos; // Temporary variable, replace with
memset(&start_pos, 0, sizeof(start_pos)); // previous waypoint when available
struct vehicle_global_position_setpoint_s global_setpoint;
memset(&global_setpoint, 0, sizeof(global_setpoint));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct crosstrack_error_s xtrack_err;
memset(&xtrack_err, 0, sizeof(xtrack_err));
/* output structs */
struct vehicle_attitude_setpoint_s attitude_setpoint;
memset(&attitude_setpoint, 0, sizeof(attitude_setpoint));
/* declare and safely initialize all structs */
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct vehicle_global_position_s start_pos; // Temporary variable, replace with
memset(&start_pos, 0, sizeof(start_pos)); // previous waypoint when available
struct vehicle_global_position_setpoint_s global_setpoint;
memset(&global_setpoint, 0, sizeof(global_setpoint));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct crosstrack_error_s xtrack_err;
memset(&xtrack_err, 0, sizeof(xtrack_err));
struct parameter_update_s param_update;
memset(&param_update, 0, sizeof(param_update));
/* publish attitude setpoint */
attitude_setpoint.roll_body = 0.0f;
attitude_setpoint.pitch_body = 0.0f;
attitude_setpoint.yaw_body = 0.0f;
orb_advert_t attitude_setpoint_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &attitude_setpoint);
/* output structs */
struct vehicle_attitude_setpoint_s attitude_setpoint;
memset(&attitude_setpoint, 0, sizeof(attitude_setpoint));
/* subscribe */
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
int global_setpoint_sub = orb_subscribe(ORB_ID(vehicle_global_position_setpoint));
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
/* publish attitude setpoint */
attitude_setpoint.roll_body = 0.0f;
attitude_setpoint.pitch_body = 0.0f;
attitude_setpoint.yaw_body = 0.0f;
attitude_setpoint.thrust = 0.0f;
orb_advert_t attitude_setpoint_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &attitude_setpoint);
/* Setup of loop */
struct pollfd fds = { .fd = att_sub, .events = POLLIN };
bool global_sp_updated_set_once = false;
/* subscribe */
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
int global_setpoint_sub = orb_subscribe(ORB_ID(vehicle_global_position_setpoint));
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int param_sub = orb_subscribe(ORB_ID(parameter_update));
float psi_track = 0.0f;
/* Setup of loop */
struct pollfd fds[2] = {
{ .fd = param_sub, .events = POLLIN },
{ .fd = att_sub, .events = POLLIN }
};
bool global_sp_updated_set_once = false;
while(!thread_should_exit)
{
/* wait for a sensor update, check for exit condition every 500 ms */
poll(&fds, 1, 500);
float psi_track = 0.0f;
static int counter = 0;
static bool initialized = false;
int counter = 0;
static struct fw_pos_control_params p;
static struct fw_pos_control_param_handles h;
struct fw_pos_control_params p;
struct fw_pos_control_param_handles h;
PID_t heading_controller;
PID_t altitude_controller;
PID_t heading_controller;
PID_t heading_rate_controller;
PID_t offtrack_controller;
PID_t altitude_controller;
if(!initialized)
{
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&heading_controller, p.heading_p, 0.0f, 0.0f, 0.0f,p.roll_lim,PID_MODE_DERIVATIV_NONE);
pid_init(&altitude_controller, p.altitude_p, 0.0f, 0.0f, 0.0f,p.pitch_lim,PID_MODE_DERIVATIV_NONE);
initialized = true;
}
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&heading_controller, p.heading_p, 0.0f, 0.0f, 0.0f, 10000.0f, PID_MODE_DERIVATIV_NONE); //arbitrary high limit
pid_init(&heading_rate_controller, p.headingr_p, p.headingr_i, 0.0f, 0.0f, p.roll_lim, PID_MODE_DERIVATIV_NONE);
pid_init(&altitude_controller, p.altitude_p, 0.0f, 0.0f, 0.0f, p.pitch_lim, PID_MODE_DERIVATIV_NONE);
pid_init(&offtrack_controller, p.xtrack_p, 0.0f, 0.0f, 0.0f , 60.0f * M_DEG_TO_RAD, PID_MODE_DERIVATIV_NONE); //TODO: remove hardcoded value
/* error and performance monitoring */
perf_counter_t fw_interval_perf = perf_alloc(PC_INTERVAL, "fixedwing_pos_control_interval");
perf_counter_t fw_err_perf = perf_alloc(PC_COUNT, "fixedwing_pos_control_err");
while (!thread_should_exit) {
/* wait for a sensor update, check for exit condition every 500 ms */
int ret = poll(fds, 2, 500);
if (ret < 0) {
/* poll error, count it in perf */
perf_count(fw_err_perf);
} else if (ret == 0) {
/* no return value, ignore */
} else {
/* only update parameters if they changed */
if (fds[0].revents & POLLIN) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), param_sub, &update);
/* load new parameters with lower rate */
if (counter % 100 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
pid_set_parameters(&heading_controller, p.heading_p, 0, 0, 0, p.roll_lim);
pid_set_parameters(&heading_controller, p.heading_p, 0, 0, 0, 10000.0f); //arbitrary high limit
pid_set_parameters(&heading_rate_controller, p.headingr_p, p.headingr_i, 0, 0, p.roll_lim);
pid_set_parameters(&altitude_controller, p.altitude_p, 0, 0, 0, p.pitch_lim);
pid_set_parameters(&offtrack_controller, p.xtrack_p, 0, 0, 0, 60.0f * M_DEG_TO_RAD); //TODO: remove hardcoded value
}
/* Check if there is a new position or setpoint */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool global_sp_updated;
orb_check(global_setpoint_sub, &global_sp_updated);
/* Load local copies */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
if(pos_updated)
orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
if (global_sp_updated)
orb_copy(ORB_ID(vehicle_global_position_setpoint), global_setpoint_sub, &global_setpoint);
if(global_sp_updated) {
start_pos = global_pos; //for now using the current position as the startpoint (= approx. last waypoint because the setpoint switch occurs at the waypoint)
global_sp_updated_set_once = true;
psi_track = get_bearing_to_next_waypoint((double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
printf("psi_track: %0.4f\n", (double)psi_track);
}
/* Control */
/* only run controller if attitude changed */
if (fds[1].revents & POLLIN) {
/* Simple Horizontal Control */
if(global_sp_updated_set_once)
{
// if (counter % 100 == 0)
// printf("lat_sp %d, ln_sp %d, lat: %d, lon: %d\n", global_setpoint.lat, global_setpoint.lon, global_pos.lat, global_pos.lon);
/* calculate crosstrack error */
// Only the case of a straight line track following handled so far
int distance_res = get_distance_to_line(&xtrack_err, (double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
(double)start_pos.lat / (double)1e7d, (double)start_pos.lon / (double)1e7d,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
static uint64_t last_run = 0;
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
if(!(distance_res != OK || xtrack_err.past_end)) {
/* check if there is a new position or setpoint */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool global_sp_updated;
orb_check(global_setpoint_sub, &global_sp_updated);
float delta_psi_c = -p.xtrack_p * xtrack_err.distance; //(-) because z axis points downwards
/* load local copies */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
if(delta_psi_c > 60.0f*M_DEG_TO_RAD_F)
delta_psi_c = 60.0f*M_DEG_TO_RAD_F;
if(delta_psi_c < -60.0f*M_DEG_TO_RAD_F)
delta_psi_c = -60.0f*M_DEG_TO_RAD_F;
float psi_c = psi_track + delta_psi_c;
float psi_e = psi_c - att.yaw;
/* shift error to prevent wrapping issues */
psi_e = _wrap_pi(psi_e);
/* calculate roll setpoint, do this artificially around zero */
attitude_setpoint.roll_body = pid_calculate(&heading_controller, psi_e, 0.0f, 0.0f, 0.0f);
// if (counter % 100 == 0)
// printf("xtrack_err.distance: %0.4f, delta_psi_c: %0.4f\n",xtrack_err.distance, delta_psi_c);
}
else {
if (counter % 100 == 0)
printf("distance_res: %d, past_end %d\n", distance_res, xtrack_err.past_end);
if (pos_updated) {
orb_copy(ORB_ID(vehicle_global_position), global_pos_sub, &global_pos);
}
if (global_sp_updated) {
orb_copy(ORB_ID(vehicle_global_position_setpoint), global_setpoint_sub, &global_setpoint);
start_pos = global_pos; //for now using the current position as the startpoint (= approx. last waypoint because the setpoint switch occurs at the waypoint)
global_sp_updated_set_once = true;
psi_track = get_bearing_to_next_waypoint((double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
printf("next wp direction: %0.4f\n", (double)psi_track);
}
/* Simple Horizontal Control */
if (global_sp_updated_set_once) {
// if (counter % 100 == 0)
// printf("lat_sp %d, ln_sp %d, lat: %d, lon: %d\n", global_setpoint.lat, global_setpoint.lon, global_pos.lat, global_pos.lon);
/* calculate crosstrack error */
// Only the case of a straight line track following handled so far
int distance_res = get_distance_to_line(&xtrack_err, (double)global_pos.lat / (double)1e7d, (double)global_pos.lon / (double)1e7d,
(double)start_pos.lat / (double)1e7d, (double)start_pos.lon / (double)1e7d,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
// XXX what is xtrack_err.past_end?
if (distance_res == OK /*&& !xtrack_err.past_end*/) {
float delta_psi_c = pid_calculate(&offtrack_controller, 0, xtrack_err.distance, 0.0f, 0.0f); //p.xtrack_p * xtrack_err.distance
float psi_c = psi_track + delta_psi_c;
float psi_e = psi_c - att.yaw;
/* wrap difference back onto -pi..pi range */
psi_e = _wrap_pi(psi_e);
if (verbose) {
printf("xtrack_err.distance %.4f ", (double)xtrack_err.distance);
printf("delta_psi_c %.4f ", (double)delta_psi_c);
printf("psi_c %.4f ", (double)psi_c);
printf("att.yaw %.4f ", (double)att.yaw);
printf("psi_e %.4f ", (double)psi_e);
}
/* calculate roll setpoint, do this artificially around zero */
float delta_psi_rate_c = pid_calculate(&heading_controller, psi_e, 0.0f, 0.0f, 0.0f);
float psi_rate_track = 0; //=V_gr/r_track , this will be needed for implementation of arc following
float psi_rate_c = delta_psi_rate_c + psi_rate_track;
/* limit turn rate */
if (psi_rate_c > p.headingr_lim) {
psi_rate_c = p.headingr_lim;
} else if (psi_rate_c < -p.headingr_lim) {
psi_rate_c = -p.headingr_lim;
}
float psi_rate_e = psi_rate_c - att.yawspeed;
// XXX sanity check: Assume 10 m/s stall speed and no stall condition
float ground_speed = sqrtf(global_pos.vx * global_pos.vx + global_pos.vy * global_pos.vy);
if (ground_speed < 10.0f) {
ground_speed = 10.0f;
}
float psi_rate_e_scaled = psi_rate_e * ground_speed / 9.81f; //* V_gr / g
attitude_setpoint.roll_body = pid_calculate(&heading_rate_controller, psi_rate_e_scaled, 0.0f, 0.0f, deltaT);
if (verbose) {
printf("psi_rate_c %.4f ", (double)psi_rate_c);
printf("psi_rate_e_scaled %.4f ", (double)psi_rate_e_scaled);
printf("rollbody %.4f\n", (double)attitude_setpoint.roll_body);
}
if (verbose && counter % 100 == 0)
printf("xtrack_err.distance: %0.4f, delta_psi_c: %0.4f\n", xtrack_err.distance, delta_psi_c);
} else {
if (verbose && counter % 100 == 0)
printf("distance_res: %d, past_end %d\n", distance_res, xtrack_err.past_end);
}
/* Very simple Altitude Control */
if (pos_updated) {
//TODO: take care of relative vs. ab. altitude
attitude_setpoint.pitch_body = pid_calculate(&altitude_controller, global_setpoint.altitude, global_pos.alt, 0.0f, 0.0f);
}
// XXX need speed control
attitude_setpoint.thrust = 0.7f;
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_attitude_setpoint), attitude_setpoint_pub, &attitude_setpoint);
/* measure in what intervals the controller runs */
perf_count(fw_interval_perf);
counter++;
} else {
// XXX no setpoint, decent default needed (loiter?)
}
}
/* Very simple Altitude Control */
if(global_sp_updated_set_once && pos_updated)
{
//TODO: take care of relative vs. ab. altitude
attitude_setpoint.pitch_body = pid_calculate(&altitude_controller, global_setpoint.altitude, global_pos.alt, 0.0f, 0.0f);
}
/*Publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_attitude_setpoint), attitude_setpoint_pub, &attitude_setpoint);
counter++;
}
}
printf("[fixedwing_pos_control] exiting.\n");
thread_running = false;
printf("[fixedwing_pos_control] exiting.\n");
thread_running = false;
close(attitude_setpoint_pub);
close(attitude_setpoint_pub);
fflush(stdout);
exit(0);
fflush(stdout);
exit(0);
return 0;
return 0;
}
@ -338,6 +421,7 @@ usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: fixedwing_pos_control {start|stop|status}\n\n");
exit(1);
}
@ -367,7 +451,7 @@ int fixedwing_pos_control_main(int argc, char *argv[])
deamon_task = task_spawn("fixedwing_pos_control",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 20,
4096,
2048,
fixedwing_pos_control_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
thread_running = true;
@ -382,9 +466,11 @@ int fixedwing_pos_control_main(int argc, char *argv[])
if (!strcmp(argv[1], "status")) {
if (thread_running) {
printf("\tfixedwing_pos_control is running\n");
} else {
printf("\tfixedwing_pos_control not started\n");
}
exit(0);
}

148
apps/mavlink/mavlink.c
View File

@ -156,12 +156,15 @@ set_hil_on_off(bool hil_enabled)
if (baudrate < 19200) {
/* 10 Hz */
hil_rate_interval = 100;
} else if (baudrate < 38400) {
/* 10 Hz */
hil_rate_interval = 100;
} else if (baudrate < 115200) {
/* 20 Hz */
hil_rate_interval = 50;
} else {
/* 200 Hz */
hil_rate_interval = 5;
@ -189,17 +192,38 @@ get_mavlink_mode_and_state(uint8_t *mavlink_state, uint8_t *mavlink_mode)
*mavlink_mode = 0;
/* set mode flags independent of system state */
/* HIL */
if (v_status.flag_hil_enabled) {
*mavlink_mode |= MAV_MODE_FLAG_HIL_ENABLED;
}
/* manual input */
if (v_status.flag_control_manual_enabled) {
*mavlink_mode |= MAV_MODE_FLAG_MANUAL_INPUT_ENABLED;
}
if (v_status.flag_hil_enabled) {
*mavlink_mode |= MAV_MODE_FLAG_HIL_ENABLED;
/* attitude or rate control */
if (v_status.flag_control_attitude_enabled ||
v_status.flag_control_rates_enabled) {
*mavlink_mode |= MAV_MODE_FLAG_STABILIZE_ENABLED;
}
/* vector control */
if (v_status.flag_control_velocity_enabled ||
v_status.flag_control_position_enabled) {
*mavlink_mode |= MAV_MODE_FLAG_GUIDED_ENABLED;
}
/* autonomous mode */
if (v_status.state_machine == SYSTEM_STATE_AUTO) {
*mavlink_mode |= MAV_MODE_FLAG_AUTO_ENABLED;
}
/* set arming state */
if (armed.armed) {
*mavlink_mode |= MAV_MODE_FLAG_SAFETY_ARMED;
} else {
*mavlink_mode &= ~MAV_MODE_FLAG_SAFETY_ARMED;
}
@ -210,9 +234,11 @@ get_mavlink_mode_and_state(uint8_t *mavlink_state, uint8_t *mavlink_mode)
v_status.flag_preflight_mag_calibration ||
v_status.flag_preflight_accel_calibration) {
*mavlink_state = MAV_STATE_CALIBRATING;
} else {
*mavlink_state = MAV_STATE_UNINIT;
}
break;
case SYSTEM_STATE_STANDBY:
@ -225,17 +251,14 @@ get_mavlink_mode_and_state(uint8_t *mavlink_state, uint8_t *mavlink_mode)
case SYSTEM_STATE_MANUAL:
*mavlink_state = MAV_STATE_ACTIVE;
*mavlink_mode |= MAV_MODE_FLAG_MANUAL_INPUT_ENABLED;
break;
case SYSTEM_STATE_STABILIZED:
*mavlink_state = MAV_STATE_ACTIVE;
*mavlink_mode |= MAV_MODE_FLAG_STABILIZE_ENABLED;
break;
case SYSTEM_STATE_AUTO:
*mavlink_state = MAV_STATE_ACTIVE;
*mavlink_mode |= MAV_MODE_FLAG_GUIDED_ENABLED;
break;
case SYSTEM_STATE_MISSION_ABORT:
@ -267,41 +290,48 @@ int set_mavlink_interval_limit(struct mavlink_subscriptions *subs, int mavlink_m
int ret = OK;
switch (mavlink_msg_id) {
case MAVLINK_MSG_ID_SCALED_IMU:
/* sensor sub triggers scaled IMU */
orb_set_interval(subs->sensor_sub, min_interval);
break;
case MAVLINK_MSG_ID_HIGHRES_IMU:
/* sensor sub triggers highres IMU */
orb_set_interval(subs->sensor_sub, min_interval);
break;
case MAVLINK_MSG_ID_RAW_IMU:
/* sensor sub triggers RAW IMU */
orb_set_interval(subs->sensor_sub, min_interval);
break;
case MAVLINK_MSG_ID_ATTITUDE:
/* attitude sub triggers attitude */
orb_set_interval(subs->att_sub, min_interval);
break;
case MAVLINK_MSG_ID_SERVO_OUTPUT_RAW:
/* actuator_outputs triggers this message */
orb_set_interval(subs->act_0_sub, min_interval);
orb_set_interval(subs->act_1_sub, min_interval);
orb_set_interval(subs->act_2_sub, min_interval);
orb_set_interval(subs->act_3_sub, min_interval);
orb_set_interval(subs->actuators_sub, min_interval);
break;
case MAVLINK_MSG_ID_MANUAL_CONTROL:
/* manual_control_setpoint triggers this message */
orb_set_interval(subs->man_control_sp_sub, min_interval);
break;
case MAVLINK_MSG_ID_NAMED_VALUE_FLOAT:
orb_set_interval(subs->debug_key_value, min_interval);
break;
default:
/* not found */
ret = ERROR;
break;
case MAVLINK_MSG_ID_SCALED_IMU:
/* sensor sub triggers scaled IMU */
orb_set_interval(subs->sensor_sub, min_interval);
break;
case MAVLINK_MSG_ID_HIGHRES_IMU:
/* sensor sub triggers highres IMU */
orb_set_interval(subs->sensor_sub, min_interval);
break;
case MAVLINK_MSG_ID_RAW_IMU:
/* sensor sub triggers RAW IMU */
orb_set_interval(subs->sensor_sub, min_interval);
break;
case MAVLINK_MSG_ID_ATTITUDE:
/* attitude sub triggers attitude */
orb_set_interval(subs->att_sub, min_interval);
break;
case MAVLINK_MSG_ID_SERVO_OUTPUT_RAW:
/* actuator_outputs triggers this message */
orb_set_interval(subs->act_0_sub, min_interval);
orb_set_interval(subs->act_1_sub, min_interval);
orb_set_interval(subs->act_2_sub, min_interval);
orb_set_interval(subs->act_3_sub, min_interval);
orb_set_interval(subs->actuators_sub, min_interval);
break;
case MAVLINK_MSG_ID_MANUAL_CONTROL:
/* manual_control_setpoint triggers this message */
orb_set_interval(subs->man_control_sp_sub, min_interval);
break;
case MAVLINK_MSG_ID_NAMED_VALUE_FLOAT:
orb_set_interval(subs->debug_key_value, min_interval);
break;
default:
/* not found */
ret = ERROR;
break;
}
return ret;
@ -443,7 +473,7 @@ int mavlink_open_uart(int baud, const char *uart_name, struct termios *uart_conf
return uart;
}
void
void
mavlink_send_uart_bytes(mavlink_channel_t channel, uint8_t *ch, int length)
{
write(uart, ch, (size_t)(sizeof(uint8_t) * length));
@ -452,7 +482,7 @@ mavlink_send_uart_bytes(mavlink_channel_t channel, uint8_t *ch, int length)
/*
* Internal function to give access to the channel status for each channel
*/
mavlink_status_t* mavlink_get_channel_status(uint8_t channel)
mavlink_status_t *mavlink_get_channel_status(uint8_t channel)
{
static mavlink_status_t m_mavlink_status[MAVLINK_COMM_NUM_BUFFERS];
return &m_mavlink_status[channel];
@ -461,7 +491,7 @@ mavlink_status_t* mavlink_get_channel_status(uint8_t channel)
/*
* Internal function to give access to the channel buffer for each channel
*/
mavlink_message_t* mavlink_get_channel_buffer(uint8_t channel)
mavlink_message_t *mavlink_get_channel_buffer(uint8_t channel)
{
static mavlink_message_t m_mavlink_buffer[MAVLINK_COMM_NUM_BUFFERS];
return &m_mavlink_buffer[channel];
@ -470,31 +500,35 @@ mavlink_message_t* mavlink_get_channel_buffer(uint8_t channel)
void mavlink_update_system(void)
{
static bool initialized = false;
param_t param_system_id;
param_t param_component_id;
param_t param_system_type;
static param_t param_system_id;
static param_t param_component_id;
static param_t param_system_type;
if (!initialized) {
param_system_id = param_find("MAV_SYS_ID");
param_component_id = param_find("MAV_COMP_ID");
param_system_type = param_find("MAV_TYPE");
initialized = true;
}
/* update system and component id */
int32_t system_id;
param_get(param_system_id, &system_id);
if (system_id > 0 && system_id < 255) {
mavlink_system.sysid = system_id;
}
int32_t component_id;
param_get(param_component_id, &component_id);
if (component_id > 0 && component_id < 255) {
mavlink_system.compid = component_id;
}
int32_t system_type;
param_get(param_system_type, &system_type);
if (system_type >= 0 && system_type < MAV_TYPE_ENUM_END) {
mavlink_system.type = system_type;
}
@ -520,8 +554,10 @@ int mavlink_thread_main(int argc, char *argv[])
switch (ch) {
case 'b':
baudrate = strtoul(optarg, NULL, 10);
if (baudrate == 0)
errx(1, "invalid baud rate '%s'", optarg);
break;
case 'd':
@ -542,6 +578,7 @@ int mavlink_thread_main(int argc, char *argv[])
}
struct termios uart_config_original;
bool usb_uart;
/* print welcome text */
@ -555,6 +592,7 @@ int mavlink_thread_main(int argc, char *argv[])
/* default values for arguments */
uart = mavlink_open_uart(baudrate, device_name, &uart_config_original, &usb_uart);
if (uart < 0)
err(1, "could not open %s", device_name);
@ -585,6 +623,7 @@ int mavlink_thread_main(int argc, char *argv[])
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_SERVO_OUTPUT_RAW, 50);
/* 2 Hz */
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_MANUAL_CONTROL, 100);
} else if (baudrate >= 115200) {
/* 20 Hz / 50 ms */
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_HIGHRES_IMU, 50);
@ -595,6 +634,7 @@ int mavlink_thread_main(int argc, char *argv[])
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_SERVO_OUTPUT_RAW, 200);
/* 2 Hz */
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_MANUAL_CONTROL, 500);
} else if (baudrate >= 57600) {
/* 10 Hz / 100 ms */
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_RAW_IMU, 300);
@ -607,6 +647,7 @@ int mavlink_thread_main(int argc, char *argv[])
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_SERVO_OUTPUT_RAW, 500);
/* 2 Hz */
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_MANUAL_CONTROL, 500);
} else {
/* very low baud rate, limit to 1 Hz / 1000 ms */
set_mavlink_interval_limit(&mavlink_subs, MAVLINK_MSG_ID_RAW_IMU, 1000);
@ -659,6 +700,7 @@ int mavlink_thread_main(int argc, char *argv[])
v_status.errors_count4);
lowspeed_counter = 0;
}
lowspeed_counter++;
/* sleep quarter the time */
@ -675,6 +717,7 @@ int mavlink_thread_main(int argc, char *argv[])
/* sleep quarter the time */
usleep(25000);
if (baudrate > 57600) {
mavlink_pm_queued_send();
}
@ -686,6 +729,7 @@ int mavlink_thread_main(int argc, char *argv[])
if (!mavlink_logbuffer_is_empty(&lb)) {
struct mavlink_logmessage msg;
int lb_ret = mavlink_logbuffer_read(&lb, &msg);
if (lb_ret == OK) {
mavlink_missionlib_send_gcs_string(msg.text);
}
@ -712,8 +756,8 @@ static void
usage()
{
fprintf(stderr, "usage: mavlink start [-d <devicename>] [-b <baud rate>]\n"
" mavlink stop\n"
" mavlink status\n");
" mavlink stop\n"
" mavlink status\n");
exit(1);
}
@ -737,15 +781,18 @@ int mavlink_main(int argc, char *argv[])
SCHED_PRIORITY_DEFAULT,
2048,
mavlink_thread_main,
(const char**)argv);
(const char **)argv);
exit(0);
}
if (!strcmp(argv[1], "stop")) {
thread_should_exit = true;
while (thread_running) {
usleep(200000);
printf(".");
}
warnx("terminated.");
exit(0);
}
@ -753,6 +800,7 @@ int mavlink_main(int argc, char *argv[])
if (!strcmp(argv[1], "status")) {
if (thread_running) {
errx(0, "running");
} else {
errx(1, "not running");
}

