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px4-firmware
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merged

This commit is contained in:
Lorenz Meier 2012-12-30 10:03:05 +01:00
parent b8250de1e6 62a95bf8e6
commit 142556b442
44 changed files with 2125 additions and 1308 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
#

27
apps/attitude_estimator_ekf/attitude_estimator_ekf_main.c
View File

@ -65,6 +65,7 @@
#include <systemlib/systemlib.h>
#include <systemlib/perf_counter.h>
#include <systemlib/err.h>
#include <systemlib/conversions.h>
#include "codegen/attitudeKalmanfilter_initialize.h"
#include "codegen/attitudeKalmanfilter.h"
@ -254,6 +255,7 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
bool initialized = false;
float gyro_offsets[3] = { 0.0f, 0.0f, 0.0f };
float accel_magnitude = CONSTANTS_ONE_G;
unsigned offset_count = 0;
/* register the perf counter */
@ -329,13 +331,34 @@ int attitude_estimator_ekf_thread_main(int argc, char *argv[])
z_k[1] = raw.gyro_rad_s[1] - gyro_offsets[1];
z_k[2] = raw.gyro_rad_s[2] - gyro_offsets[2];
/* update accelerometer measurements */
if (sensor_last_count[1] != raw.accelerometer_counter) {
/*
* Check if assumption of zero acceleration roughly holds.
* If not, do not update the accelerometer, predict only with gyroscopes.
* The violation of the zero acceleration assumption can only hold shortly,
* and predicting the angle with the gyros is safe for
*/
bool acceleration_stationary = true;
/* lowpass accel magnitude to prevent threshold aliasing in presence of vibrations */
accel_magnitude = accel_magnitude * 0.95f + 0.05f * sqrtf(raw.accelerometer_m_s2[0] * raw.accelerometer_m_s2[0]
+ raw.accelerometer_m_s2[1] * raw.accelerometer_m_s2[1]
+ raw.accelerometer_m_s2[2] * raw.accelerometer_m_s2[2]);
/* check if length of gravity vector differs in more than 15 % from expected result */
if (fabsf(accel_magnitude - CONSTANTS_ONE_G) > (CONSTANTS_ONE_G * 0.15f)) {
/* acceleration violates assumptions, disable updates */
acceleration_stationary = false;
}
/* update accelerometer measurements, reject if vector norm ends up being weird */
if (sensor_last_count[1] != raw.accelerometer_counter &&
acceleration_stationary) {
update_vect[1] = 1;
sensor_last_count[1] = raw.accelerometer_counter;
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];

6
apps/attitude_estimator_ekf/attitude_estimator_ekf_params.c
View File

@ -65,9 +65,9 @@ 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);

462
apps/commander/commander.c
View File

@ -72,10 +72,12 @@
#include <uORB/topics/sensor_combined.h>
#include <uORB/topics/manual_control_setpoint.h>
#include <uORB/topics/offboard_control_setpoint.h>
#include <uORB/topics/vehicle_gps_position.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_local_position.h>
#include <uORB/topics/vehicle_command.h>
#include <uORB/topics/subsystem_info.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/parameter_update.h>
#include <mavlink/mavlink_log.h>
#include <systemlib/param/param.h>
@ -93,6 +95,9 @@
PARAM_DEFINE_INT32(SYS_FAILSAVE_LL, 0); /**< Go into low-level failsafe after 0 ms */
//PARAM_DEFINE_INT32(SYS_FAILSAVE_HL, 0); /**< Go into high-level failsafe after 0 ms */
PARAM_DEFINE_FLOAT(TRIM_ROLL, 0.0f);
PARAM_DEFINE_FLOAT(TRIM_PITCH, 0.0f);
PARAM_DEFINE_FLOAT(TRIM_YAW, 0.0f);
#include <systemlib/cpuload.h>
extern struct system_load_s system_load;
@ -142,7 +147,6 @@ int commander_thread_main(int argc, char *argv[]);
static int buzzer_init(void);
static void buzzer_deinit(void);
static void tune_confirm(void);
static int led_init(void);
static void led_deinit(void);
static int led_toggle(int led);
@ -150,6 +154,7 @@ static int led_on(int led);
static int led_off(int led);
static void do_gyro_calibration(int status_pub, struct vehicle_status_s *status);