4
apps/mavlink/mavlink_bridge_header.h
View File

@ -75,7 +75,7 @@ extern mavlink_system_t mavlink_system;
*/
extern void mavlink_send_uart_bytes(mavlink_channel_t chan, uint8_t *ch, int length);
mavlink_status_t* mavlink_get_channel_status(uint8_t chan);
mavlink_message_t* mavlink_get_channel_buffer(uint8_t chan);
mavlink_status_t *mavlink_get_channel_status(uint8_t chan);
mavlink_message_t *mavlink_get_channel_buffer(uint8_t chan);
#endif /* MAVLINK_BRIDGE_HEADER_H */

2
apps/mavlink/mavlink_hil.h
View File

@ -50,7 +50,7 @@ extern orb_advert_t pub_hil_attitude;
* Enable / disable Hardware in the Loop simulation mode.
*
* @param hil_enabled The new HIL enable/disable state.
* @return OK if the HIL state changed, ERROR if the
* @return OK if the HIL state changed, ERROR if the
* requested change could not be made or was
* redundant.
*/

68
apps/mavlink/mavlink_log.c
View File

@ -43,39 +43,47 @@
#include <stdlib.h>
#include "mavlink_log.h"
void mavlink_logbuffer_init(struct mavlink_logbuffer *lb, int size) {
lb->size = size;
lb->start = 0;
lb->count = 0;
lb->elems = (struct mavlink_logmessage *)calloc(lb->size, sizeof(struct mavlink_logmessage));
void mavlink_logbuffer_init(struct mavlink_logbuffer *lb, int size)
{
lb->size = size;
lb->start = 0;
lb->count = 0;
lb->elems = (struct mavlink_logmessage *)calloc(lb->size, sizeof(struct mavlink_logmessage));
}
int mavlink_logbuffer_is_full(struct mavlink_logbuffer *lb) {
int mavlink_logbuffer_is_full(struct mavlink_logbuffer *lb)
{
return lb->count == (int)lb->size;
}
int mavlink_logbuffer_is_empty(struct mavlink_logbuffer *lb) {
return lb->count == 0;
int mavlink_logbuffer_is_empty(struct mavlink_logbuffer *lb)
{
return lb->count == 0;
}
void mavlink_logbuffer_write(struct mavlink_logbuffer *lb, const struct mavlink_logmessage *elem) {
int end = (lb->start + lb->count) % lb->size;
memcpy(&(lb->elems[end]), elem, sizeof(struct mavlink_logmessage));
if (mavlink_logbuffer_is_full(lb)) {
lb->start = (lb->start + 1) % lb->size; /* full, overwrite */
} else {
++lb->count;
}
void mavlink_logbuffer_write(struct mavlink_logbuffer *lb, const struct mavlink_logmessage *elem)
{
int end = (lb->start + lb->count) % lb->size;
memcpy(&(lb->elems[end]), elem, sizeof(struct mavlink_logmessage));
if (mavlink_logbuffer_is_full(lb)) {
lb->start = (lb->start + 1) % lb->size; /* full, overwrite */
} else {
++lb->count;
}
}
int mavlink_logbuffer_read(struct mavlink_logbuffer *lb, struct mavlink_logmessage *elem) {
if (!mavlink_logbuffer_is_empty(lb)) {
memcpy(elem, &(lb->elems[lb->start]), sizeof(struct mavlink_logmessage));
lb->start = (lb->start + 1) % lb->size;
--lb->count;
return 0;
} else {
return 1;
}
int mavlink_logbuffer_read(struct mavlink_logbuffer *lb, struct mavlink_logmessage *elem)
{
if (!mavlink_logbuffer_is_empty(lb)) {
memcpy(elem, &(lb->elems[lb->start]), sizeof(struct mavlink_logmessage));
lb->start = (lb->start + 1) % lb->size;
--lb->count;
return 0;
} else {
return 1;
}
}

22
apps/mavlink/mavlink_log.h
View File

@ -82,26 +82,26 @@
#define mavlink_log_info(_fd, _text) ioctl(_fd, MAVLINK_IOC_SEND_TEXT_INFO, (unsigned long)_text);
struct mavlink_logmessage {
char text[51];
unsigned char severity;
char text[51];
unsigned char severity;
};
struct mavlink_logbuffer {
unsigned int start;
// unsigned int end;
unsigned int size;
int count;
struct mavlink_logmessage *elems;
unsigned int start;
// unsigned int end;
unsigned int size;
int count;
struct mavlink_logmessage *elems;
};
void mavlink_logbuffer_init(struct mavlink_logbuffer *lb, int size);
int mavlink_logbuffer_is_full(struct mavlink_logbuffer *lb);
int mavlink_logbuffer_is_empty(struct mavlink_logbuffer *lb);
void mavlink_logbuffer_write(struct mavlink_logbuffer *lb, const struct mavlink_logmessage *elem);
int mavlink_logbuffer_read(struct mavlink_logbuffer *lb, struct mavlink_logmessage *elem);
#endif

53
apps/mavlink/mavlink_parameters.c
View File

@ -75,7 +75,7 @@ void mavlink_pm_callback(void *arg, param_t param);
void mavlink_pm_callback(void *arg, param_t param)
{
mavlink_pm_send_param(param);
usleep(*(unsigned int*)arg);
usleep(*(unsigned int *)arg);
}
void mavlink_pm_send_all_params(unsigned int delay)
@ -90,6 +90,7 @@ int mavlink_pm_queued_send()
mavlink_pm_send_param(param_for_index(mavlink_param_queue_index));
mavlink_param_queue_index++;
return 0;
} else {
return 1;
}
@ -105,7 +106,7 @@ int mavlink_pm_send_param_for_index(uint16_t index)
return mavlink_pm_send_param(param_for_index(index));
}
int mavlink_pm_send_param_for_name(const char* name)
int mavlink_pm_send_param_for_name(const char *name)
{
return mavlink_pm_send_param(param_find(name));
}
@ -123,16 +124,19 @@ int mavlink_pm_send_param(param_t param)
param_type_t type = param_type(param);
/* copy parameter name */
strncpy((char *)name_buf, param_name(param), MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN);
/*
* Map onboard parameter type to MAVLink type,
* endianess matches (both little endian)
*/
uint8_t mavlink_type;
if (type == PARAM_TYPE_INT32) {
mavlink_type = MAVLINK_TYPE_INT32_T;
} else if (type == PARAM_TYPE_FLOAT) {
mavlink_type = MAVLINK_TYPE_FLOAT;
} else {
mavlink_type = MAVLINK_TYPE_FLOAT;
}
@ -143,7 +147,10 @@ int mavlink_pm_send_param(param_t param)
*/
int ret;
if ((ret = param_get(param, &val_buf)) != OK) return ret;
if ((ret = param_get(param, &val_buf)) != OK) {
return ret;
}
mavlink_msg_param_value_pack_chan(mavlink_system.sysid,
mavlink_system.compid,
@ -161,13 +168,13 @@ int mavlink_pm_send_param(param_t param)
void mavlink_pm_message_handler(const mavlink_channel_t chan, const mavlink_message_t *msg)
{
switch (msg->msgid) {
case MAVLINK_MSG_ID_PARAM_REQUEST_LIST: {
case MAVLINK_MSG_ID_PARAM_REQUEST_LIST: {
/* Start sending parameters */
mavlink_pm_start_queued_send();
mavlink_missionlib_send_gcs_string("[mavlink pm] sending list");
} break;
case MAVLINK_MSG_ID_PARAM_SET: {
case MAVLINK_MSG_ID_PARAM_SET: {
/* Handle parameter setting */
@ -177,7 +184,7 @@ void mavlink_pm_message_handler(const mavlink_channel_t chan, const mavlink_mess
if (mavlink_param_set.target_system == mavlink_system.sysid && ((mavlink_param_set.target_component == mavlink_system.compid) || (mavlink_param_set.target_component == MAV_COMP_ID_ALL))) {
/* local name buffer to enforce null-terminated string */
char name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN+1];
char name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN + 1];
strncpy(name, mavlink_param_set.param_id, MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN);
/* enforce null termination */
name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN] = '\0';
@ -188,6 +195,7 @@ void mavlink_pm_message_handler(const mavlink_channel_t chan, const mavlink_mess
char buf[MAVLINK_MSG_STATUSTEXT_FIELD_TEXT_LEN];
sprintf(buf, "[mavlink pm] unknown: %s", name);
mavlink_missionlib_send_gcs_string(buf);
} else {
/* set and send parameter */
param_set(param, &(mavlink_param_set.param_value));
@ -197,25 +205,26 @@ void mavlink_pm_message_handler(const mavlink_channel_t chan, const mavlink_mess
}
} break;
case MAVLINK_MSG_ID_PARAM_REQUEST_READ: {
case MAVLINK_MSG_ID_PARAM_REQUEST_READ: {
mavlink_param_request_read_t mavlink_param_request_read;
mavlink_msg_param_request_read_decode(msg, &mavlink_param_request_read);
if (mavlink_param_request_read.target_system == mavlink_system.sysid && ((mavlink_param_request_read.target_component == mavlink_system.compid) || (mavlink_param_request_read.target_component == MAV_COMP_ID_ALL))) {
/* when no index is given, loop through string ids and compare them */
if (mavlink_param_request_read.param_index == -1) {
/* local name buffer to enforce null-terminated string */
char name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN+1];
strncpy(name, mavlink_param_request_read.param_id, MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN);
/* enforce null termination */
name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN] = '\0';
/* attempt to find parameter and send it */
mavlink_pm_send_param_for_name(name);
} else {
/* when index is >= 0, send this parameter again */
mavlink_pm_send_param_for_index(mavlink_param_request_read.param_index);
}
if (mavlink_param_request_read.target_system == mavlink_system.sysid && ((mavlink_param_request_read.target_component == mavlink_system.compid) || (mavlink_param_request_read.target_component == MAV_COMP_ID_ALL))) {
/* when no index is given, loop through string ids and compare them */
if (mavlink_param_request_read.param_index == -1) {
/* local name buffer to enforce null-terminated string */
char name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN + 1];
strncpy(name, mavlink_param_request_read.param_id, MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN);
/* enforce null termination */
name[MAVLINK_MSG_PARAM_VALUE_FIELD_PARAM_ID_LEN] = '\0';
/* attempt to find parameter and send it */
mavlink_pm_send_param_for_name(name);
} else {
/* when index is >= 0, send this parameter again */
mavlink_pm_send_param_for_index(mavlink_param_request_read.param_index);
}
}
} break;
}

6
apps/mavlink/mavlink_parameters.h
View File

@ -48,7 +48,7 @@
#include <systemlib/param/param.h>
/**
* Handle parameter related messages.
* Handle parameter related messages.
*/
void mavlink_pm_message_handler(const mavlink_channel_t chan, const mavlink_message_t *msg);
@ -84,14 +84,14 @@ int mavlink_pm_send_param_for_index(uint16_t index);
* @param name The index of the parameter to send.
* @return zero on success, nonzero else.
*/
int mavlink_pm_send_param_for_name(const char* name);
int mavlink_pm_send_param_for_name(const char *name);
/**
* Send a queue of parameters, one parameter per function call.
*
* @return zero on success, nonzero on failure
*/
int mavlink_pm_queued_send(void);
int mavlink_pm_queued_send(void);
/**
* Start sending the parameter queue.

86
apps/mavlink/mavlink_receiver.c
View File

@ -106,7 +106,7 @@ handle_message(mavlink_message_t *msg)
mavlink_msg_command_long_decode(msg, &cmd_mavlink);
if (cmd_mavlink.target_system == mavlink_system.sysid && ((cmd_mavlink.target_component == mavlink_system.compid)
|| (cmd_mavlink.target_component == MAV_COMP_ID_ALL))) {
|| (cmd_mavlink.target_component == MAV_COMP_ID_ALL))) {
//check for MAVLINK terminate command
if (cmd_mavlink.command == MAV_CMD_PREFLIGHT_REBOOT_SHUTDOWN && ((int)cmd_mavlink.param1) == 3) {
/* This is the link shutdown command, terminate mavlink */
@ -138,6 +138,7 @@ handle_message(mavlink_message_t *msg)
if (cmd_pub <= 0) {
cmd_pub = orb_advertise(ORB_ID(vehicle_command), &vcmd);
}
/* publish */
orb_publish(ORB_ID(vehicle_command), cmd_pub, &vcmd);
}
@ -162,6 +163,7 @@ handle_message(mavlink_message_t *msg)
/* check if topic is advertised */
if (flow_pub <= 0) {
flow_pub = orb_advertise(ORB_ID(optical_flow), &f);
} else {
/* publish */
orb_publish(ORB_ID(optical_flow), flow_pub, &f);
@ -191,6 +193,7 @@ handle_message(mavlink_message_t *msg)
/* check if topic is advertised */
if (cmd_pub <= 0) {
cmd_pub = orb_advertise(ORB_ID(vehicle_command), &vcmd);
} else {
/* create command */
orb_publish(ORB_ID(vehicle_command), cmd_pub, &vcmd);
@ -214,6 +217,7 @@ handle_message(mavlink_message_t *msg)
if (vicon_position_pub <= 0) {
vicon_position_pub = orb_advertise(ORB_ID(vehicle_vicon_position), &vicon_position);
} else {
orb_publish(ORB_ID(vehicle_vicon_position), vicon_position_pub, &vicon_position);
}
@ -230,7 +234,7 @@ handle_message(mavlink_message_t *msg)
/* switch to a receiving link mode */
gcs_link = false;
/*
/*
* rate control mode - defined by MAVLink
*/
@ -238,33 +242,37 @@ handle_message(mavlink_message_t *msg)
bool ml_armed = false;
switch (quad_motors_setpoint.mode) {
case 0:
ml_armed = false;
break;
case 1:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_RATES;
ml_armed = true;
case 0:
ml_armed = false;
break;
break;
case 2:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_ATTITUDE;
ml_armed = true;
case 1:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_RATES;
ml_armed = true;
break;
case 3:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_VELOCITY;
break;
case 4:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_POSITION;
break;
break;
case 2:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_ATTITUDE;
ml_armed = true;
break;
case 3:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_VELOCITY;
break;
case 4:
ml_mode = OFFBOARD_CONTROL_MODE_DIRECT_POSITION;
break;
}
offboard_control_sp.p1 = (float)quad_motors_setpoint.roll[mavlink_system.sysid-1] / (float)INT16_MAX;
offboard_control_sp.p2 = (float)quad_motors_setpoint.pitch[mavlink_system.sysid-1] / (float)INT16_MAX;
offboard_control_sp.p3= (float)quad_motors_setpoint.yaw[mavlink_system.sysid-1] / (float)INT16_MAX;
offboard_control_sp.p4 = (float)quad_motors_setpoint.thrust[mavlink_system.sysid-1]/(float)UINT16_MAX;
offboard_control_sp.p1 = (float)quad_motors_setpoint.roll[mavlink_system.sysid - 1] / (float)INT16_MAX;
offboard_control_sp.p2 = (float)quad_motors_setpoint.pitch[mavlink_system.sysid - 1] / (float)INT16_MAX;
offboard_control_sp.p3 = (float)quad_motors_setpoint.yaw[mavlink_system.sysid - 1] / (float)INT16_MAX;
offboard_control_sp.p4 = (float)quad_motors_setpoint.thrust[mavlink_system.sysid - 1] / (float)UINT16_MAX;
if (quad_motors_setpoint.thrust[mavlink_system.sysid-1] == 0) {
if (quad_motors_setpoint.thrust[mavlink_system.sysid - 1] == 0) {
ml_armed = false;
}
@ -276,6 +284,7 @@ handle_message(mavlink_message_t *msg)
/* check if topic has to be advertised */
if (offboard_control_sp_pub <= 0) {
offboard_control_sp_pub = orb_advertise(ORB_ID(offboard_control_setpoint), &offboard_control_sp);
} else {
/* Publish */
orb_publish(ORB_ID(offboard_control_setpoint), offboard_control_sp_pub, &offboard_control_sp);
@ -298,6 +307,26 @@ handle_message(mavlink_message_t *msg)
mavlink_hil_state_t hil_state;
mavlink_msg_hil_state_decode(msg, &hil_state);
/* Calculate Rotation Matrix */
//TODO: better clarification which app does this, atm we have a ekf for quadrotors which does this, but there is no such thing if fly in fixed wing mode
if (mavlink_system.type == MAV_TYPE_FIXED_WING) {
//TODO: assuming low pitch and roll values for now
hil_attitude.R[0][0] = cosf(hil_state.yaw);
hil_attitude.R[0][1] = sinf(hil_state.yaw);
hil_attitude.R[0][2] = 0.0f;
hil_attitude.R[1][0] = -sinf(hil_state.yaw);
hil_attitude.R[1][1] = cosf(hil_state.yaw);
hil_attitude.R[1][2] = 0.0f;
hil_attitude.R[2][0] = 0.0f;
hil_attitude.R[2][1] = 0.0f;
hil_attitude.R[2][2] = 1.0f;
hil_attitude.R_valid = true;
}
hil_global_pos.lat = hil_state.lat;
hil_global_pos.lon = hil_state.lon;
hil_global_pos.alt = hil_state.alt / 1000.0f;
@ -305,6 +334,7 @@ handle_message(mavlink_message_t *msg)
hil_global_pos.vy = hil_state.vy / 100.0f;
hil_global_pos.vz = hil_state.vz / 100.0f;
/* set timestamp and notify processes (broadcast) */
hil_global_pos.timestamp = hrt_absolute_time();
orb_publish(ORB_ID(vehicle_global_position), pub_hil_global_pos, &hil_global_pos);
@ -357,12 +387,14 @@ handle_message(mavlink_message_t *msg)
if (rc_pub == 0) {
rc_pub = orb_advertise(ORB_ID(rc_channels), &rc_hil);
} else {
orb_publish(ORB_ID(rc_channels), rc_pub, &rc_hil);
}
if (mc_pub == 0) {
mc_pub = orb_advertise(ORB_ID(manual_control_setpoint), &mc);
} else {
orb_publish(ORB_ID(manual_control_setpoint), mc_pub, &mc);
}
@ -377,7 +409,7 @@ handle_message(mavlink_message_t *msg)
static void *
receive_thread(void *arg)
{
int uart_fd = *((int*)arg);
int uart_fd = *((int *)arg);
const int timeout = 1000;
uint8_t ch;
@ -421,8 +453,8 @@ receive_start(int uart)
pthread_attr_init(&receiveloop_attr);
struct sched_param param;
param.sched_priority = SCHED_PRIORITY_MAX - 40;
(void)pthread_attr_setschedparam(&receiveloop_attr, &param);
param.sched_priority = SCHED_PRIORITY_MAX - 40;
(void)pthread_attr_setschedparam(&receiveloop_attr, &param);
pthread_attr_setstacksize(&receiveloop_attr, 2048);

12
apps/mavlink/missionlib.c
View File

@ -106,6 +106,7 @@ mavlink_missionlib_send_gcs_string(const char *string)
mavlink_msg_statustext_encode(mavlink_system.sysid, mavlink_system.compid, &msg, &statustext);
return mavlink_missionlib_send_message(&msg);
} else {
return 1;
}
@ -144,12 +145,15 @@ void mavlink_missionlib_current_waypoint_changed(uint16_t index, float param1,
sp.altitude = param7_alt_z;
sp.altitude_is_relative = false;
sp.yaw = (param4 / 180.0f) * M_PI_F - M_PI_F;
/* Initialize publication if necessary */
if (global_position_setpoint_pub < 0) {
global_position_setpoint_pub = orb_advertise(ORB_ID(vehicle_global_position_setpoint), &sp);
} else {
orb_publish(ORB_ID(vehicle_global_position_setpoint), global_position_setpoint_pub, &sp);
}
sprintf(buf, "[mp] WP#%i lat: % 3.6f/lon % 3.6f/alt % 4.6f/hdg %3.4f\n", (int)index, (double)param5_lat_x, (double)param6_lon_y, (double)param7_alt_z, (double)param4);
} else if (frame == (int)MAV_FRAME_GLOBAL_RELATIVE_ALT) {
@ -160,12 +164,15 @@ void mavlink_missionlib_current_waypoint_changed(uint16_t index, float param1,
sp.altitude = param7_alt_z;
sp.altitude_is_relative = true;
sp.yaw = (param4 / 180.0f) * M_PI_F - M_PI_F;
/* Initialize publication if necessary */
if (global_position_setpoint_pub < 0) {
global_position_setpoint_pub = orb_advertise(ORB_ID(vehicle_global_position_setpoint), &sp);
} else {
orb_publish(ORB_ID(vehicle_global_position_setpoint), global_position_setpoint_pub, &sp);
}
sprintf(buf, "[mp] WP#%i (lat: %f/lon %f/rel alt %f/hdg %f\n", (int)index, (double)param5_lat_x, (double)param6_lon_y, (double)param7_alt_z, (double)param4);
} else if (frame == (int)MAV_FRAME_LOCAL_ENU || frame == (int)MAV_FRAME_LOCAL_NED) {
@ -175,15 +182,18 @@ void mavlink_missionlib_current_waypoint_changed(uint16_t index, float param1,
sp.y = param6_lon_y;
sp.z = param7_alt_z;
sp.yaw = (param4 / 180.0f) * M_PI_F - M_PI_F;
/* Initialize publication if necessary */
if (local_position_setpoint_pub < 0) {
local_position_setpoint_pub = orb_advertise(ORB_ID(vehicle_local_position_setpoint), &sp);
} else {
orb_publish(ORB_ID(vehicle_local_position_setpoint), local_position_setpoint_pub, &sp);
}
sprintf(buf, "[mp] WP#%i (x: %f/y %f/z %f/hdg %f\n", (int)index, (double)param5_lat_x, (double)param6_lon_y, (double)param7_alt_z, (double)param4);
}
mavlink_missionlib_send_gcs_string(buf);
printf("%s\n", buf);
//printf("[mavlink mp] new setpoint\n");//: frame: %d, lat: %d, lon: %d, alt: %d, yaw: %d\n", frame, param5_lat_x*1000, param6_lon_y*1000, param7_alt_z*1000, param4*1000);

4
apps/mavlink/missionlib.h
View File

@ -48,5 +48,5 @@ extern int mavlink_missionlib_send_message(mavlink_message_t *msg);
extern int mavlink_missionlib_send_gcs_string(const char *string);
extern uint64_t mavlink_missionlib_get_system_timestamp(void);
extern void mavlink_missionlib_current_waypoint_changed(uint16_t index, float param1,
float param2, float param3, float param4, float param5_lat_x,
float param6_lon_y, float param7_alt_z, uint8_t frame, uint16_t command);
float param2, float param3, float param4, float param5_lat_x,
float param6_lon_y, float param7_alt_z, uint8_t frame, uint16_t command);

288
apps/mavlink/orb_listener.c
View File

@ -90,9 +90,8 @@ static uint64_t last_sensor_timestamp;
static void *uorb_receive_thread(void *arg);
struct listener
{
void (*callback)(struct listener *l);
struct listener {
void (*callback)(struct listener *l);
int *subp;
uintptr_t arg;
};
@ -185,14 +184,14 @@ l_sensor_combined(struct listener *l)
if (gcs_link)
mavlink_msg_highres_imu_send(MAVLINK_COMM_0, last_sensor_timestamp,
raw.accelerometer_m_s2[0], raw.accelerometer_m_s2[1],
raw.accelerometer_m_s2[2], raw.gyro_rad_s[0],
raw.gyro_rad_s[1], raw.gyro_rad_s[2],
raw.magnetometer_ga[0],
raw.magnetometer_ga[1],raw.magnetometer_ga[2],
raw.baro_pres_mbar, 0 /* no diff pressure yet */,
raw.baro_alt_meter, raw.baro_temp_celcius,
fields_updated);
raw.accelerometer_m_s2[0], raw.accelerometer_m_s2[1],
raw.accelerometer_m_s2[2], raw.gyro_rad_s[0],
raw.gyro_rad_s[1], raw.gyro_rad_s[2],
raw.magnetometer_ga[0],
raw.magnetometer_ga[1], raw.magnetometer_ga[2],
raw.baro_pres_mbar, 0 /* no diff pressure yet */,
raw.baro_alt_meter, raw.baro_temp_celcius,
fields_updated);
sensors_raw_counter++;
}
@ -209,13 +208,13 @@ l_vehicle_attitude(struct listener *l)
if (gcs_link)
/* send sensor values */
mavlink_msg_attitude_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
att.roll,
att.pitch,
att.yaw,
att.rollspeed,
att.pitchspeed,
att.yawspeed);
last_sensor_timestamp / 1000,
att.roll,
att.pitch,
att.yaw,
att.rollspeed,
att.pitchspeed,
att.yawspeed);
attitude_counter++;
}
@ -291,21 +290,21 @@ l_input_rc(struct listener *l)
{
/* copy rc channels into local buffer */
orb_copy(ORB_ID(input_rc), mavlink_subs.input_rc_sub, &rc_raw);
if (gcs_link)
/* Channels are sent in MAVLink main loop at a fixed interval */
mavlink_msg_rc_channels_raw_send(chan,
rc_raw.timestamp / 1000,
0,
(rc_raw.channel_count > 0) ? rc_raw.values[0] : UINT16_MAX,
(rc_raw.channel_count > 1) ? rc_raw.values[1] : UINT16_MAX,
(rc_raw.channel_count > 2) ? rc_raw.values[2] : UINT16_MAX,
(rc_raw.channel_count > 3) ? rc_raw.values[3] : UINT16_MAX,
(rc_raw.channel_count > 4) ? rc_raw.values[4] : UINT16_MAX,
(rc_raw.channel_count > 5) ? rc_raw.values[5] : UINT16_MAX,
(rc_raw.channel_count > 6) ? rc_raw.values[6] : UINT16_MAX,
(rc_raw.channel_count > 7) ? rc_raw.values[7] : UINT16_MAX,
255);
rc_raw.timestamp / 1000,
0,
(rc_raw.channel_count > 0) ? rc_raw.values[0] : UINT16_MAX,
(rc_raw.channel_count > 1) ? rc_raw.values[1] : UINT16_MAX,
(rc_raw.channel_count > 2) ? rc_raw.values[2] : UINT16_MAX,
(rc_raw.channel_count > 3) ? rc_raw.values[3] : UINT16_MAX,
(rc_raw.channel_count > 4) ? rc_raw.values[4] : UINT16_MAX,
(rc_raw.channel_count > 5) ? rc_raw.values[5] : UINT16_MAX,
(rc_raw.channel_count > 6) ? rc_raw.values[6] : UINT16_MAX,
(rc_raw.channel_count > 7) ? rc_raw.values[7] : UINT16_MAX,
255);
}
void
@ -317,7 +316,7 @@ l_global_position(struct listener *l)
uint64_t timestamp = global_pos.timestamp;
int32_t lat = global_pos.lat;
int32_t lon = global_pos.lon;
int32_t alt = (int32_t)(global_pos.alt*1000);
int32_t alt = (int32_t)(global_pos.alt * 1000);
int32_t relative_alt = (int32_t)(global_pos.relative_alt * 1000.0f);
int16_t vx = (int16_t)(global_pos.vx * 100.0f);
int16_t vy = (int16_t)(global_pos.vy * 100.0f);
@ -343,16 +342,16 @@ l_local_position(struct listener *l)
{
/* copy local position data into local buffer */
orb_copy(ORB_ID(vehicle_local_position), mavlink_subs.local_pos_sub, &local_pos);
if (gcs_link)
mavlink_msg_local_position_ned_send(MAVLINK_COMM_0,
local_pos.timestamp / 1000,
local_pos.x,
local_pos.y,
local_pos.z,
local_pos.vx,
local_pos.vy,
local_pos.vz);
local_pos.timestamp / 1000,
local_pos.x,
local_pos.y,
local_pos.z,
local_pos.vx,
local_pos.vy,
local_pos.vz);
}
void
@ -364,16 +363,17 @@ l_global_position_setpoint(struct listener *l)
orb_copy(ORB_ID(vehicle_global_position_setpoint), mavlink_subs.spg_sub, &global_sp);
uint8_t coordinate_frame = MAV_FRAME_GLOBAL;
if (global_sp.altitude_is_relative)
coordinate_frame = MAV_FRAME_GLOBAL_RELATIVE_ALT;
if (gcs_link)
mavlink_msg_global_position_setpoint_int_send(MAVLINK_COMM_0,
coordinate_frame,
global_sp.lat,
global_sp.lon,
global_sp.altitude,
global_sp.yaw);
coordinate_frame,
global_sp.lat,
global_sp.lon,
global_sp.altitude,
global_sp.yaw);
}
void
@ -386,11 +386,11 @@ l_local_position_setpoint(struct listener *l)
if (gcs_link)
mavlink_msg_local_position_setpoint_send(MAVLINK_COMM_0,
MAV_FRAME_LOCAL_NED,
local_sp.x,
local_sp.y,
local_sp.z,
local_sp.yaw);
MAV_FRAME_LOCAL_NED,
local_sp.x,
local_sp.y,
local_sp.z,
local_sp.yaw);
}
void
@ -403,11 +403,11 @@ l_attitude_setpoint(struct listener *l)
if (gcs_link)
mavlink_msg_roll_pitch_yaw_thrust_setpoint_send(MAVLINK_COMM_0,
att_sp.timestamp/1000,
att_sp.roll_body,
att_sp.pitch_body,
att_sp.yaw_body,
att_sp.thrust);
att_sp.timestamp / 1000,
att_sp.roll_body,
att_sp.pitch_body,
att_sp.yaw_body,
att_sp.thrust);
}
void
@ -420,11 +420,11 @@ l_vehicle_rates_setpoint(struct listener *l)
if (gcs_link)
mavlink_msg_roll_pitch_yaw_rates_thrust_setpoint_send(MAVLINK_COMM_0,
rates_sp.timestamp/1000,
rates_sp.roll,
rates_sp.pitch,
rates_sp.yaw,
rates_sp.thrust);
rates_sp.timestamp / 1000,
rates_sp.roll,
rates_sp.pitch,
rates_sp.yaw,
rates_sp.thrust);
}
void
@ -444,18 +444,18 @@ l_actuator_outputs(struct listener *l)
if (gcs_link) {
mavlink_msg_servo_output_raw_send(MAVLINK_COMM_0, last_sensor_timestamp / 1000,
l->arg /* port number */,
act_outputs.output[0],
act_outputs.output[1],
act_outputs.output[2],
act_outputs.output[3],
act_outputs.output[4],
act_outputs.output[5],
act_outputs.output[6],
act_outputs.output[7]);
l->arg /* port number */,
act_outputs.output[0],
act_outputs.output[1],
act_outputs.output[2],
act_outputs.output[3],
act_outputs.output[4],
act_outputs.output[5],
act_outputs.output[6],
act_outputs.output[7]);
/* only send in HIL mode */
if (mavlink_hil_enabled) {
if (mavlink_hil_enabled && armed.armed) {
/* translate the current syste state to mavlink state and mode */
uint8_t mavlink_state = 0;
@ -468,72 +468,75 @@ l_actuator_outputs(struct listener *l)
if (mavlink_system.type == MAV_TYPE_QUADROTOR) {
mavlink_msg_hil_controls_send(chan,
hrt_absolute_time(),
((act_outputs.output[0] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[1] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f,
-1,
-1,
-1,
-1,
mavlink_mode,
0);
hrt_absolute_time(),
((act_outputs.output[0] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[1] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f,
-1,
-1,
-1,
-1,
mavlink_mode,
0);
} else if (mavlink_system.type == MAV_TYPE_HEXAROTOR) {
mavlink_msg_hil_controls_send(chan,
hrt_absolute_time(),
((act_outputs.output[0] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[1] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[4] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[5] - 900.0f) / 600.0f) / 2.0f,
-1,
-1,
mavlink_mode,
0);
hrt_absolute_time(),
((act_outputs.output[0] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[1] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[4] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[5] - 900.0f) / 600.0f) / 2.0f,
-1,
-1,
mavlink_mode,
0);
} else if (mavlink_system.type == MAV_TYPE_OCTOROTOR) {
mavlink_msg_hil_controls_send(chan,
hrt_absolute_time(),
((act_outputs.output[0] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[1] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[4] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[5] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[6] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[7] - 900.0f) / 600.0f) / 2.0f,
mavlink_mode,
0);
hrt_absolute_time(),
((act_outputs.output[0] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[1] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[4] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[5] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[6] - 900.0f) / 600.0f) / 2.0f,
((act_outputs.output[7] - 900.0f) / 600.0f) / 2.0f,
mavlink_mode,
0);
} else {
/*
* Catch the case where no rudder is in use and throttle is not
* on output four
*/
float rudder, throttle;
/* SCALING: PWM min: 900, PWM max: 2100, center: 1500 */
if (act_outputs.noutputs < 4) {
rudder = 0.0f;
throttle = (act_outputs.output[2] - 900.0f) / 1200.0f;
// XXX very ugly, needs rework
if (isfinite(act_outputs.output[3])
&& act_outputs.output[3] > 800 && act_outputs.output[3] < 2200) {
/* throttle is fourth output */
rudder = (act_outputs.output[2] - 1500.0f) / 600.0f;
throttle = (((act_outputs.output[3] - 900.0f) / 600.0f) / 2.0f);
} else {
/* only three outputs, put throttle on position 4 / index 3 */
rudder = 0;
throttle = (((act_outputs.output[2] - 900.0f) / 600.0f) / 2.0f);
rudder = (act_outputs.output[2] - 1500.0f) / 600.0f;
throttle = (act_outputs.output[3] - 900.0f) / 1200.0f;
}
mavlink_msg_hil_controls_send(chan,
hrt_absolute_time(),
(act_outputs.output[0] - 1500.0f) / 600.0f,
(act_outputs.output[1] - 1500.0f) / 600.0f,
rudder,
throttle,
(act_outputs.output[4] - 1500.0f) / 600.0f,
(act_outputs.output[5] - 1500.0f) / 600.0f,
(act_outputs.output[6] - 1500.0f) / 600.0f,
(act_outputs.output[7] - 1500.0f) / 600.0f,
mavlink_mode,
0);
hrt_absolute_time(),
(act_outputs.output[0] - 1500.0f) / 600.0f,
(act_outputs.output[1] - 1500.0f) / 600.0f,
rudder,
throttle,
(act_outputs.output[4] - 1500.0f) / 600.0f,
(act_outputs.output[5] - 1500.0f) / 600.0f,
(act_outputs.output[6] - 1500.0f) / 600.0f,
(act_outputs.output[7] - 1500.0f) / 600.0f,
mavlink_mode,
0);
}
}
}
@ -555,39 +558,39 @@ l_manual_control_setpoint(struct listener *l)
if (gcs_link)
mavlink_msg_manual_control_send(MAVLINK_COMM_0,
mavlink_system.sysid,
man_control.roll * 1000,
man_control.pitch * 1000,
man_control.yaw * 1000,
man_control.throttle * 1000,
0);
mavlink_system.sysid,
man_control.roll * 1000,
man_control.pitch * 1000,
man_control.yaw * 1000,
man_control.throttle * 1000,
0);
}
void
l_vehicle_attitude_controls(struct listener *l)
{
struct actuator_controls_s actuators;
struct actuator_controls_effective_s actuators;
orb_copy(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, mavlink_subs.actuators_sub, &actuators);
orb_copy(ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE, mavlink_subs.actuators_sub, &actuators);
if (gcs_link) {
/* send, add spaces so that string buffer is at least 10 chars long */
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"ctrl0 ",
actuators.control[0]);
"eff ctrl0 ",
actuators.control_effective[0]);
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"ctrl1 ",
actuators.control[1]);
"eff ctrl1 ",
actuators.control_effective[1]);
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"ctrl2 ",
actuators.control[2]);
"eff ctrl2 ",
actuators.control_effective[2]);
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"ctrl3 ",
actuators.control[3]);
"eff ctrl3 ",
actuators.control_effective[3]);
}
}
@ -615,7 +618,7 @@ l_optical_flow(struct listener *l)
orb_copy(ORB_ID(optical_flow), mavlink_subs.optical_flow, &flow);
mavlink_msg_optical_flow_send(MAVLINK_COMM_0, flow.timestamp, flow.sensor_id, flow.flow_raw_x, flow.flow_raw_y,
flow.flow_comp_x_m, flow.flow_comp_y_m, flow.quality, flow.ground_distance_m);
flow.flow_comp_x_m, flow.flow_comp_y_m, flow.quality, flow.ground_distance_m);
}
static void *
@ -636,6 +639,7 @@ uorb_receive_thread(void *arg)
* Might want to invoke each listener once to set initial state.
*/
struct pollfd fds[n_listeners];
for (unsigned i = 0; i < n_listeners; i++) {
fds[i].fd = *listeners[i].subp;
fds[i].events = POLLIN;
@ -651,8 +655,10 @@ uorb_receive_thread(void *arg)
/* handle the poll result */
if (poll_ret == 0) {
mavlink_missionlib_send_gcs_string("[mavlink] No telemetry data for 1 s");
} else if (poll_ret < 0) {
mavlink_missionlib_send_gcs_string("[mavlink] ERROR reading uORB data");
} else {
for (unsigned i = 0; i < n_listeners; i++) {
@ -739,7 +745,7 @@ uorb_receive_start(void)
orb_set_interval(mavlink_subs.man_control_sp_sub, 100); /* 10Hz updates */
/* --- ACTUATOR CONTROL VALUE --- */
mavlink_subs.actuators_sub = orb_subscribe(ORB_ID_VEHICLE_ATTITUDE_CONTROLS);
mavlink_subs.actuators_sub = orb_subscribe(ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE);
orb_set_interval(mavlink_subs.actuators_sub, 100); /* 10Hz updates */
/* --- DEBUG VALUE OUTPUT --- */