static void do_mag_calibration(int status_pub, struct vehicle_status_s *status);
static void do_rc_calibration(int status_pub, struct vehicle_status_s *status);
static void do_accel_calibration(int status_pub, struct vehicle_status_s *status);
static void handle_command(int status_pub, struct vehicle_status_s *current_status, struct vehicle_command_s *cmd);
@ -177,7 +182,7 @@ static int buzzer_init()
buzzer = open("/dev/tone_alarm", O_WRONLY);
if (buzzer < 0) {
fprintf(stderr, "[commander] Buzzer: open fail\n");
fprintf(stderr, "[cmd] Buzzer: open fail\n");
return ERROR;
}
@ -195,12 +200,12 @@ static int led_init()
leds = open(LED_DEVICE_PATH, 0);
if (leds < 0) {
fprintf(stderr, "[commander] LED: open fail\n");
fprintf(stderr, "[cmd] LED: open fail\n");
return ERROR;
}
if (ioctl(leds, LED_ON, LED_BLUE) || ioctl(leds, LED_ON, LED_AMBER)) {
fprintf(stderr, "[commander] LED: ioctl fail\n");
fprintf(stderr, "[cmd] LED: ioctl fail\n");
return ERROR;
}
@ -266,6 +271,34 @@ void tune_confirm(void) {
ioctl(buzzer, TONE_SET_ALARM, 3);
}
void tune_error(void) {
ioctl(buzzer, TONE_SET_ALARM, 4);
}
void do_rc_calibration(int status_pub, struct vehicle_status_s *status)
{
int sub_man = orb_subscribe(ORB_ID(manual_control_setpoint));
struct manual_control_setpoint_s sp;
orb_copy(ORB_ID(manual_control_setpoint), sub_man, &sp);
/* set parameters */
float p = sp.roll;
param_set(param_find("TRIM_ROLL"), &p);
p = sp.pitch;
param_set(param_find("TRIM_PITCH"), &p);
p = sp.yaw;
param_set(param_find("TRIM_YAW"), &p);
/* store to permanent storage */
/* auto-save to EEPROM */
int save_ret = param_save_default();
if(save_ret != 0) {
mavlink_log_critical(mavlink_fd, "TRIM CAL: WARN: auto-save of params failed");
}
mavlink_log_info(mavlink_fd, "[cmd] trim calibration done");
}
void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
{
@ -308,7 +341,7 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
};
if (OK != ioctl(fd, MAGIOCSSCALE, (long unsigned int)&mscale_null)) {
warn("WARNING: failed to set scale / offsets for mag");
mavlink_log_info(mavlink_fd, "[commander] failed to set scale / offsets for mag");
mavlink_log_info(mavlink_fd, "[cmd] failed to set scale / offsets for mag");
}
/* calibrate range */
@ -356,7 +389,7 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
axis_index++;
char buf[50];
sprintf(buf, "[commander] Please rotate around %c", axislabels[axis_index]);
sprintf(buf, "[cmd] Please rotate around %c", axislabels[axis_index]);
mavlink_log_info(mavlink_fd, buf);
tune_confirm();
@ -371,7 +404,7 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
// if ((axis_left / 1000) == 0 && axis_left > 0) {
// char buf[50];
// sprintf(buf, "[commander] %d seconds left for axis %c", axis_left, axislabels[axis_index]);
// sprintf(buf, "[cmd] %d seconds left for axis %c", axis_left, axislabels[axis_index]);
// mavlink_log_info(mavlink_fd, buf);
// }
@ -408,7 +441,7 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
calibration_counter++;
} else {
/* any poll failure for 1s is a reason to abort */
mavlink_log_info(mavlink_fd, "[commander] mag cal canceled");
mavlink_log_info(mavlink_fd, "[cmd] mag cal canceled");
break;
}
}
@ -444,27 +477,27 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
/* announce and set new offset */
if (param_set(param_find("SENS_MAG_XOFF"), &(mscale.x_offset))) {
fprintf(stderr, "[commander] Setting X mag offset failed!\n");
fprintf(stderr, "[cmd] Setting X mag offset failed!\n");
}
if (param_set(param_find("SENS_MAG_YOFF"), &(mscale.y_offset))) {
fprintf(stderr, "[commander] Setting Y mag offset failed!\n");
fprintf(stderr, "[cmd] Setting Y mag offset failed!\n");
}
if (param_set(param_find("SENS_MAG_ZOFF"), &(mscale.z_offset))) {
fprintf(stderr, "[commander] Setting Z mag offset failed!\n");