1
apps/mavlink/waypoints.c
View File

@ -379,6 +379,7 @@ void check_waypoints_reached(uint64_t now, const struct vehicle_global_position_
if (counter % 100 == 0)
printf("Setpoint reached: %0.4f, orbit: %.4f\n", dist, orbit);
}
// else
// {
// if(counter % 100 == 0)

134
apps/multirotor_att_control/multirotor_att_control_main.c
View File

@ -116,7 +116,7 @@ mc_thread_main(int argc, char *argv[])
int manual_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
int sensor_sub = orb_subscribe(ORB_ID(sensor_combined));
/*
/*
* Do not rate-limit the loop to prevent aliasing
* if rate-limiting would be desired later, the line below would
* enable it.
@ -125,9 +125,9 @@ mc_thread_main(int argc, char *argv[])
* orb_set_interval(att_sub, 5);
*/
struct pollfd fds[2] = {
{ .fd = att_sub, .events = POLLIN },
{ .fd = param_sub, .events = POLLIN }
};
{ .fd = att_sub, .events = POLLIN },
{ .fd = param_sub, .events = POLLIN }
};
/* publish actuator controls */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++) {
@ -171,6 +171,7 @@ mc_thread_main(int argc, char *argv[])
if (ret < 0) {
/* poll error, count it in perf */
perf_count(mc_err_perf);
} else if (ret == 0) {
/* no return value, ignore */
} else {
@ -193,9 +194,11 @@ mc_thread_main(int argc, char *argv[])
/* get a local copy of system state */
bool updated;
orb_check(state_sub, &updated);
if (updated) {
orb_copy(ORB_ID(vehicle_status), state_sub, &state);
}
/* get a local copy of manual setpoint */
orb_copy(ORB_ID(manual_control_setpoint), manual_sub, &manual);
/* get a local copy of attitude */
@ -204,9 +207,11 @@ mc_thread_main(int argc, char *argv[])
orb_copy(ORB_ID(vehicle_attitude_setpoint), att_setpoint_sub, &att_sp);
/* get a local copy of rates setpoint */
orb_check(setpoint_sub, &updated);
if (updated) {
orb_copy(ORB_ID(offboard_control_setpoint), setpoint_sub, &offboard_sp);
}
/* get a local copy of the current sensor values */
orb_copy(ORB_ID(sensor_combined), sensor_sub, &raw);
@ -222,6 +227,7 @@ mc_thread_main(int argc, char *argv[])
// printf("thrust_rate=%8.4f\n",offboard_sp.p4);
rates_sp.timestamp = hrt_absolute_time();
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_sp_pub, &rates_sp);
} else if (offboard_sp.mode == OFFBOARD_CONTROL_MODE_DIRECT_ATTITUDE) {
att_sp.roll_body = offboard_sp.p1;
att_sp.pitch_body = offboard_sp.p2;
@ -232,38 +238,42 @@ mc_thread_main(int argc, char *argv[])
/* STEP 2: publish the result to the vehicle actuators */
orb_publish(ORB_ID(vehicle_attitude_setpoint), att_sp_pub, &att_sp);
}
/* decide wether we want rate or position input */
}
else if (state.flag_control_manual_enabled) {
/* manual inputs, from RC control or joystick */
if (state.flag_control_rates_enabled && !state.flag_control_attitude_enabled) {
rates_sp.roll = manual.roll;
rates_sp.pitch = manual.pitch;
rates_sp.yaw = manual.yaw;
rates_sp.thrust = manual.throttle;
rates_sp.timestamp = hrt_absolute_time();
}
} else if (state.flag_control_manual_enabled) {
if (state.flag_control_attitude_enabled) {
/* initialize to current yaw if switching to manual or att control */
if (state.flag_control_attitude_enabled != flag_control_attitude_enabled ||
state.flag_control_manual_enabled != flag_control_manual_enabled ||
state.flag_system_armed != flag_system_armed) {
state.flag_control_manual_enabled != flag_control_manual_enabled ||
state.flag_system_armed != flag_system_armed) {
att_sp.yaw_body = att.yaw;
}
static bool rc_loss_first_time = true;
/* if the RC signal is lost, try to stay level and go slowly back down to ground */
if(state.rc_signal_lost) {
if (state.rc_signal_lost) {
/* the failsafe throttle is stored as a parameter, as it depends on the copter and the payload */
param_get(failsafe_throttle_handle, &failsafe_throttle);
att_sp.roll_body = 0.0f;
att_sp.pitch_body = 0.0f;
att_sp.thrust = failsafe_throttle;
/*
* Only go to failsafe throttle if last known throttle was
* high enough to create some lift to make hovering state likely.
*
* This is to prevent that someone landing, but not disarming his
* multicopter (throttle = 0) does not make it jump up in the air
* if shutting down his remote.
*/
if (isfinite(manual.throttle) && manual.throttle > 0.2f) {
att_sp.thrust = failsafe_throttle;
} else {
att_sp.thrust = 0.0f;
}
/* keep current yaw, do not attempt to go to north orientation,
* since if the pilot regains RC control, he will be lost regarding
@ -285,50 +295,78 @@ mc_thread_main(int argc, char *argv[])
att_sp.yaw_body = att.yaw;
}
/* only move setpoint if manual input is != 0 */
/* act if stabilization is active or if the (nonsense) direct pass through mode is set */
if (state.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS ||
state.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_DIRECT) {
if(manual.mode == MANUAL_CONTROL_MODE_ATT_YAW_POS) {
if ((manual.yaw < -0.01f || 0.01f < manual.yaw) && manual.throttle > 0.3f) {
if (state.manual_sas_mode == VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_RATE) {
rates_sp.yaw = manual.yaw;
control_yaw_position = false;
first_time_after_yaw_speed_control = true;
} else {
if (first_time_after_yaw_speed_control) {
att_sp.yaw_body = att.yaw;
first_time_after_yaw_speed_control = false;
/*
* This mode SHOULD be the default mode, which is:
* VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_ABS
*
* However, we fall back to this setting for all other (nonsense)
* settings as well.
*/
/* only move setpoint if manual input is != 0 */
if ((manual.yaw < -0.01f || 0.01f < manual.yaw) && manual.throttle > 0.3f) {
rates_sp.yaw = manual.yaw;
control_yaw_position = false;
first_time_after_yaw_speed_control = true;
} else {
if (first_time_after_yaw_speed_control) {
att_sp.yaw_body = att.yaw;
first_time_after_yaw_speed_control = false;
}
control_yaw_position = true;
}
control_yaw_position = true;
}
} else if (manual.mode == MANUAL_CONTROL_MODE_ATT_YAW_RATE) {
rates_sp.yaw = manual.yaw;
control_yaw_position = false;
}
att_sp.thrust = manual.throttle;
att_sp.timestamp = hrt_absolute_time();
}
}
/* STEP 2: publish the result to the vehicle actuators */
orb_publish(ORB_ID(vehicle_attitude_setpoint), att_sp_pub, &att_sp);
if (motor_test_mode) {
printf("testmode");
att_sp.roll_body = 0.0f;
att_sp.pitch_body = 0.0f;
att_sp.yaw_body = 0.0f;
att_sp.thrust = 0.1f;
att_sp.timestamp = hrt_absolute_time();
/* STEP 2: publish the result to the vehicle actuators */
/* STEP 2: publish the controller output */
orb_publish(ORB_ID(vehicle_attitude_setpoint), att_sp_pub, &att_sp);
if (motor_test_mode) {
printf("testmode");
att_sp.roll_body = 0.0f;
att_sp.pitch_body = 0.0f;
att_sp.yaw_body = 0.0f;
att_sp.thrust = 0.1f;
att_sp.timestamp = hrt_absolute_time();
/* STEP 2: publish the result to the vehicle actuators */
orb_publish(ORB_ID(vehicle_attitude_setpoint), att_sp_pub, &att_sp);
}
} else {
/* manual rate inputs, from RC control or joystick */
if (state.flag_control_rates_enabled &&
state.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_RATES) {
rates_sp.roll = manual.roll;
rates_sp.pitch = manual.pitch;
rates_sp.yaw = manual.yaw;
rates_sp.thrust = manual.throttle;
rates_sp.timestamp = hrt_absolute_time();
}
}
}
/** STEP 3: Identify the controller setup to run and set up the inputs correctly */
if (state.flag_control_attitude_enabled) {
multirotor_control_attitude(&att_sp, &att, &rates_sp, control_yaw_position);
multirotor_control_attitude(&att_sp, &att, &rates_sp, control_yaw_position);
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_sp_pub, &rates_sp);
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_sp_pub, &rates_sp);
}
/* measure in what intervals the controller runs */
@ -339,6 +377,7 @@ mc_thread_main(int argc, char *argv[])
/* get current rate setpoint */
bool rates_sp_valid = false;
orb_check(rates_sp_sub, &rates_sp_valid);
if (rates_sp_valid) {
orb_copy(ORB_ID(vehicle_rates_setpoint), rates_sp_sub, &rates_sp);
}
@ -366,6 +405,7 @@ mc_thread_main(int argc, char *argv[])
/* kill all outputs */
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROLS; i++)
actuators.control[i] = 0.0f;
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
@ -387,6 +427,7 @@ usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: multirotor_att_control [-m <mode>] [-t] {start|status|stop}\n");
fprintf(stderr, " <mode> is 'rates' or 'attitude'\n");
fprintf(stderr, " -t enables motor test mode with 10%% thrust\n");
@ -404,22 +445,25 @@ int multirotor_att_control_main(int argc, char *argv[])
motor_test_mode = true;
optioncount += 1;
break;
case ':':
usage("missing parameter");
break;
default:
fprintf(stderr, "option: -%c\n", ch);
usage("unrecognized option");
break;
}
}
argc -= optioncount;
//argv += optioncount;
if (argc < 1)
usage("missing command");
if (!strcmp(argv[1+optioncount], "start")) {
if (!strcmp(argv[1 + optioncount], "start")) {
thread_should_exit = false;
mc_task = task_spawn("multirotor_att_control",
@ -431,7 +475,7 @@ int multirotor_att_control_main(int argc, char *argv[])
exit(0);
}
if (!strcmp(argv[1+optioncount], "stop")) {
if (!strcmp(argv[1 + optioncount], "stop")) {
thread_should_exit = true;
exit(0);
}

25
apps/multirotor_att_control/multirotor_attitude_control.c
View File

@ -158,16 +158,18 @@ static int parameters_update(const struct mc_att_control_param_handles *h, struc
}
void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att, struct vehicle_rates_setpoint_s *rates_sp, bool control_yaw_position)
const struct vehicle_attitude_s *att, struct vehicle_rates_setpoint_s *rates_sp, bool control_yaw_position)
{
static uint64_t last_run = 0;
static uint64_t last_input = 0;
float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
float dT_input = (hrt_absolute_time() - last_input) / 1000000.0f;
last_run = hrt_absolute_time();
if (last_input != att_sp->timestamp) {
last_input = att_sp->timestamp;
}
static int sensor_delay;
sensor_delay = hrt_absolute_time() - att->timestamp;
@ -189,15 +191,15 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
parameters_update(&h, &p);
pid_init(&pitch_controller, p.att_p, p.att_i, p.att_d, 1000.0f,
1000.0f, PID_MODE_DERIVATIV_SET);
1000.0f, PID_MODE_DERIVATIV_SET);
pid_init(&roll_controller, p.att_p, p.att_i, p.att_d, 1000.0f,
1000.0f, PID_MODE_DERIVATIV_SET);
1000.0f, PID_MODE_DERIVATIV_SET);
initialized = true;
}
/* load new parameters with lower rate */
if (motor_skip_counter % 1000 == 0) {
if (motor_skip_counter % 500 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
@ -206,17 +208,24 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
pid_set_parameters(&roll_controller, p.att_p, p.att_i, p.att_d, 1000.0f, 1000.0f);
}
/* reset integral if on ground */
if (att_sp->thrust < 0.1f) {
pid_reset_integral(&pitch_controller);
pid_reset_integral(&roll_controller);
}
/* calculate current control outputs */
/* control pitch (forward) output */
rates_sp->pitch = pid_calculate(&pitch_controller, att_sp->pitch_body ,
att->pitch, att->pitchspeed, deltaT);
att->pitch, att->pitchspeed, deltaT);
/* control roll (left/right) output */
rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body ,
att->roll, att->rollspeed, deltaT);
att->roll, att->rollspeed, deltaT);
if(control_yaw_position) {
if (control_yaw_position) {
/* control yaw rate */
/* positive error: rotate to right, negative error, rotate to left (NED frame) */
@ -226,12 +235,14 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
if (yaw_error > M_PI_F) {
yaw_error -= M_TWOPI_F;
} else if (yaw_error < -M_PI_F) {
yaw_error += M_TWOPI_F;
}
rates_sp->yaw = p.yaw_p * (yaw_error) - (p.yaw_d * att->yawspeed);
}
rates_sp->thrust = att_sp->thrust;
motor_skip_counter++;

2
apps/multirotor_att_control/multirotor_attitude_control.h
View File

@ -52,6 +52,6 @@
#include <uORB/topics/actuator_controls.h>
void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att, struct vehicle_rates_setpoint_s *rates_sp, bool control_yaw_position);
const struct vehicle_attitude_s *att, struct vehicle_rates_setpoint_s *rates_sp, bool control_yaw_position);
#endif /* MULTIROTOR_ATTITUDE_CONTROL_H_ */

10
apps/multirotor_att_control/multirotor_rate_control.c
View File

@ -148,7 +148,7 @@ static int parameters_update(const struct mc_rate_control_param_handles *h, stru
}
void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[], struct actuator_controls_s *actuators)
const float rates[], struct actuator_controls_s *actuators)
{
static float roll_control_last = 0;
static float pitch_control_last = 0;
@ -157,6 +157,7 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
static uint64_t last_input = 0;
float dT_input = (hrt_absolute_time() - last_input) / 1000000.0f;
if (last_input != rate_sp->timestamp) {
last_input = rate_sp->timestamp;
}
@ -186,12 +187,14 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
}
/* calculate current control outputs */
/* control pitch (forward) output */
float pitch_control = p.attrate_p * (rate_sp->pitch - rates[1]) - (p.attrate_d * pitch_control_last);
/* increase resilience to faulty control inputs */
if (isfinite(pitch_control)) {
pitch_control_last = pitch_control;
} else {
pitch_control = 0.0f;
warnx("rej. NaN ctrl pitch");
@ -199,9 +202,11 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
/* control roll (left/right) output */
float roll_control = p.attrate_p * (rate_sp->roll - rates[0]) - (p.attrate_d * roll_control_last);
/* increase resilience to faulty control inputs */
if (isfinite(roll_control)) {
roll_control_last = roll_control;
} else {
roll_control = 0.0f;
warnx("rej. NaN ctrl roll");
@ -209,6 +214,7 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
/* control yaw rate */
float yaw_rate_control = p.yawrate_p * (rate_sp->yaw - rates[2]);
/* increase resilience to faulty control inputs */
if (!isfinite(yaw_rate_control)) {
yaw_rate_control = 0.0f;

2
apps/multirotor_att_control/multirotor_rate_control.h
View File

@ -51,6 +51,6 @@
#include <uORB/topics/actuator_controls.h>
void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[], struct actuator_controls_s *actuators);
const float rates[], struct actuator_controls_s *actuators);
#endif /* MULTIROTOR_RATE_CONTROL_H_ */

13
apps/px4io/adc.c
View File

@ -87,12 +87,16 @@ adc_init(void)
#ifdef ADC_CR2_CAL
rCR2 |= ADC_CR2_RSTCAL;
up_udelay(1);
if (rCR2 & ADC_CR2_RSTCAL)
return -1;
rCR2 |= ADC_CR2_CAL;
up_udelay(100);
if (rCR2 & ADC_CR2_CAL)
return -1;
#endif
/* arbitrarily configure all channels for 55 cycle sample time */
@ -103,7 +107,7 @@ adc_init(void)
rCR1 = 0;
/* enable the temperature sensor / Vrefint channel if supported*/
rCR2 =
rCR2 =
#ifdef ADC_CR2_TSVREFE
/* enable the temperature sensor in CR2 */
ADC_CR2_TSVREFE |
@ -118,7 +122,7 @@ adc_init(void)
/* configure for a single-channel sequence */
rSQR1 = 0;
rSQR2 = 0;
rSQR3 = 0; /* will be updated with the channel each tick */
rSQR3 = 0; /* will be updated with the channel each tick */
/* power-cycle the ADC and turn it on */
rCR2 &= ~ADC_CR2_ADON;
@ -146,6 +150,7 @@ adc_measure(unsigned channel)
/* wait for the conversion to complete */
hrt_abstime now = hrt_absolute_time();
while (!(rSR & ADC_SR_EOC)) {
/* never spin forever - this will give a bogus result though */
@ -159,5 +164,5 @@ adc_measure(unsigned channel)
uint16_t result = rDR;
perf_end(adc_perf);
return result;
}
return result;
}

62
apps/px4io/comms.c
View File

@ -52,6 +52,7 @@
#include <nuttx/clock.h>
#include <drivers/drv_hrt.h>
#include <drivers/drv_pwm_output.h>
#include <systemlib/hx_stream.h>
#include <systemlib/perf_counter.h>
@ -139,8 +140,9 @@ comms_main(void)
last_report_time = now;
/* populate the report */
for (unsigned i = 0; i < system_state.rc_channels; i++)
for (unsigned i = 0; i < system_state.rc_channels; i++) {
report.rc_channel[i] = system_state.rc_channel_data[i];
}
report.channel_count = system_state.rc_channels;
report.armed = system_state.armed;
@ -188,7 +190,7 @@ comms_main(void)
system_state.adc_in5 = adc_measure(ADC_IN5);
system_state.overcurrent =
system_state.overcurrent =
(OVERCURRENT_SERVO ? (1 << 0) : 0) |
(OVERCURRENT_ACC ? (1 << 1) : 0);
@ -205,7 +207,19 @@ comms_handle_config(const void *buffer, size_t length)
if (length != sizeof(*cfg))
return;
/* XXX */
/* fetch the rc mappings */
for (unsigned i = 0; i < 4; i++) {
system_state.rc_map[i] = cfg->rc_map[i];
}
/* fetch the rc channel attributes */
for (unsigned i = 0; i < 4; i++) {
system_state.rc_min[i] = cfg->rc_min[i];
system_state.rc_trim[i] = cfg->rc_trim[i];
system_state.rc_max[i] = cfg->rc_max[i];
system_state.rc_rev[i] = cfg->rc_rev[i];
system_state.rc_dz[i] = cfg->rc_dz[i];
}
}
static void
@ -215,7 +229,7 @@ comms_handle_command(const void *buffer, size_t length)
if (length != sizeof(*cmd))
return;
irqstate_t flags = irqsave();
/* fetch new PWM output values */
@ -227,31 +241,59 @@ comms_handle_command(const void *buffer, size_t length)
system_state.armed = false;
system_state.arm_ok = cmd->arm_ok;
system_state.mixer_use_fmu = true;
system_state.fmu_data_received = true;
system_state.vector_flight_mode_ok = cmd->vector_flight_mode_ok;
system_state.manual_override_ok = cmd->manual_override_ok;
system_state.mixer_fmu_available = true;
system_state.fmu_data_received_time = hrt_absolute_time();
/* handle changes signalled by FMU */
// if (!system_state.arm_ok && system_state.armed)
// system_state.armed = false;
/* set PWM update rate if changed (after limiting) */
uint16_t new_servo_rate = cmd->servo_rate;
/* handle relay state changes here */
/* reject faster than 500 Hz updates */
if (new_servo_rate > 500) {
new_servo_rate = 500;
}
/* reject slower than 50 Hz updates */
if (new_servo_rate < 50) {
new_servo_rate = 50;
}
if (system_state.servo_rate != new_servo_rate) {
up_pwm_servo_set_rate(new_servo_rate);
system_state.servo_rate = new_servo_rate;
}
/*
* update servo values immediately.
* the updates are done in addition also
* in the mainloop, since this function will only
* update with a connected FMU.
*/
mixer_tick();
/* handle relay state changes here */
for (unsigned i = 0; i < PX4IO_RELAY_CHANNELS; i++) {
if (system_state.relays[i] != cmd->relay_state[i]) {
switch (i) {
case 0:
POWER_ACC1(cmd->relay_state[i]);
break;
case 1:
POWER_ACC2(cmd->relay_state[i]);
break;
case 2:
POWER_RELAY1(cmd->relay_state[i]);
break;
case 3:
POWER_RELAY2(cmd->relay_state[i]);
break;
}
}
system_state.relays[i] = cmd->relay_state[i];
}

42
apps/px4io/controls.c
View File

@ -60,6 +60,10 @@
#define DEBUG
#include "px4io.h"
#define RC_FAILSAFE_TIMEOUT 2000000 /**< two seconds failsafe timeout */
#define RC_CHANNEL_HIGH_THRESH 1700
#define RC_CHANNEL_LOW_THRESH 1300
static void ppm_input(void);
void
@ -88,6 +92,12 @@ controls_main(void)
*/
bool locked = false;
/*
* Store RC channel count to detect switch to RC loss sooner
* than just by timeout
*/
unsigned rc_channels = system_state.rc_channels;
if (fds[0].revents & POLLIN)
locked |= dsm_input();
@ -107,22 +117,39 @@ controls_main(void)
if (!locked)
ppm_input();
/* check for manual override status */
if (system_state.rc_channel_data[4] > RC_CHANNEL_HIGH_THRESH) {
/* force manual input override */
system_state.mixer_manual_override = true;
} else {
/* override not engaged, use FMU */
system_state.mixer_manual_override = false;
}
/*
* If we haven't seen any new control data in 200ms, assume we
* have lost input and tell FMU.
*/
if ((hrt_absolute_time() - system_state.rc_channels_timestamp) > 200000) {
if (system_state.rc_channels > 0) {
/*
* If the RC signal status (lost / present) has
* just changed, request an update immediately.
*/
system_state.fmu_report_due = true;
}
/* set the number of channels to zero - no inputs */
system_state.rc_channels = 0;
/* trigger an immediate report to the FMU */
system_state.fmu_report_due = true;
}
/* XXX do bypass mode, etc. here */
/* do PWM output updates */
/*
* PWM output updates are performed in addition on each comm update.
* the updates here are required to ensure operation if FMU is not started
* or stopped responding.
*/
mixer_tick();
}
}
@ -141,8 +168,9 @@ ppm_input(void)
/* PPM data exists, copy it */
system_state.rc_channels = ppm_decoded_channels;
for (unsigned i = 0; i < ppm_decoded_channels; i++)
for (unsigned i = 0; i < ppm_decoded_channels; i++) {
system_state.rc_channel_data[i] = ppm_buffer[i];
}
/* copy the timestamp and clear it */
system_state.rc_channels_timestamp = ppm_last_valid_decode;

116
apps/px4io/mixer.cpp
View File

@ -47,8 +47,14 @@
#include <errno.h>
#include <unistd.h>
#include <fcntl.h>
#include <sched.h>
#include <debug.h>
#include <drivers/drv_pwm_output.h>
#include <drivers/drv_hrt.h>
#include <drivers/device/device.h>
#include <systemlib/mixer/mixer.h>
extern "C" {
@ -57,10 +63,16 @@ extern "C" {
}
/*
* Count of periodic calls in which we have no FMU input.
* Maximum interval in us before FMU signal is considered lost
*/
static unsigned fmu_input_drops;
#define FMU_INPUT_DROP_LIMIT 20
#define FMU_INPUT_DROP_LIMIT_US 200000
/* XXX need to move the RC_CHANNEL_FUNCTION out of rc_channels.h and into systemlib */
#define ROLL 0
#define PITCH 1
#define YAW 2
#define THROTTLE 3
#define OVERRIDE 4
/* current servo arm/disarm state */
bool mixer_servos_armed = false;
@ -69,6 +81,8 @@ bool mixer_servos_armed = false;
static uint16_t *control_values;
static int control_count;
static uint16_t rc_channel_data[PX4IO_INPUT_CHANNELS];
static int mixer_callback(uintptr_t handle,
uint8_t control_group,
uint8_t control_index,
@ -81,37 +95,80 @@ mixer_tick(void)
{
bool should_arm;
/* check that we are receiving fresh data from the FMU */
if ((hrt_absolute_time() - system_state.fmu_data_received_time) > FMU_INPUT_DROP_LIMIT_US) {
/* too many frames without FMU input, time to go to failsafe */
system_state.mixer_manual_override = true;
system_state.mixer_fmu_available = false;
lib_lowprintf("RX timeout\n");
}
/*
* Decide which set of inputs we're using.
*/
if (system_state.mixer_use_fmu) {
/* we have recent control data from the FMU */
control_count = PX4IO_CONTROL_CHANNELS;
control_values = &system_state.fmu_channel_data[0];
/* this is for planes, where manual override makes sense */
if (system_state.manual_override_ok) {
/* if everything is ok */
if (!system_state.mixer_manual_override && system_state.mixer_fmu_available) {
/* we have recent control data from the FMU */
control_count = PX4IO_CONTROL_CHANNELS;
control_values = &system_state.fmu_channel_data[0];
/* check that we are receiving fresh data from the FMU */
if (!system_state.fmu_data_received) {
fmu_input_drops++;
} else if (system_state.rc_channels > 0) {
/* when override is on or the fmu is not available, but RC is present */
control_count = system_state.rc_channels;
/* too many frames without FMU input, time to go to failsafe */
if (fmu_input_drops >= FMU_INPUT_DROP_LIMIT) {
system_state.mixer_use_fmu = false;
sched_lock();
/* remap roll, pitch, yaw and throttle from RC specific to internal ordering */
rc_channel_data[ROLL] = system_state.rc_channel_data[system_state.rc_map[ROLL] - 1];
rc_channel_data[PITCH] = system_state.rc_channel_data[system_state.rc_map[PITCH] - 1];
rc_channel_data[YAW] = system_state.rc_channel_data[system_state.rc_map[YAW] - 1];
rc_channel_data[THROTTLE] = system_state.rc_channel_data[system_state.rc_map[THROTTLE] - 1];
//rc_channel_data[OVERRIDE] = system_state.rc_channel_data[system_state.rc_map[OVERRIDE] - 1];
/* get the remaining channels, no remapping needed */
for (unsigned i = 4; i < system_state.rc_channels; i++) {
rc_channel_data[i] = system_state.rc_channel_data[i];
}
/* scale the control inputs */
rc_channel_data[THROTTLE] = ((float)(rc_channel_data[THROTTLE] - system_state.rc_min[THROTTLE]) /
(float)(system_state.rc_max[THROTTLE] - system_state.rc_min[THROTTLE])) * 1000.0f + 1000;
if (rc_channel_data[THROTTLE] > 2000) {
rc_channel_data[THROTTLE] = 2000;
}
if (rc_channel_data[THROTTLE] < 1000) {
rc_channel_data[THROTTLE] = 1000;
}
// lib_lowprintf("Tmin: %d Ttrim: %d Tmax: %d T: %d \n",
// (int)(system_state.rc_min[THROTTLE]), (int)(system_state.rc_trim[THROTTLE]),
// (int)(system_state.rc_max[THROTTLE]), (int)(rc_channel_data[THROTTLE]));
control_values = &rc_channel_data[0];
sched_unlock();
} else {
fmu_input_drops = 0;
system_state.fmu_data_received = false;
/* we have no control input (no FMU, no RC) */
// XXX builtin failsafe would activate here
control_count = 0;
}
//lib_lowprintf("R: %d P: %d Y: %d T: %d \n", control_values[0], control_values[1], control_values[2], control_values[3]);
} else if (system_state.rc_channels > 0) {
/* we have control data from an R/C input */
control_count = system_state.rc_channels;
control_values = &system_state.rc_channel_data[0];
/* this is for multicopters, etc. where manual override does not make sense */
} else {
/* we have no control input */
/* XXX builtin failsafe would activate here */
control_count = 0;
/* if the fmu is available whe are good */
if (system_state.mixer_fmu_available) {
control_count = PX4IO_CONTROL_CHANNELS;
control_values = &system_state.fmu_channel_data[0];
/* we better shut everything off */
} else {
control_count = 0;
}
}
/*
@ -138,14 +195,17 @@ mixer_tick(void)
/*
* If we are armed, update the servo output.
*/
if (system_state.armed && system_state.arm_ok)
if (system_state.armed && system_state.arm_ok) {
up_pwm_servo_set(i, system_state.servos[i]);
}
}
}
/*
* Decide whether the servos should be armed right now.
* A sufficient reason is armed state and either FMU or RC control inputs
*/
should_arm = system_state.armed && system_state.arm_ok && (control_count > 0);
if (should_arm && !mixer_servos_armed) {
@ -171,7 +231,11 @@ mixer_callback(uintptr_t handle,
return -1;
/* scale from current PWM units (1000-2000) to mixer input values */
control = ((float)control_values[control_index] - 1500.0f) / 500.0f;
if (system_state.manual_override_ok && system_state.mixer_manual_override && control_index == 3) {
control = ((float)control_values[control_index] - 1000.0f) / 1000.0f;
} else {
control = ((float)control_values[control_index] - 1500.0f) / 500.0f;
}
return 0;
}
@ -229,4 +293,4 @@ mixer_handle_text(const void *buffer, size_t length)
break;
}
}
}

16
apps/px4io/protocol.h
View File

@ -54,9 +54,12 @@ struct px4io_command {
uint16_t f2i_magic;
#define F2I_MAGIC 0x636d
uint16_t output_control[PX4IO_CONTROL_CHANNELS];
bool relay_state[PX4IO_RELAY_CHANNELS];
bool arm_ok;
uint16_t servo_rate;
uint16_t output_control[PX4IO_CONTROL_CHANNELS]; /**< PWM output rate in Hz */
bool relay_state[PX4IO_RELAY_CHANNELS]; /**< relay states as requested by FMU */
bool arm_ok; /**< FMU allows full arming */
bool vector_flight_mode_ok; /**< FMU aquired a valid position lock, ready for pos control */
bool manual_override_ok; /**< if true, IO performs a direct manual override */
};
/**
@ -82,7 +85,12 @@ struct px4io_config {
uint16_t f2i_config_magic;
#define F2I_CONFIG_MAGIC 0x6366
/* XXX currently nothing here */
uint8_t rc_map[4]; /**< channel ordering of roll, pitch, yaw, throttle */
uint16_t rc_min[4]; /**< min value for each channel */
uint16_t rc_trim[4]; /**< trim value for each channel */
uint16_t rc_max[4]; /**< max value for each channel */
int8_t rc_rev[4]; /**< rev value for each channel */
uint16_t rc_dz[4]; /**< dz value for each channel */
};
/**

2
apps/px4io/px4io.c
View File

@ -66,6 +66,8 @@ int user_start(int argc, char *argv[])
/* reset all to zero */
memset(&system_state, 0, sizeof(system_state));
/* default to 50 Hz PWM outputs */
system_state.servo_rate = 50;
/* configure the high-resolution time/callout interface */
hrt_init();

68
apps/px4io/px4io.h
View File

@ -70,43 +70,89 @@ struct sys_state_s {
bool armed; /* IO armed */
bool arm_ok; /* FMU says OK to arm */
uint16_t servo_rate; /* output rate of servos in Hz */
/*
/**
* Remote control input(s) channel mappings
*/
uint8_t rc_map[4];
/**
* Remote control channel attributes
*/
uint16_t rc_min[4];
uint16_t rc_trim[4];
uint16_t rc_max[4];
int16_t rc_rev[4];
uint16_t rc_dz[4];
/**
* Data from the remote control input(s)
*/
unsigned rc_channels;
uint16_t rc_channel_data[PX4IO_INPUT_CHANNELS];
uint64_t rc_channels_timestamp;
/*
/**
* Control signals from FMU.
*/
uint16_t fmu_channel_data[PX4IO_CONTROL_CHANNELS];
/*
/**
* Mixed servo outputs
*/
uint16_t servos[IO_SERVO_COUNT];
/*
/**
* Relay controls
*/
bool relays[PX4IO_RELAY_CHANNELS];
/*
* If true, we are using the FMU controls.
/**
* If true, we are using the FMU controls, else RC input if available.
*/
bool mixer_use_fmu;
bool mixer_manual_override;
/*
/**
* If true, FMU input is available.
*/
bool mixer_fmu_available;
/**
* If true, state that should be reported to FMU has been updated.
*/
bool fmu_report_due;
/*
* If true, new control data from the FMU has been received.
/**
* Last FMU receive time, in microseconds since system boot
*/
bool fmu_data_received;
uint64_t fmu_data_received_time;
/**
* Current serial interface mode, per the serial_rx_mode parameter
* in the config packet.
*/
uint8_t serial_rx_mode;
/**
* If true, the RC signal has been lost for more than a timeout interval
*/
bool rc_lost;
/**
* If true, the connection to FMU has been lost for more than a timeout interval
*/
bool fmu_lost;
/**
* If true, FMU is ready for autonomous position control. Only used for LED indication
*/
bool vector_flight_mode_ok;
/**
* If true, IO performs an on-board manual override with the RC channel values
*/
bool manual_override_ok;
/*
* Measured battery voltage in mV

43
apps/px4io/safety.c
View File

@ -58,20 +58,27 @@ static struct hrt_call failsafe_call;
* Count the number of times in a row that we see the arming button
* held down.
*/
static unsigned counter;
static unsigned counter = 0;
/*
* Define the various LED flash sequences for each system state.
*/
#define LED_PATTERN_SAFE 0xffff // always on
#define LED_PATTERN_FMU_ARMED 0x4444 // slow blinking
#define LED_PATTERN_IO_ARMED 0x5555 // fast blinking
#define LED_PATTERN_IO_FMU_ARMED 0x5050 // long off then double blink
#define LED_PATTERN_SAFE 0xffff /**< always on */
#define LED_PATTERN_VECTOR_FLIGHT_MODE_OK 0xFFFE /**< always on with short break */
#define LED_PATTERN_FMU_ARMED 0x4444 /**< slow blinking */
#define LED_PATTERN_IO_ARMED 0x5555 /**< fast blinking */
#define LED_PATTERN_IO_FMU_ARMED 0x5050 /**< long off then double blink */
static unsigned blink_counter = 0;
/*
* IMPORTANT: The arming state machine critically
* depends on using the same threshold
* for arming and disarming. Since disarming
* is quite deadly for the system, a similar
* length can be justified.
*/
#define ARM_COUNTER_THRESHOLD 10
#define DISARM_COUNTER_THRESHOLD 2
static bool safety_button_pressed;
@ -101,12 +108,16 @@ safety_check_button(void *arg)
*/
safety_button_pressed = BUTTON_SAFETY;
if (safety_button_pressed) {
//printf("Pressed, Arm counter: %d, Disarm counter: %d\n", arm_counter, disarm_counter);
}
/* Keep pressed for a while to arm */
/*
* Keep pressed for a while to arm.
*
* Note that the counting sequence has to be same length
* for arming / disarming in order to end up as proper
* state machine, keep ARM_COUNTER_THRESHOLD the same
* length in all cases of the if/else struct below.
*/
if (safety_button_pressed && !system_state.armed) {
if (counter < ARM_COUNTER_THRESHOLD) {
counter++;
@ -120,10 +131,11 @@ safety_check_button(void *arg)
/* Disarm quickly */
} else if (safety_button_pressed && system_state.armed) {
if (counter < DISARM_COUNTER_THRESHOLD) {
if (counter < ARM_COUNTER_THRESHOLD) {
counter++;
} else if (counter == DISARM_COUNTER_THRESHOLD) {
} else if (counter == ARM_COUNTER_THRESHOLD) {
/* change to disarmed state and notify the FMU */
system_state.armed = false;
counter++;
@ -147,6 +159,9 @@ safety_check_button(void *arg)
} else if (system_state.arm_ok) {
pattern = LED_PATTERN_FMU_ARMED;
} else if (system_state.vector_flight_mode_ok) {
pattern = LED_PATTERN_VECTOR_FLIGHT_MODE_OK;
}
/* Turn the LED on if we have a 1 at the current bit position */
@ -173,7 +188,7 @@ failsafe_blink(void *arg)
static bool failsafe = false;
/* blink the failsafe LED if we don't have FMU input */
if (!system_state.mixer_use_fmu) {
if (!system_state.mixer_fmu_available) {
failsafe = !failsafe;
} else {