fprintf(stderr, "[cmd] Setting Z mag offset failed!\n");
}
if (param_set(param_find("SENS_MAG_XSCALE"), &(mscale.x_scale))) {
fprintf(stderr, "[commander] Setting X mag scale failed!\n");
fprintf(stderr, "[cmd] Setting X mag scale failed!\n");
}
if (param_set(param_find("SENS_MAG_YSCALE"), &(mscale.y_scale))) {
fprintf(stderr, "[commander] Setting Y mag scale failed!\n");
fprintf(stderr, "[cmd] Setting Y mag scale failed!\n");
}
if (param_set(param_find("SENS_MAG_ZSCALE"), &(mscale.z_scale))) {
fprintf(stderr, "[commander] Setting Z mag scale failed!\n");
fprintf(stderr, "[cmd] Setting Z mag scale failed!\n");
}
/* auto-save to EEPROM */
@ -487,7 +520,7 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
(double)mscale.y_scale, (double)mscale.z_scale);
mavlink_log_info(mavlink_fd, buf);
mavlink_log_info(mavlink_fd, "[commander] mag calibration done");
mavlink_log_info(mavlink_fd, "[cmd] mag calibration done");
tune_confirm();
sleep(2);
@ -496,7 +529,7 @@ void do_mag_calibration(int status_pub, struct vehicle_status_s *status)
/* third beep by cal end routine */
} else {
mavlink_log_info(mavlink_fd, "[commander] mag calibration FAILED (NaN)");
mavlink_log_info(mavlink_fd, "[cmd] mag calibration FAILED (NaN)");
}
/* disable calibration mode */
@ -547,7 +580,7 @@ void do_gyro_calibration(int status_pub, struct vehicle_status_s *status)
calibration_counter++;
} else {
/* any poll failure for 1s is a reason to abort */
mavlink_log_info(mavlink_fd, "[commander] gyro calibration aborted, retry");
mavlink_log_info(mavlink_fd, "[cmd] gyro calibration aborted, retry");
return;
}
}
@ -563,15 +596,15 @@ void do_gyro_calibration(int status_pub, struct vehicle_status_s *status)
if (isfinite(gyro_offset[0]) && isfinite(gyro_offset[1]) && isfinite(gyro_offset[2])) {
if (param_set(param_find("SENS_GYRO_XOFF"), &(gyro_offset[0]))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting X gyro offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting X gyro offset failed!");
}
if (param_set(param_find("SENS_GYRO_YOFF"), &(gyro_offset[1]))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting Y gyro offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting Y gyro offset failed!");
}
if (param_set(param_find("SENS_GYRO_ZOFF"), &(gyro_offset[2]))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting Z gyro offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting Z gyro offset failed!");
}
/* set offsets to actual value */
@ -597,7 +630,7 @@ void do_gyro_calibration(int status_pub, struct vehicle_status_s *status)
// char buf[50];
// sprintf(buf, "cal: x:%8.4f y:%8.4f z:%8.4f", (double)gyro_offset[0], (double)gyro_offset[1], (double)gyro_offset[2]);
// mavlink_log_info(mavlink_fd, buf);
mavlink_log_info(mavlink_fd, "[commander] gyro calibration done");
mavlink_log_info(mavlink_fd, "[cmd] gyro calibration done");
tune_confirm();
sleep(2);
@ -605,7 +638,7 @@ void do_gyro_calibration(int status_pub, struct vehicle_status_s *status)
sleep(2);
/* third beep by cal end routine */
} else {
mavlink_log_info(mavlink_fd, "[commander] gyro calibration FAILED (NaN)");
mavlink_log_info(mavlink_fd, "[cmd] gyro calibration FAILED (NaN)");
}
close(sub_sensor_combined);
@ -615,7 +648,7 @@ void do_accel_calibration(int status_pub, struct vehicle_status_s *status)
{
/* announce change */
mavlink_log_info(mavlink_fd, "[commander] keep it level and still");
mavlink_log_info(mavlink_fd, "[cmd] keep it level and still");
/* set to accel calibration mode */
status->flag_preflight_accel_calibration = true;
state_machine_publish(status_pub, status, mavlink_fd);
@ -653,7 +686,7 @@ void do_accel_calibration(int status_pub, struct vehicle_status_s *status)
calibration_counter++;
} else {
/* any poll failure for 1s is a reason to abort */
mavlink_log_info(mavlink_fd, "[commander] acceleration calibration aborted");