3
apps/px4io/sbus.c
View File

@ -88,6 +88,7 @@ sbus_init(const char *device)
last_rx_time = hrt_absolute_time();
debug("S.Bus: ready");
} else {
debug("S.Bus: open failed");
}
@ -209,7 +210,7 @@ sbus_decode(hrt_abstime frame_time)
/* if the failsafe or connection lost bit is set, we consider the frame invalid */
if ((frame[23] & (1 << 2)) && /* signal lost */
(frame[23] & (1 << 3))) { /* failsafe */
(frame[23] & (1 << 3))) { /* failsafe */
/* actively announce signal loss */
system_state.rc_channels = 0;

69
apps/sensors/sensor_params.c
View File

@ -69,58 +69,86 @@ PARAM_DEFINE_FLOAT(RC1_TRIM, 1500.0f);
PARAM_DEFINE_FLOAT(RC1_MAX, 2000.0f);
PARAM_DEFINE_FLOAT(RC1_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC1_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC1_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC2_MIN, 1000);
PARAM_DEFINE_FLOAT(RC2_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC2_MAX, 2000);
PARAM_DEFINE_FLOAT(RC2_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC2_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC2_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC3_MIN, 1000);
PARAM_DEFINE_FLOAT(RC3_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC3_MAX, 2000);
PARAM_DEFINE_FLOAT(RC3_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC3_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC3_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC4_MIN, 1000);
PARAM_DEFINE_FLOAT(RC4_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC4_MAX, 2000);
PARAM_DEFINE_FLOAT(RC4_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC4_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC4_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC5_MIN, 1000);
PARAM_DEFINE_FLOAT(RC5_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC5_MAX, 2000);
PARAM_DEFINE_FLOAT(RC5_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC5_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC5_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC6_MIN, 1000);
PARAM_DEFINE_FLOAT(RC6_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC6_MAX, 2000);
PARAM_DEFINE_FLOAT(RC6_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC6_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC6_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC7_MIN, 1000);
PARAM_DEFINE_FLOAT(RC7_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC7_MAX, 2000);
PARAM_DEFINE_FLOAT(RC7_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC7_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC7_EXP, 0.0f);
PARAM_DEFINE_FLOAT(RC8_MIN, 1000);
PARAM_DEFINE_FLOAT(RC8_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC8_MAX, 2000);
PARAM_DEFINE_FLOAT(RC8_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC8_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC8_EXP, 0.0f);
PARAM_DEFINE_INT32(RC_TYPE, 1); // 1 = FUTABA
PARAM_DEFINE_FLOAT(RC9_MIN, 1000);
PARAM_DEFINE_FLOAT(RC9_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC9_MAX, 2000);
PARAM_DEFINE_FLOAT(RC9_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC9_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC10_MIN, 1000);
PARAM_DEFINE_FLOAT(RC10_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC10_MAX, 2000);
PARAM_DEFINE_FLOAT(RC10_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC10_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC11_MIN, 1000);
PARAM_DEFINE_FLOAT(RC11_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC11_MAX, 2000);
PARAM_DEFINE_FLOAT(RC11_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC11_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC12_MIN, 1000);
PARAM_DEFINE_FLOAT(RC12_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC12_MAX, 2000);
PARAM_DEFINE_FLOAT(RC12_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC12_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC13_MIN, 1000);
PARAM_DEFINE_FLOAT(RC13_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC13_MAX, 2000);
PARAM_DEFINE_FLOAT(RC13_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC13_DZ, 0.0f);
PARAM_DEFINE_FLOAT(RC14_MIN, 1000);
PARAM_DEFINE_FLOAT(RC14_TRIM, 1500);
PARAM_DEFINE_FLOAT(RC14_MAX, 2000);
PARAM_DEFINE_FLOAT(RC14_REV, 1.0f);
PARAM_DEFINE_FLOAT(RC14_DZ, 0.0f);
PARAM_DEFINE_INT32(RC_TYPE, 1); /** 1 = FUTABA, 2 = Spektrum, 3 = Graupner HoTT, 4 = Turnigy 9x */
/* default is conversion factor for the PX4IO / PX4IOAR board, the factor for PX4FMU standalone is different */
PARAM_DEFINE_FLOAT(BAT_V_SCALING, (3.3f * 52.0f / 5.0f / 4095.0f));
@ -129,12 +157,23 @@ PARAM_DEFINE_INT32(RC_MAP_ROLL, 1);
PARAM_DEFINE_INT32(RC_MAP_PITCH, 2);
PARAM_DEFINE_INT32(RC_MAP_THROTTLE, 3);
PARAM_DEFINE_INT32(RC_MAP_YAW, 4);
PARAM_DEFINE_INT32(RC_MAP_MODE_SW, 5);
PARAM_DEFINE_INT32(RC_MAP_AUX1, 6);
PARAM_DEFINE_INT32(RC_MAP_AUX2, 7);
PARAM_DEFINE_INT32(RC_MAP_AUX3, 8);
PARAM_DEFINE_INT32(RC_MAP_OVER_SW, 5);
PARAM_DEFINE_INT32(RC_MAP_MODE_SW, 6);
PARAM_DEFINE_INT32(RC_MAP_MAN_SW, 0);
PARAM_DEFINE_INT32(RC_MAP_SAS_SW, 0);
PARAM_DEFINE_INT32(RC_MAP_RTL_SW, 0);
PARAM_DEFINE_INT32(RC_MAP_OFFB_SW, 0);
PARAM_DEFINE_INT32(RC_MAP_FLAPS, 0);
PARAM_DEFINE_INT32(RC_MAP_AUX1, 0); /**< default function: camera yaw / azimuth */
PARAM_DEFINE_INT32(RC_MAP_AUX2, 0); /**< default function: camera pitch / tilt */
PARAM_DEFINE_INT32(RC_MAP_AUX3, 0); /**< default function: camera trigger */
PARAM_DEFINE_INT32(RC_MAP_AUX4, 0); /**< default function: camera roll */
PARAM_DEFINE_INT32(RC_MAP_AUX5, 0); /**< default function: payload drop */
PARAM_DEFINE_FLOAT(RC_SCALE_ROLL, 0.4f);
PARAM_DEFINE_FLOAT(RC_SCALE_PITCH, 0.4f);
PARAM_DEFINE_FLOAT(RC_SCALE_YAW, 3.0f);
PARAM_DEFINE_FLOAT(RC_SCALE_YAW, 1.0f);

309
apps/sensors/sensors.cpp
View File

@ -96,6 +96,8 @@
#define PPM_INPUT_TIMEOUT_INTERVAL 50000 /**< 50 ms timeout / 20 Hz */
#define limit_minus_one_to_one(arg) (arg < -1.0f) ? -1.0f : ((arg > 1.0f) ? 1.0f : arg)
/**
* Sensor app start / stop handling function
*
@ -124,7 +126,7 @@ public:
int start();
private:
static const unsigned _rc_max_chan_count = 8; /**< maximum number of r/c channels we handle */
static const unsigned _rc_max_chan_count = RC_CHANNELS_MAX; /**< maximum number of r/c channels we handle */
#if CONFIG_HRT_PPM
hrt_abstime _ppm_last_valid; /**< last time we got a valid ppm signal */
@ -170,7 +172,7 @@ private:
float max[_rc_max_chan_count];
float rev[_rc_max_chan_count];
float dz[_rc_max_chan_count];
float ex[_rc_max_chan_count];
// float ex[_rc_max_chan_count];
float scaling_factor[_rc_max_chan_count];
float gyro_offset[3];
@ -185,11 +187,27 @@ private:
int rc_map_pitch;
int rc_map_yaw;
int rc_map_throttle;
int rc_map_mode_sw;
int rc_map_manual_override_sw;
int rc_map_auto_mode_sw;
int rc_map_manual_mode_sw;
int rc_map_sas_mode_sw;
int rc_map_rtl_sw;
int rc_map_offboard_ctrl_mode_sw;
int rc_map_flaps;
int rc_map_aux1;
int rc_map_aux2;
int rc_map_aux3;
int rc_map_aux4;
int rc_map_aux5;
float rc_scale_roll;
float rc_scale_pitch;
float rc_scale_yaw;
float rc_scale_flaps;
float battery_voltage_scaling;
} _parameters; /**< local copies of interesting parameters */
@ -200,9 +218,11 @@ private:
param_t max[_rc_max_chan_count];
param_t rev[_rc_max_chan_count];
param_t dz[_rc_max_chan_count];
param_t ex[_rc_max_chan_count];
// param_t ex[_rc_max_chan_count];
param_t rc_type;
param_t rc_demix;
param_t gyro_offset[3];
param_t accel_offset[3];
param_t accel_scale[3];
@ -213,11 +233,27 @@ private:
param_t rc_map_pitch;
param_t rc_map_yaw;
param_t rc_map_throttle;
param_t rc_map_mode_sw;
param_t rc_map_manual_override_sw;
param_t rc_map_auto_mode_sw;
param_t rc_map_manual_mode_sw;
param_t rc_map_sas_mode_sw;
param_t rc_map_rtl_sw;
param_t rc_map_offboard_ctrl_mode_sw;
param_t rc_map_flaps;
param_t rc_map_aux1;
param_t rc_map_aux2;
param_t rc_map_aux3;
param_t rc_map_aux4;
param_t rc_map_aux5;
param_t rc_scale_roll;
param_t rc_scale_pitch;
param_t rc_scale_yaw;
param_t rc_scale_flaps;
param_t battery_voltage_scaling;
} _parameter_handles; /**< handles for interesting parameters */
@ -381,22 +417,38 @@ Sensors::Sensors() :
sprintf(nbuf, "RC%d_DZ", i + 1);
_parameter_handles.dz[i] = param_find(nbuf);
/* channel exponential gain */
sprintf(nbuf, "RC%d_EXP", i + 1);
_parameter_handles.ex[i] = param_find(nbuf);
}
_parameter_handles.rc_type = param_find("RC_TYPE");
/* mandatory input switched, mapped to channels 1-4 per default */
_parameter_handles.rc_map_roll = param_find("RC_MAP_ROLL");
_parameter_handles.rc_map_pitch = param_find("RC_MAP_PITCH");
_parameter_handles.rc_map_yaw = param_find("RC_MAP_YAW");
_parameter_handles.rc_map_throttle = param_find("RC_MAP_THROTTLE");
_parameter_handles.rc_map_mode_sw = param_find("RC_MAP_MODE_SW");
/* mandatory mode switches, mapped to channel 5 and 6 per default */
_parameter_handles.rc_map_manual_override_sw = param_find("RC_MAP_OVER_SW");
_parameter_handles.rc_map_auto_mode_sw = param_find("RC_MAP_MODE_SW");
_parameter_handles.rc_map_flaps = param_find("RC_MAP_FLAPS");
/* optional mode switches, not mapped per default */
_parameter_handles.rc_map_manual_mode_sw = param_find("RC_MAP_MAN_SW");
_parameter_handles.rc_map_sas_mode_sw = param_find("RC_MAP_SAS_SW");
_parameter_handles.rc_map_rtl_sw = param_find("RC_MAP_RTL_SW");
_parameter_handles.rc_map_offboard_ctrl_mode_sw = param_find("RC_MAP_OFFB_SW");
_parameter_handles.rc_map_aux1 = param_find("RC_MAP_AUX1");
_parameter_handles.rc_map_aux2 = param_find("RC_MAP_AUX2");
_parameter_handles.rc_map_aux3 = param_find("RC_MAP_AUX3");
_parameter_handles.rc_map_aux4 = param_find("RC_MAP_AUX4");
_parameter_handles.rc_map_aux5 = param_find("RC_MAP_AUX5");
_parameter_handles.rc_scale_roll = param_find("RC_SCALE_ROLL");
_parameter_handles.rc_scale_pitch = param_find("RC_SCALE_PITCH");
_parameter_handles.rc_scale_yaw = param_find("RC_SCALE_YAW");
_parameter_handles.rc_scale_flaps = param_find("RC_SCALE_FLAPS");
/* gyro offsets */
_parameter_handles.gyro_offset[0] = param_find("SENS_GYRO_XOFF");
@ -453,10 +505,10 @@ Sensors::~Sensors()
int
Sensors::parameters_update()
{
const unsigned int nchans = 8;
bool rc_valid = true;
/* rc values */
for (unsigned int i = 0; i < nchans; i++) {
for (unsigned int i = 0; i < RC_CHANNELS_MAX; i++) {
if (param_get(_parameter_handles.min[i], &(_parameters.min[i])) != OK) {
warnx("Failed getting min for chan %d", i);
@ -473,25 +525,24 @@ Sensors::parameters_update()
if (param_get(_parameter_handles.dz[i], &(_parameters.dz[i])) != OK) {
warnx("Failed getting dead zone for chan %d", i);
}
if (param_get(_parameter_handles.ex[i], &(_parameters.ex[i])) != OK) {
warnx("Failed getting exponential gain for chan %d", i);
}
_parameters.scaling_factor[i] = (1.0f / ((_parameters.max[i] - _parameters.min[i]) / 2.0f) * _parameters.rev[i]);
/* handle blowup in the scaling factor calculation */
if (isnan(_parameters.scaling_factor[i]) || isinf(_parameters.scaling_factor[i])) {
if (!isfinite(_parameters.scaling_factor[i]) ||
_parameters.scaling_factor[i] * _parameters.rev[i] < 0.000001f ||
_parameters.scaling_factor[i] * _parameters.rev[i] > 0.2f) {
/* scaling factors do not make sense, lock them down */
_parameters.scaling_factor[i] = 0;
rc_valid = false;
}
}
/* update RC function mappings */
_rc.function[0] = _parameters.rc_map_throttle - 1;
_rc.function[1] = _parameters.rc_map_roll - 1;
_rc.function[2] = _parameters.rc_map_pitch - 1;
_rc.function[3] = _parameters.rc_map_yaw - 1;
_rc.function[4] = _parameters.rc_map_mode_sw - 1;
/* handle wrong values */
if (!rc_valid)
warnx("WARNING WARNING WARNING\n\nRC CALIBRATION NOT SANE!\n\n");
/* remote control type */
if (param_get(_parameter_handles.rc_type, &(_parameters.rc_type)) != OK) {
@ -511,8 +562,44 @@ Sensors::parameters_update()
if (param_get(_parameter_handles.rc_map_throttle, &(_parameters.rc_map_throttle)) != OK) {
warnx("Failed getting throttle chan index");
}
if (param_get(_parameter_handles.rc_map_mode_sw, &(_parameters.rc_map_mode_sw)) != OK) {
warnx("Failed getting mode sw chan index");
if (param_get(_parameter_handles.rc_map_manual_override_sw, &(_parameters.rc_map_manual_override_sw)) != OK) {
warnx("Failed getting override sw chan index");
}
if (param_get(_parameter_handles.rc_map_auto_mode_sw, &(_parameters.rc_map_auto_mode_sw)) != OK) {
warnx("Failed getting auto mode sw chan index");
}
if (param_get(_parameter_handles.rc_map_flaps, &(_parameters.rc_map_flaps)) != OK) {
warnx("Failed getting flaps chan index");
}
if (param_get(_parameter_handles.rc_map_manual_mode_sw, &(_parameters.rc_map_manual_mode_sw)) != OK) {
warnx("Failed getting manual mode sw chan index");
}
if (param_get(_parameter_handles.rc_map_rtl_sw, &(_parameters.rc_map_rtl_sw)) != OK) {
warnx("Failed getting rtl sw chan index");
}
if (param_get(_parameter_handles.rc_map_sas_mode_sw, &(_parameters.rc_map_sas_mode_sw)) != OK) {
warnx("Failed getting sas mode sw chan index");
}
if (param_get(_parameter_handles.rc_map_offboard_ctrl_mode_sw, &(_parameters.rc_map_offboard_ctrl_mode_sw)) != OK) {
warnx("Failed getting offboard control mode sw chan index");
}
if (param_get(_parameter_handles.rc_map_aux1, &(_parameters.rc_map_aux1)) != OK) {
warnx("Failed getting mode aux 1 index");
}
if (param_get(_parameter_handles.rc_map_aux2, &(_parameters.rc_map_aux2)) != OK) {
warnx("Failed getting mode aux 2 index");
}
if (param_get(_parameter_handles.rc_map_aux3, &(_parameters.rc_map_aux3)) != OK) {
warnx("Failed getting mode aux 3 index");
}
if (param_get(_parameter_handles.rc_map_aux4, &(_parameters.rc_map_aux4)) != OK) {
warnx("Failed getting mode aux 4 index");
}
if (param_get(_parameter_handles.rc_map_aux5, &(_parameters.rc_map_aux5)) != OK) {
warnx("Failed getting mode aux 5 index");
}
if (param_get(_parameter_handles.rc_scale_roll, &(_parameters.rc_scale_roll)) != OK) {
@ -524,6 +611,31 @@ Sensors::parameters_update()
if (param_get(_parameter_handles.rc_scale_yaw, &(_parameters.rc_scale_yaw)) != OK) {
warnx("Failed getting rc scaling for yaw");
}
if (param_get(_parameter_handles.rc_scale_flaps, &(_parameters.rc_scale_flaps)) != OK) {
warnx("Failed getting rc scaling for flaps");
}
/* update RC function mappings */
_rc.function[THROTTLE] = _parameters.rc_map_throttle - 1;
_rc.function[ROLL] = _parameters.rc_map_roll - 1;
_rc.function[PITCH] = _parameters.rc_map_pitch - 1;
_rc.function[YAW] = _parameters.rc_map_yaw - 1;
_rc.function[OVERRIDE] = _parameters.rc_map_manual_override_sw - 1;
_rc.function[AUTO_MODE] = _parameters.rc_map_auto_mode_sw - 1;
_rc.function[FLAPS] = _parameters.rc_map_flaps - 1;
_rc.function[MANUAL_MODE] = _parameters.rc_map_manual_mode_sw - 1;
_rc.function[RTL] = _parameters.rc_map_rtl_sw - 1;
_rc.function[SAS_MODE] = _parameters.rc_map_sas_mode_sw - 1;
_rc.function[OFFBOARD_MODE] = _parameters.rc_map_offboard_ctrl_mode_sw - 1;
_rc.function[AUX_1] = _parameters.rc_map_aux1 - 1;
_rc.function[AUX_2] = _parameters.rc_map_aux2 - 1;
_rc.function[AUX_3] = _parameters.rc_map_aux3 - 1;
_rc.function[AUX_4] = _parameters.rc_map_aux4 - 1;
_rc.function[AUX_5] = _parameters.rc_map_aux5 - 1;
/* gyro offsets */
param_get(_parameter_handles.gyro_offset[0], &(_parameters.gyro_offset[0]));
@ -917,8 +1029,23 @@ Sensors::ppm_poll()
struct manual_control_setpoint_s manual_control;
/* get a copy first, to prevent altering values */
orb_copy(ORB_ID(manual_control_setpoint), _manual_control_sub, &manual_control);
/* initialize to default values */
manual_control.roll = NAN;
manual_control.pitch = NAN;
manual_control.yaw = NAN;
manual_control.throttle = NAN;
manual_control.manual_mode_switch = NAN;
manual_control.manual_sas_switch = NAN;
manual_control.return_to_launch_switch = NAN;
manual_control.auto_offboard_input_switch = NAN;
manual_control.flaps = NAN;
manual_control.aux1 = NAN;
manual_control.aux2 = NAN;
manual_control.aux3 = NAN;
manual_control.aux4 = NAN;
manual_control.aux5 = NAN;
/* require at least four channels to consider the signal valid */
if (rc_input.channel_count < 4)
@ -966,44 +1093,99 @@ Sensors::ppm_poll()
manual_control.timestamp = rc_input.timestamp;
/* roll input - rolling right is stick-wise and rotation-wise positive */
manual_control.roll = _rc.chan[_rc.function[ROLL]].scaled;
if (manual_control.roll < -1.0f) manual_control.roll = -1.0f;
if (manual_control.roll > 1.0f) manual_control.roll = 1.0f;
if (!isnan(_parameters.rc_scale_roll) || !isinf(_parameters.rc_scale_roll)) {
manual_control.roll *= _parameters.rc_scale_roll;
}
manual_control.roll = limit_minus_one_to_one(_rc.chan[_rc.function[ROLL]].scaled);
/*
* pitch input - stick down is negative, but stick down is pitching up (pos) in NED,
* so reverse sign.
*/
manual_control.pitch = -1.0f * _rc.chan[_rc.function[PITCH]].scaled;
if (manual_control.pitch < -1.0f) manual_control.pitch = -1.0f;
if (manual_control.pitch > 1.0f) manual_control.pitch = 1.0f;
if (!isnan(_parameters.rc_scale_pitch) || !isinf(_parameters.rc_scale_pitch)) {
manual_control.pitch *= _parameters.rc_scale_pitch;
}
manual_control.pitch = limit_minus_one_to_one(-1.0f * _rc.chan[_rc.function[PITCH]].scaled);
/* yaw input - stick right is positive and positive rotation */
manual_control.yaw = _rc.chan[_rc.function[YAW]].scaled * _parameters.rc_scale_yaw;
if (manual_control.yaw < -1.0f) manual_control.yaw = -1.0f;
if (manual_control.yaw > 1.0f) manual_control.yaw = 1.0f;
if (!isnan(_parameters.rc_scale_yaw) || !isinf(_parameters.rc_scale_yaw)) {
manual_control.yaw *= _parameters.rc_scale_yaw;
}
manual_control.yaw = limit_minus_one_to_one(_rc.chan[_rc.function[YAW]].scaled);
/* throttle input */
manual_control.throttle = _rc.chan[_rc.function[THROTTLE]].scaled;
if (manual_control.throttle < 0.0f) manual_control.throttle = 0.0f;
if (manual_control.throttle > 1.0f) manual_control.throttle = 1.0f;
/* mode switch input */
manual_control.override_mode_switch = _rc.chan[_rc.function[OVERRIDE]].scaled;
if (manual_control.override_mode_switch < -1.0f) manual_control.override_mode_switch = -1.0f;
if (manual_control.override_mode_switch > 1.0f) manual_control.override_mode_switch = 1.0f;
/* scale output */
if (isfinite(_parameters.rc_scale_roll) && _parameters.rc_scale_roll > 0.0f) {
manual_control.roll *= _parameters.rc_scale_roll;
}
orb_publish(ORB_ID(rc_channels), _rc_pub, &_rc);
orb_publish(ORB_ID(manual_control_setpoint), _manual_control_pub, &manual_control);
if (isfinite(_parameters.rc_scale_pitch) && _parameters.rc_scale_pitch > 0.0f) {
manual_control.pitch *= _parameters.rc_scale_pitch;
}
if (isfinite(_parameters.rc_scale_yaw) && _parameters.rc_scale_yaw > 0.0f) {
manual_control.yaw *= _parameters.rc_scale_yaw;
}
/* override switch input */
manual_control.manual_override_switch = limit_minus_one_to_one(_rc.chan[_rc.function[OVERRIDE]].scaled);
/* mode switch input */
manual_control.auto_mode_switch = limit_minus_one_to_one(_rc.chan[_rc.function[AUTO_MODE]].scaled);
/* flaps */
if (_rc.function[FLAPS] >= 0) {
manual_control.flaps = limit_minus_one_to_one(_rc.chan[_rc.function[FLAPS]].scaled);
if (isfinite(_parameters.rc_scale_flaps) && _parameters.rc_scale_flaps > 0.0f) {
manual_control.flaps *= _parameters.rc_scale_flaps;
}
}
if (_rc.function[MANUAL_MODE] >= 0) {
manual_control.manual_mode_switch = limit_minus_one_to_one(_rc.chan[_rc.function[MANUAL_MODE]].scaled);
}
if (_rc.function[SAS_MODE] >= 0) {
manual_control.manual_sas_switch = limit_minus_one_to_one(_rc.chan[_rc.function[SAS_MODE]].scaled);
}
if (_rc.function[RTL] >= 0) {
manual_control.return_to_launch_switch = limit_minus_one_to_one(_rc.chan[_rc.function[RTL]].scaled);
}
if (_rc.function[OFFBOARD_MODE] >= 0) {
manual_control.auto_offboard_input_switch = limit_minus_one_to_one(_rc.chan[_rc.function[OFFBOARD_MODE]].scaled);
}
/* aux functions, only assign if valid mapping is present */
if (_rc.function[AUX_1] >= 0) {
manual_control.aux1 = limit_minus_one_to_one(_rc.chan[_rc.function[AUX_1]].scaled);
}
if (_rc.function[AUX_2] >= 0) {
manual_control.aux2 = limit_minus_one_to_one(_rc.chan[_rc.function[AUX_2]].scaled);
}
if (_rc.function[AUX_3] >= 0) {
manual_control.aux3 = limit_minus_one_to_one(_rc.chan[_rc.function[AUX_3]].scaled);
}
if (_rc.function[AUX_4] >= 0) {
manual_control.aux4 = limit_minus_one_to_one(_rc.chan[_rc.function[AUX_4]].scaled);
}
if (_rc.function[AUX_5] >= 0) {
manual_control.aux5 = limit_minus_one_to_one(_rc.chan[_rc.function[AUX_5]].scaled);
}
/* check if ready for publishing */
if (_rc_pub > 0) {
orb_publish(ORB_ID(rc_channels), _rc_pub, &_rc);
} else {
/* advertise the rc topic */
_rc_pub = orb_advertise(ORB_ID(rc_channels), &_rc);
}
/* check if ready for publishing */
if (_manual_control_pub > 0) {
orb_publish(ORB_ID(manual_control_setpoint), _manual_control_pub, &manual_control);
} else {
_manual_control_pub = orb_advertise(ORB_ID(manual_control_setpoint), &manual_control);
}
}
}
@ -1051,7 +1233,7 @@ Sensors::task_main()
struct sensor_combined_s raw;
memset(&raw, 0, sizeof(raw));
raw.timestamp = hrt_absolute_time();
raw.adc_voltage_v[0] = 0.9f;
raw.adc_voltage_v[0] = 0.0f;
raw.adc_voltage_v[1] = 0.0f;
raw.adc_voltage_v[2] = 0.0f;
raw.adc_voltage_v[3] = 0.0f;
@ -1070,27 +1252,6 @@ Sensors::task_main()
/* advertise the sensor_combined topic and make the initial publication */
_sensor_pub = orb_advertise(ORB_ID(sensor_combined), &raw);
/* advertise the manual_control topic */
struct manual_control_setpoint_s manual_control;
manual_control.mode = MANUAL_CONTROL_MODE_ATT_YAW_POS;
manual_control.roll = 0.0f;
manual_control.pitch = 0.0f;
manual_control.yaw = 0.0f;
manual_control.throttle = 0.0f;
manual_control.aux1_cam_pan_flaps = 0.0f;
manual_control.aux2_cam_tilt = 0.0f;
manual_control.aux3_cam_zoom = 0.0f;
manual_control.aux4_cam_roll = 0.0f;
_manual_control_pub = orb_advertise(ORB_ID(manual_control_setpoint), &manual_control);
/* advertise the rc topic */
{
struct rc_channels_s rc;
memset(&rc, 0, sizeof(rc));
_rc_pub = orb_advertise(ORB_ID(rc_channels), &rc);
}
/* wakeup source(s) */
struct pollfd fds[1];

96
apps/systemlib/conversions.c
View File

@ -59,8 +59,100 @@ int16_t_from_bytes(uint8_t bytes[])
return u.w;
}
void rot2quat(const float R[9], float Q[4])
{
float q0_2;
float q1_2;
float q2_2;
float q3_2;
int32_t idx;
/* conversion of rotation matrix to quaternion
* choose the largest component to begin with */
q0_2 = (((1.0F + R[0]) + R[4]) + R[8]) / 4.0F;
q1_2 = (((1.0F + R[0]) - R[4]) - R[8]) / 4.0F;
q2_2 = (((1.0F - R[0]) + R[4]) - R[8]) / 4.0F;
q3_2 = (((1.0F - R[0]) - R[4]) + R[8]) / 4.0F;
idx = 0;
if (q0_2 < q1_2) {
q0_2 = q1_2;
idx = 1;
}
if (q0_2 < q2_2) {
q0_2 = q2_2;
idx = 2;
}
if (q0_2 < q3_2) {
q0_2 = q3_2;
idx = 3;
}
q0_2 = sqrtf(q0_2);
/* solve for the remaining three components */
if (idx == 0) {
q1_2 = q0_2;
q2_2 = (R[5] - R[7]) / 4.0F / q0_2;
q3_2 = (R[6] - R[2]) / 4.0F / q0_2;
q0_2 = (R[1] - R[3]) / 4.0F / q0_2;
} else if (idx == 1) {
q2_2 = q0_2;
q1_2 = (R[5] - R[7]) / 4.0F / q0_2;
q3_2 = (R[3] + R[1]) / 4.0F / q0_2;
q0_2 = (R[6] + R[2]) / 4.0F / q0_2;
} else if (idx == 2) {
q3_2 = q0_2;
q1_2 = (R[6] - R[2]) / 4.0F / q0_2;
q2_2 = (R[3] + R[1]) / 4.0F / q0_2;
q0_2 = (R[7] + R[5]) / 4.0F / q0_2;
} else {
q1_2 = (R[1] - R[3]) / 4.0F / q0_2;
q2_2 = (R[6] + R[2]) / 4.0F / q0_2;
q3_2 = (R[7] + R[5]) / 4.0F / q0_2;
}
/* return values */
Q[0] = q1_2;
Q[1] = q2_2;
Q[2] = q3_2;
Q[3] = q0_2;
}
void quat2rot(const float Q[4], float R[9])
{
float q0_2;
float q1_2;
float q2_2;
float q3_2;
memset(&R[0], 0, 9U * sizeof(float));
q0_2 = Q[0] * Q[0];
q1_2 = Q[1] * Q[1];
q2_2 = Q[2] * Q[2];
q3_2 = Q[3] * Q[3];
R[0] = ((q0_2 + q1_2) - q2_2) - q3_2;
R[3] = 2.0F * (Q[1] * Q[2] - Q[0] * Q[3]);
R[6] = 2.0F * (Q[1] * Q[3] + Q[0] * Q[2]);
R[1] = 2.0F * (Q[1] * Q[2] + Q[0] * Q[3]);
R[4] = ((q0_2 + q2_2) - q1_2) - q3_2;
R[7] = 2.0F * (Q[2] * Q[3] - Q[0] * Q[1]);
R[2] = 2.0F * (Q[1] * Q[3] - Q[0] * Q[2]);
R[5] = 2.0F * (Q[2] * Q[3] + Q[0] * Q[1]);
R[8] = ((q0_2 + q3_2) - q1_2) - q2_2;
}
float get_air_density(float static_pressure, float temperature_celsius)
{
return static_pressure/(air_gas_constant * (temperature_celsius + absolute_null_kelvin));
return static_pressure / (air_gas_constant * (temperature_celsius + absolute_null_kelvin));
}

25
apps/systemlib/conversions.h
View File

@ -44,6 +44,8 @@
#include <float.h>
#include <stdint.h>
#define CONSTANTS_ONE_G 9.80665f
__BEGIN_DECLS
/**
@ -56,8 +58,31 @@ __BEGIN_DECLS
*/
__EXPORT int16_t int16_t_from_bytes(uint8_t bytes[]);
/**
* Converts a 3 x 3 rotation matrix to an unit quaternion.
*
* All orientations are expressed in NED frame.
*
* @param R rotation matrix to convert
* @param Q quaternion to write back to
*/
__EXPORT void rot2quat(const float R[9], float Q[4]);
/**
* Converts an unit quaternion to a 3 x 3 rotation matrix.
*
* All orientations are expressed in NED frame.
*
* @param Q quaternion to convert
* @param R rotation matrix to write back to
*/
__EXPORT void quat2rot(const float Q[4], float R[9]);
/**
* Calculates air density.
*
* @param static_pressure ambient pressure in millibar
* @param temperature_celcius air / ambient temperature in celcius
*/
__EXPORT float get_air_density(float static_pressure, float temperature_celsius);

2
apps/systemlib/mixer/mixer_group.cpp
View File

@ -55,6 +55,8 @@
#define debug(fmt, args...) do { } while(0)
//#define debug(fmt, args...) do { printf("[mixer] " fmt "\n", ##args); } while(0)
//#include <debug.h>
//#define debug(fmt, args...) lib_lowprintf(fmt "\n", ##args)
MixerGroup::MixerGroup(ControlCallback control_cb, uintptr_t cb_handle) :
Mixer(control_cb, cb_handle),

4
apps/systemlib/mixer/mixer_multirotor.cpp
View File

@ -217,9 +217,11 @@ unsigned
MultirotorMixer::mix(float *outputs, unsigned space)
{
float roll = get_control(0, 0) * _roll_scale;
//lib_lowprintf("roll: %d, get_control0: %d, %d\n", (int)(roll), (int)(get_control(0, 0)), (int)(_roll_scale));
float pitch = get_control(0, 1) * _pitch_scale;
float yaw = get_control(0, 2) * _yaw_scale;
float thrust = get_control(0, 3);
//lib_lowprintf("thrust: %d, get_control3: %d\n", (int)(thrust), (int)(get_control(0, 3)));
float max = 0.0f;
float fixup_scale;
@ -276,7 +278,7 @@ MultirotorMixer::mix(float *outputs, unsigned space)
if (outputs[i] < _deadband)
outputs[i] = _deadband;
return 0;
return _rotor_count;
}
void

6
apps/systemlib/pid/pid.c
View File

@ -183,3 +183,9 @@ __EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, flo
return pid->last_output;
}
__EXPORT void pid_reset_integral(PID_t *pid)
{
pid->integral = 0;
}

1
apps/systemlib/pid/pid.h
View File

@ -72,6 +72,7 @@ __EXPORT int pid_set_parameters(PID_t *pid, float kp, float ki, float kd, float
//void pid_set(PID_t *pid, float sp);
__EXPORT float pid_calculate(PID_t *pid, float sp, float val, float val_dot, float dt);
__EXPORT void pid_reset_integral(PID_t *pid);
#endif /* PID_H_ */

48
apps/systemlib/scheduling_priorities.h Normal file
View File

@ -0,0 +1,48 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
#pragma once
#include <nuttx/sched.h>
/* SCHED_PRIORITY_MAX */
#define SCHED_PRIORITY_FAST_DRIVER SCHED_PRIORITY_MAX
#define SCHED_PRIORITY_WATCHDOG (SCHED_PRIORITY_MAX - 5)
#define SCHED_PRIORITY_ACTUATOR_OUTPUTS (SCHED_PRIORITY_MAX - 15)
#define SCHED_PRIORITY_ATTITUDE_CONTROL (SCHED_PRIORITY_MAX - 25)
#define SCHED_PRIORITY_SLOW_DRIVER (SCHED_PRIORITY_MAX - 35)
#define SCHED_PRIORITY_POSITION_CONTROL (SCHED_PRIORITY_MAX - 40)
/* SCHED_PRIORITY_DEFAULT */
#define SCHED_PRIORITY_LOGGING (SCHED_PRIORITY_DEFAULT - 10)
#define SCHED_PRIORITY_PARAMS (SCHED_PRIORITY_DEFAULT - 15)
/* SCHED_PRIORITY_IDLE */

2
apps/uORB/topics/actuator_controls_effective.h
View File

@ -32,7 +32,7 @@
****************************************************************************/
/**
* @file actuator_controls.h
* @file actuator_controls_effective.h
*
* Actuator control topics - mixer inputs.
*

5
apps/uORB/topics/actuator_outputs.h
View File

@ -53,8 +53,9 @@
#define NUM_ACTUATOR_OUTPUT_GROUPS 4 /**< for sanity checking */
struct actuator_outputs_s {
uint64_t timestamp;
float output[NUM_ACTUATOR_OUTPUTS];
uint64_t timestamp; /**< output timestamp in us since system boot */
float output[NUM_ACTUATOR_OUTPUTS]; /**< output data, in natural output units */
int noutputs; /**< valid outputs */
};
/* actuator output sets; this list can be expanded as more drivers emerge */

40
apps/uORB/topics/manual_control_setpoint.h
View File

@ -48,29 +48,33 @@
* @{
*/
enum MANUAL_CONTROL_MODE
{
MANUAL_CONTROL_MODE_DIRECT = 0,
MANUAL_CONTROL_MODE_ATT_YAW_RATE = 1,
MANUAL_CONTROL_MODE_ATT_YAW_POS = 2,
MANUAL_CONTROL_MODE_MULTIROTOR_SIMPLE = 3 /**< roll / pitch rotated aligned to the takeoff orientation, throttle stabilized, yaw pos */
};
struct manual_control_setpoint_s {
uint64_t timestamp;
enum MANUAL_CONTROL_MODE mode; /**< The current control inputs mode */
float roll; /**< ailerons roll / roll rate input */
float pitch; /**< elevator / pitch / pitch rate */
float yaw; /**< rudder / yaw rate / yaw */
float throttle; /**< throttle / collective thrust / altitude */
float roll; /**< ailerons roll / roll rate input */
float pitch; /**< elevator / pitch / pitch rate */
float yaw; /**< rudder / yaw rate / yaw */
float throttle; /**< throttle / collective thrust / altitude */
float override_mode_switch;
float manual_override_switch; /**< manual override mode (mandatory) */
float auto_mode_switch; /**< auto mode switch (mandatory) */
float aux1_cam_pan_flaps;
float aux2_cam_tilt;
float aux3_cam_zoom;
float aux4_cam_roll;
/**
* Any of the channels below may not be available and be set to NaN
* to indicate that it does not contain valid data.
*/
float manual_mode_switch; /**< manual mode (man, sas, alt) switch (optional) */
float manual_sas_switch; /**< sas mode (rates / attitude) switch (optional) */
float return_to_launch_switch; /**< return to launch switch (0 = disabled, 1 = enabled) */
float auto_offboard_input_switch; /**< controller setpoint source (0 = onboard, 1 = offboard) */
float flaps; /**< flap position */
float aux1; /**< default function: camera yaw / azimuth */
float aux2; /**< default function: camera pitch / tilt */
float aux3; /**< default function: camera trigger */
float aux4; /**< default function: camera roll */
float aux5; /**< default function: payload drop */
}; /**< manual control inputs */