mavlink_log_info(mavlink_fd, "[cmd] acceleration calibration aborted");
return;
}
}
@ -672,27 +705,27 @@ void do_accel_calibration(int status_pub, struct vehicle_status_s *status)
float scale = 9.80665f / total_len;
if (param_set(param_find("SENS_ACC_XOFF"), &(accel_offset[0]))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting X accel offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting X accel offset failed!");
}
if (param_set(param_find("SENS_ACC_YOFF"), &(accel_offset[1]))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting Y accel offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting Y accel offset failed!");
}
if (param_set(param_find("SENS_ACC_ZOFF"), &(accel_offset[2]))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting Z accel offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting Z accel offset failed!");
}
if (param_set(param_find("SENS_ACC_XSCALE"), &(scale))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting X accel offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting X accel offset failed!");
}
if (param_set(param_find("SENS_ACC_YSCALE"), &(scale))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting Y accel offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting Y accel offset failed!");
}
if (param_set(param_find("SENS_ACC_ZSCALE"), &(scale))) {
mavlink_log_critical(mavlink_fd, "[commander] Setting Z accel offset failed!");
mavlink_log_critical(mavlink_fd, "[cmd] Setting Z accel offset failed!");
}
fd = open(ACCEL_DEVICE_PATH, 0);
@ -715,9 +748,9 @@ void do_accel_calibration(int status_pub, struct vehicle_status_s *status)
}
//char buf[50];
//sprintf(buf, "[commander] accel cal: x:%8.4f y:%8.4f z:%8.4f\n", (double)accel_offset[0], (double)accel_offset[1], (double)accel_offset[2]);
//sprintf(buf, "[cmd] accel cal: x:%8.4f y:%8.4f z:%8.4f\n", (double)accel_offset[0], (double)accel_offset[1], (double)accel_offset[2]);
//mavlink_log_info(mavlink_fd, buf);
mavlink_log_info(mavlink_fd, "[commander] accel calibration done");
mavlink_log_info(mavlink_fd, "[cmd] accel calibration done");
tune_confirm();
sleep(2);
@ -725,7 +758,7 @@ void do_accel_calibration(int status_pub, struct vehicle_status_s *status)
sleep(2);
/* third beep by cal end routine */
} else {
mavlink_log_info(mavlink_fd, "[commander] accel calibration FAILED (NaN)");
mavlink_log_info(mavlink_fd, "[cmd] accel calibration FAILED (NaN)");
}
/* exit accel calibration mode */
@ -851,15 +884,15 @@ void handle_command(int status_pub, struct vehicle_status_s *current_vehicle_sta
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_PREFLIGHT);
if (current_status.state_machine == SYSTEM_STATE_PREFLIGHT) {
mavlink_log_info(mavlink_fd, "[commander] CMD starting gyro calibration");
mavlink_log_info(mavlink_fd, "[cmd] starting gyro calibration");
tune_confirm();
do_gyro_calibration(status_pub, &current_status);
mavlink_log_info(mavlink_fd, "[commander] CMD finished gyro calibration");
mavlink_log_info(mavlink_fd, "[cmd] finished gyro calibration");
tune_confirm();
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_STANDBY);
result = MAV_RESULT_ACCEPTED;
} else {
mavlink_log_critical(mavlink_fd, "[commander] REJECTING gyro calibration");
mavlink_log_critical(mavlink_fd, "[cmd] REJECTING gyro calibration");
result = MAV_RESULT_DENIED;
}
handled = true;
@ -871,15 +904,50 @@ void handle_command(int status_pub, struct vehicle_status_s *current_vehicle_sta
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_PREFLIGHT);
if (current_status.state_machine == SYSTEM_STATE_PREFLIGHT) {
mavlink_log_info(mavlink_fd, "[commander] CMD starting mag calibration");
mavlink_log_info(mavlink_fd, "[cmd] starting mag calibration");
tune_confirm();
do_mag_calibration(status_pub, &current_status);