34
apps/uORB/topics/rc_channels.h
View File

@ -50,6 +50,13 @@
* @{
*/
/**
* The number of RC channel inputs supported.
* Current (Q1/2013) radios support up to 18 channels,
* leaving at a sane value of 14.
*/
#define RC_CHANNELS_MAX 14
/**
* This defines the mapping of the RC functions.
* The value assigned to the specific function corresponds to the entry of
@ -62,14 +69,18 @@ enum RC_CHANNELS_FUNCTION
PITCH = 2,
YAW = 3,
OVERRIDE = 4,
FUNC_0 = 5,
FUNC_1 = 6,
FUNC_2 = 7,
FUNC_3 = 8,
FUNC_4 = 9,
FUNC_5 = 10,
FUNC_6 = 11,
RC_CHANNELS_FUNCTION_MAX = 12
AUTO_MODE = 5,
MANUAL_MODE = 6,
SAS_MODE = 7,
RTL = 8,
OFFBOARD_MODE = 9,
FLAPS = 10,
AUX_1 = 11,
AUX_2 = 12,
AUX_3 = 13,
AUX_4 = 14,
AUX_5 = 15,
RC_CHANNELS_FUNCTION_MAX /**< indicates the number of functions. There can be more functions than RC channels. */
};
struct rc_channels_s {
@ -78,14 +89,13 @@ struct rc_channels_s {
uint64_t timestamp_last_valid; /**< timestamp of last valid RC signal. */
struct {
float scaled; /**< Scaled to -1..1 (throttle: 0..1) */
} chan[RC_CHANNELS_FUNCTION_MAX];
uint8_t chan_count; /**< maximum number of valid channels */
} chan[RC_CHANNELS_MAX];
uint8_t chan_count; /**< number of valid channels */
/*String array to store the names of the functions*/
char function_name[RC_CHANNELS_FUNCTION_MAX][20];
uint8_t function[RC_CHANNELS_FUNCTION_MAX];
int8_t function[RC_CHANNELS_FUNCTION_MAX];
uint8_t rssi; /**< Overall receive signal strength */
bool is_valid; /**< Inputs are valid, no timeout */
}; /**< radio control channels. */
/**

77
apps/uORB/topics/vehicle_command.h
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@ -50,20 +50,77 @@
* @{
*/
enum PX4_CMD {
PX4_CMD_CONTROLLER_SELECTION = 1000,
/**
* Commands for commander app.
*
* Should contain all commands from MAVLink's VEHICLE_CMD ENUM,
* but can contain additional ones.
*/
enum VEHICLE_CMD
{
VEHICLE_CMD_NAV_WAYPOINT=16, /* Navigate to MISSION. |Hold time in decimal seconds. (ignored by fixed wing, time to stay at MISSION for rotary wing)| Acceptance radius in meters (if the sphere with this radius is hit, the MISSION counts as reached)| 0 to pass through the WP, if > 0 radius in meters to pass by WP. Positive value for clockwise orbit, negative value for counter-clockwise orbit. Allows trajectory control.| Desired yaw angle at MISSION (rotary wing)| Latitude| Longitude| Altitude| */
VEHICLE_CMD_NAV_LOITER_UNLIM=17, /* Loiter around this MISSION an unlimited amount of time |Empty| Empty| Radius around MISSION, in meters. If positive loiter clockwise, else counter-clockwise| Desired yaw angle.| Latitude| Longitude| Altitude| */
VEHICLE_CMD_NAV_LOITER_TURNS=18, /* Loiter around this MISSION for X turns |Turns| Empty| Radius around MISSION, in meters. If positive loiter clockwise, else counter-clockwise| Desired yaw angle.| Latitude| Longitude| Altitude| */
VEHICLE_CMD_NAV_LOITER_TIME=19, /* Loiter around this MISSION for X seconds |Seconds (decimal)| Empty| Radius around MISSION, in meters. If positive loiter clockwise, else counter-clockwise| Desired yaw angle.| Latitude| Longitude| Altitude| */
VEHICLE_CMD_NAV_RETURN_TO_LAUNCH=20, /* Return to launch location |Empty| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_NAV_LAND=21, /* Land at location |Empty| Empty| Empty| Desired yaw angle.| Latitude| Longitude| Altitude| */
VEHICLE_CMD_NAV_TAKEOFF=22, /* Takeoff from ground / hand |Minimum pitch (if airspeed sensor present), desired pitch without sensor| Empty| Empty| Yaw angle (if magnetometer present), ignored without magnetometer| Latitude| Longitude| Altitude| */
VEHICLE_CMD_NAV_ROI=80, /* Sets the region of interest (ROI) for a sensor set or the vehicle itself. This can then be used by the vehicles control system to control the vehicle attitude and the attitude of various sensors such as cameras. |Region of intereset mode. (see MAV_ROI enum)| MISSION index/ target ID. (see MAV_ROI enum)| ROI index (allows a vehicle to manage multiple ROI's)| Empty| x the location of the fixed ROI (see MAV_FRAME)| y| z| */
VEHICLE_CMD_NAV_PATHPLANNING=81, /* Control autonomous path planning on the MAV. |0: Disable local obstacle avoidance / local path planning (without resetting map), 1: Enable local path planning, 2: Enable and reset local path planning| 0: Disable full path planning (without resetting map), 1: Enable, 2: Enable and reset map/occupancy grid, 3: Enable and reset planned route, but not occupancy grid| Empty| Yaw angle at goal, in compass degrees, [0..360]| Latitude/X of goal| Longitude/Y of goal| Altitude/Z of goal| */
VEHICLE_CMD_NAV_LAST=95, /* NOP - This command is only used to mark the upper limit of the NAV/ACTION commands in the enumeration |Empty| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_CONDITION_DELAY=112, /* Delay mission state machine. |Delay in seconds (decimal)| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_CONDITION_CHANGE_ALT=113, /* Ascend/descend at rate. Delay mission state machine until desired altitude reached. |Descent / Ascend rate (m/s)| Empty| Empty| Empty| Empty| Empty| Finish Altitude| */
VEHICLE_CMD_CONDITION_DISTANCE=114, /* Delay mission state machine until within desired distance of next NAV point. |Distance (meters)| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_CONDITION_YAW=115, /* Reach a certain target angle. |target angle: [0-360], 0 is north| speed during yaw change:[deg per second]| direction: negative: counter clockwise, positive: clockwise [-1,1]| relative offset or absolute angle: [ 1,0]| Empty| Empty| Empty| */
VEHICLE_CMD_CONDITION_LAST=159, /* NOP - This command is only used to mark the upper limit of the CONDITION commands in the enumeration |Empty| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_SET_MODE=176, /* Set system mode. |Mode, as defined by ENUM MAV_MODE| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_JUMP=177, /* Jump to the desired command in the mission list. Repeat this action only the specified number of times |Sequence number| Repeat count| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_CHANGE_SPEED=178, /* Change speed and/or throttle set points. |Speed type (0=Airspeed, 1=Ground Speed)| Speed (m/s, -1 indicates no change)| Throttle ( Percent, -1 indicates no change)| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_SET_HOME=179, /* Changes the home location either to the current location or a specified location. |Use current (1=use current location, 0=use specified location)| Empty| Empty| Empty| Latitude| Longitude| Altitude| */
VEHICLE_CMD_DO_SET_PARAMETER=180, /* Set a system parameter. Caution! Use of this command requires knowledge of the numeric enumeration value of the parameter. |Parameter number| Parameter value| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_SET_RELAY=181, /* Set a relay to a condition. |Relay number| Setting (1=on, 0=off, others possible depending on system hardware)| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_REPEAT_RELAY=182, /* Cycle a relay on and off for a desired number of cyles with a desired period. |Relay number| Cycle count| Cycle time (seconds, decimal)| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_SET_SERVO=183, /* Set a servo to a desired PWM value. |Servo number| PWM (microseconds, 1000 to 2000 typical)| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_DO_REPEAT_SERVO=184, /* Cycle a between its nominal setting and a desired PWM for a desired number of cycles with a desired period. |Servo number| PWM (microseconds, 1000 to 2000 typical)| Cycle count| Cycle time (seconds)| Empty| Empty| Empty| */
VEHICLE_CMD_DO_CONTROL_VIDEO=200, /* Control onboard camera system. |Camera ID (-1 for all)| Transmission: 0: disabled, 1: enabled compressed, 2: enabled raw| Transmission mode: 0: video stream, >0: single images every n seconds (decimal)| Recording: 0: disabled, 1: enabled compressed, 2: enabled raw| Empty| Empty| Empty| */
VEHICLE_CMD_DO_LAST=240, /* NOP - This command is only used to mark the upper limit of the DO commands in the enumeration |Empty| Empty| Empty| Empty| Empty| Empty| Empty| */
VEHICLE_CMD_PREFLIGHT_CALIBRATION=241, /* Trigger calibration. This command will be only accepted if in pre-flight mode. |Gyro calibration: 0: no, 1: yes| Magnetometer calibration: 0: no, 1: yes| Ground pressure: 0: no, 1: yes| Radio calibration: 0: no, 1: yes| Accelerometer calibration: 0: no, 1: yes| Empty| Empty| */
VEHICLE_CMD_PREFLIGHT_SET_SENSOR_OFFSETS=242, /* Set sensor offsets. This command will be only accepted if in pre-flight mode. |Sensor to adjust the offsets for: 0: gyros, 1: accelerometer, 2: magnetometer, 3: barometer, 4: optical flow| X axis offset (or generic dimension 1), in the sensor's raw units| Y axis offset (or generic dimension 2), in the sensor's raw units| Z axis offset (or generic dimension 3), in the sensor's raw units| Generic dimension 4, in the sensor's raw units| Generic dimension 5, in the sensor's raw units| Generic dimension 6, in the sensor's raw units| */
VEHICLE_CMD_PREFLIGHT_STORAGE=245, /* Request storage of different parameter values and logs. This command will be only accepted if in pre-flight mode. |Parameter storage: 0: READ FROM FLASH/EEPROM, 1: WRITE CURRENT TO FLASH/EEPROM| Mission storage: 0: READ FROM FLASH/EEPROM, 1: WRITE CURRENT TO FLASH/EEPROM| Reserved| Reserved| Empty| Empty| Empty| */
VEHICLE_CMD_PREFLIGHT_REBOOT_SHUTDOWN=246, /* Request the reboot or shutdown of system components. |0: Do nothing for autopilot, 1: Reboot autopilot, 2: Shutdown autopilot.| 0: Do nothing for onboard computer, 1: Reboot onboard computer, 2: Shutdown onboard computer.| Reserved| Reserved| Empty| Empty| Empty| */
VEHICLE_CMD_OVERRIDE_GOTO=252, /* Hold / continue the current action |MAV_GOTO_DO_HOLD: hold MAV_GOTO_DO_CONTINUE: continue with next item in mission plan| MAV_GOTO_HOLD_AT_CURRENT_POSITION: Hold at current position MAV_GOTO_HOLD_AT_SPECIFIED_POSITION: hold at specified position| MAV_FRAME coordinate frame of hold point| Desired yaw angle in degrees| Latitude / X position| Longitude / Y position| Altitude / Z position| */
VEHICLE_CMD_MISSION_START=300, /* start running a mission |first_item: the first mission item to run| last_item: the last mission item to run (after this item is run, the mission ends)| */
VEHICLE_CMD_COMPONENT_ARM_DISARM=400, /* Arms / Disarms a component |1 to arm, 0 to disarm| */
VEHICLE_CMD_ENUM_END=401, /* | */
};
/**
* Commands for commander app.
*
* Should contain all of MAVLink's VEHICLE_CMD_RESULT values
* but can contain additional ones.
*/
enum VEHICLE_CMD_RESULT
{
VEHICLE_CMD_RESULT_ACCEPTED=0, /* Command ACCEPTED and EXECUTED | */
VEHICLE_CMD_RESULT_TEMPORARILY_REJECTED=1, /* Command TEMPORARY REJECTED/DENIED | */
VEHICLE_CMD_RESULT_DENIED=2, /* Command PERMANENTLY DENIED | */
VEHICLE_CMD_RESULT_UNSUPPORTED=3, /* Command UNKNOWN/UNSUPPORTED | */
VEHICLE_CMD_RESULT_FAILED=4, /* Command executed, but failed | */
VEHICLE_CMD_RESULT_ENUM_END=5, /* | */
};
struct vehicle_command_s
{
float param1; /**< Parameter 1, as defined by MAVLink MAV_CMD enum. */
float param2; /**< Parameter 2, as defined by MAVLink MAV_CMD enum. */
float param3; /**< Parameter 3, as defined by MAVLink MAV_CMD enum. */
float param4; /**< Parameter 4, as defined by MAVLink MAV_CMD enum. */
float param5; /**< Parameter 5, as defined by MAVLink MAV_CMD enum. */
float param6; /**< Parameter 6, as defined by MAVLink MAV_CMD enum. */
float param7; /**< Parameter 7, as defined by MAVLink MAV_CMD enum. */
uint16_t command; /**< Command ID, as defined MAVLink by MAV_CMD enum. */
float param1; /**< Parameter 1, as defined by MAVLink VEHICLE_CMD enum. */
float param2; /**< Parameter 2, as defined by MAVLink VEHICLE_CMD enum. */
float param3; /**< Parameter 3, as defined by MAVLink VEHICLE_CMD enum. */
float param4; /**< Parameter 4, as defined by MAVLink VEHICLE_CMD enum. */
float param5; /**< Parameter 5, as defined by MAVLink VEHICLE_CMD enum. */
float param6; /**< Parameter 6, as defined by MAVLink VEHICLE_CMD enum. */
float param7; /**< Parameter 7, as defined by MAVLink VEHICLE_CMD enum. */
uint16_t command; /**< Command ID, as defined MAVLink by VEHICLE_CMD enum. */
uint8_t target_system; /**< System which should execute the command */
uint8_t target_component; /**< Component which should execute the command, 0 for all components */
uint8_t source_system; /**< System sending the command */

66
apps/uORB/topics/vehicle_status.h
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@ -79,7 +79,7 @@ enum VEHICLE_MODE_FLAG {
VEHICLE_MODE_FLAG_SAFETY_ARMED = 128,
VEHICLE_MODE_FLAG_MANUAL_INPUT_ENABLED = 64,
VEHICLE_MODE_FLAG_HIL_ENABLED = 32,
VEHICLE_MODE_FLAG_STABILIZE_ENABLED = 16,
VEHICLE_MODE_FLAG_STABILIZED_ENABLED = 16,
VEHICLE_MODE_FLAG_GUIDED_ENABLED = 8,
VEHICLE_MODE_FLAG_AUTO_ENABLED = 4,
VEHICLE_MODE_FLAG_TEST_ENABLED = 2,
@ -87,16 +87,48 @@ enum VEHICLE_MODE_FLAG {
}; /**< Same as MAV_MODE_FLAG of MAVLink 1.0 protocol */
enum VEHICLE_FLIGHT_MODE {
VEHICLE_FLIGHT_MODE_MANUAL = 0, /**< direct manual control, same as VEHICLE_FLIGHT_MODE_ATTITUDE for multirotors */
VEHICLE_FLIGHT_MODE_ATTITUDE, /**< attitude or rate stabilization, as defined by VEHICLE_ATTITUDE_MODE */
VEHICLE_FLIGHT_MODE_STABILIZED, /**< attitude or rate stabilization plus velocity or position stabilization */
VEHICLE_FLIGHT_MODE_AUTO /**< attitude or rate stabilization plus absolute position control and waypoints */
VEHICLE_FLIGHT_MODE_MANUAL = 0, /**< direct manual control, exact mode determined by VEHICLE_MANUAL_CONTROL_MODE */
VEHICLE_FLIGHT_MODE_STAB, /**< attitude or rate stabilization plus velocity or position stabilization */
VEHICLE_FLIGHT_MODE_HOLD, /**< hold current position (hover or loiter around position when switched) */
VEHICLE_FLIGHT_MODE_AUTO /**< attitude or rate stabilization plus absolute position control and waypoints */
};
enum VEHICLE_ATTITUDE_MODE {
VEHICLE_ATTITUDE_MODE_DIRECT, /**< no attitude control, direct stick input mixing (only fixed wing) */
VEHICLE_ATTITUDE_MODE_RATES, /**< body rates control mode */
VEHICLE_ATTITUDE_MODE_ATTITUDE /**< tait-bryan attitude control mode */
enum VEHICLE_MANUAL_CONTROL_MODE {
VEHICLE_MANUAL_CONTROL_MODE_DIRECT = 0, /**< no attitude control, direct stick input mixing (only fixed wing) */
VEHICLE_MANUAL_CONTROL_MODE_RATES, /**< body rates control mode */
VEHICLE_MANUAL_CONTROL_MODE_SAS /**< stability augmented system (SAS) mode */
};
enum VEHICLE_MANUAL_SAS_MODE {
VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_ABS = 0, /**< roll, pitch and yaw absolute */
VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_RATE, /**< roll and pitch absolute, yaw rate */
VEHICLE_MANUAL_SAS_MODE_SIMPLE, /**< simple mode (includes altitude hold) */
VEHICLE_MANUAL_SAS_MODE_ALTITUDE /**< altitude hold */
};
/**
* Should match 1:1 MAVLink's MAV_TYPE ENUM
*/
enum VEHICLE_TYPE {
VEHICLE_TYPE_GENERIC=0, /* Generic micro air vehicle. | */
VEHICLE_TYPE_FIXED_WING=1, /* Fixed wing aircraft. | */
VEHICLE_TYPE_QUADROTOR=2, /* Quadrotor | */
VEHICLE_TYPE_COAXIAL=3, /* Coaxial helicopter | */
VEHICLE_TYPE_HELICOPTER=4, /* Normal helicopter with tail rotor. | */
VEHICLE_TYPE_ANTENNA_TRACKER=5, /* Ground installation | */
VEHICLE_TYPE_GCS=6, /* Operator control unit / ground control station | */
VEHICLE_TYPE_AIRSHIP=7, /* Airship, controlled | */
VEHICLE_TYPE_FREE_BALLOON=8, /* Free balloon, uncontrolled | */
VEHICLE_TYPE_ROCKET=9, /* Rocket | */
VEHICLE_TYPE_GROUND_ROVER=10, /* Ground rover | */
VEHICLE_TYPE_SURFACE_BOAT=11, /* Surface vessel, boat, ship | */
VEHICLE_TYPE_SUBMARINE=12, /* Submarine | */
VEHICLE_TYPE_HEXAROTOR=13, /* Hexarotor | */
VEHICLE_TYPE_OCTOROTOR=14, /* Octorotor | */
VEHICLE_TYPE_TRICOPTER=15, /* Octorotor | */
VEHICLE_TYPE_FLAPPING_WING=16, /* Flapping wing | */
VEHICLE_TYPE_KITE=17, /* Kite | */
VEHICLE_TYPE_ENUM_END=18, /* | */
};
enum VEHICLE_BATTERY_WARNING {
@ -122,10 +154,9 @@ struct vehicle_status_s
commander_state_machine_t state_machine; /**< current flight state, main state machine */
enum VEHICLE_FLIGHT_MODE flight_mode; /**< current flight mode, as defined by mode switch */
enum VEHICLE_ATTITUDE_MODE attitute_mode; /**< current attitude control mode, as defined by VEHICLE_ATTITUDE_MODE enum */
// uint8_t mode;
enum VEHICLE_MANUAL_CONTROL_MODE manual_control_mode; /**< current attitude control mode, as defined by VEHICLE_ATTITUDE_MODE enum */
enum VEHICLE_MANUAL_SAS_MODE manual_sas_mode; /**< current stabilization mode */
int32_t system_type; /**< system type, inspired by MAVLinks VEHICLE_TYPE enum */
/* system flags - these represent the state predicates */
@ -172,9 +203,12 @@ struct vehicle_status_s
uint16_t errors_count3;
uint16_t errors_count4;
// bool remote_manual; /**< set to true by the commander when the manual-switch on the remote is set to manual */
bool gps_valid; /**< set to true by the commander app if the quality of the gps signal is good enough to use it in the position estimator */
bool flag_global_position_valid; /**< set to true by the commander app if the quality of the gps signal is good enough to use it in the position estimator */
bool flag_local_position_valid;
bool flag_vector_flight_mode_ok; /**< position estimation, battery voltage and other critical subsystems are good for autonomous flight */
bool flag_auto_flight_mode_ok; /**< conditions of vector flight mode apply plus a valid takeoff position lock has been aquired */
bool flag_external_manual_override_ok; /**< external override non-fatal for system. Only true for fixed wing */
bool flag_valid_launch_position; /**< indicates a valid launch position */
};
/**