mavlink_log_info(mavlink_fd, "[commander] CMD finished mag calibration");
mavlink_log_info(mavlink_fd, "[cmd] finished mag calibration");
tune_confirm();
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_STANDBY);
result = MAV_RESULT_ACCEPTED;
} else {
mavlink_log_critical(mavlink_fd, "[commander] CMD REJECTING mag calibration");
mavlink_log_critical(mavlink_fd, "[cmd] REJECTING mag calibration");
result = MAV_RESULT_DENIED;
}
handled = true;
}
/* zero-altitude pressure calibration */
if ((int)(cmd->param3) == 1) {
/* transition to calibration state */
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_PREFLIGHT);
if (current_status.state_machine == SYSTEM_STATE_PREFLIGHT) {
mavlink_log_info(mavlink_fd, "[cmd] zero altitude cal. not implemented");
tune_confirm();
} else {
mavlink_log_critical(mavlink_fd, "[cmd] REJECTING altitude calibration");
result = MAV_RESULT_DENIED;
}
handled = true;
}
/* trim calibration */
if ((int)(cmd->param4) == 1) {
/* transition to calibration state */
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_PREFLIGHT);
if (current_status.state_machine == SYSTEM_STATE_PREFLIGHT) {
mavlink_log_info(mavlink_fd, "[cmd] starting trim calibration");
tune_confirm();
do_rc_calibration(status_pub, &current_status);
mavlink_log_info(mavlink_fd, "[cmd] finished trim calibration");
tune_confirm();
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_STANDBY);
result = MAV_RESULT_ACCEPTED;
} else {
mavlink_log_critical(mavlink_fd, "[cmd] REJECTING trim calibration");
result = MAV_RESULT_DENIED;
}
handled = true;
@ -891,15 +959,15 @@ void handle_command(int status_pub, struct vehicle_status_s *current_vehicle_sta
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_PREFLIGHT);
if (current_status.state_machine == SYSTEM_STATE_PREFLIGHT) {
mavlink_log_info(mavlink_fd, "[commander] CMD starting accel calibration");
mavlink_log_info(mavlink_fd, "[cmd] CMD starting accel calibration");
tune_confirm();
do_accel_calibration(status_pub, &current_status);
tune_confirm();
mavlink_log_info(mavlink_fd, "[commander] CMD finished accel calibration");
mavlink_log_info(mavlink_fd, "[cmd] CMD finished accel calibration");
do_state_update(status_pub, &current_status, mavlink_fd, SYSTEM_STATE_STANDBY);
result = MAV_RESULT_ACCEPTED;
} else {
mavlink_log_critical(mavlink_fd, "[commander] REJECTING accel calibration");
mavlink_log_critical(mavlink_fd, "[cmd] REJECTING accel calibration");
result = MAV_RESULT_DENIED;
}
handled = true;
@ -907,16 +975,21 @@ void handle_command(int status_pub, struct vehicle_status_s *current_vehicle_sta
/* none found */
if (!handled) {
//fprintf(stderr, "[commander] refusing unsupported calibration request\n");
mavlink_log_critical(mavlink_fd, "[commander] CMD refusing unsup. calib. request");
//fprintf(stderr, "[cmd] refusing unsupported calibration request\n");
mavlink_log_critical(mavlink_fd, "[cmd] CMD refusing unsup. calib. request");
result = MAV_RESULT_UNSUPPORTED;
}
}
break;
case MAV_CMD_PREFLIGHT_STORAGE: {
if (current_status.flag_system_armed) {
mavlink_log_info(mavlink_fd, "[cmd] REJECTING param command while armed");
if (current_status.flag_system_armed &&
((current_status.system_type == MAV_TYPE_QUADROTOR) ||
(current_status.system_type == MAV_TYPE_HEXAROTOR) ||
(current_status.system_type == MAV_TYPE_OCTOROTOR))) {
/* do not perform expensive memory tasks on multirotors in flight */
// XXX this is over-safe, as soon as cmd is in low prio thread this can be allowed
mavlink_log_info(mavlink_fd, "[cmd] REJECTING save cmd while multicopter armed");
} else {
// XXX move this to LOW PRIO THREAD of commander app
@ -1167,8 +1240,10 @@ int commander_thread_main(int argc, char *argv[])
failsafe_lowlevel_timeout_ms = 0;
param_get(param_find("SYS_FAILSAVE_LL"), &failsafe_lowlevel_timeout_ms);
param_t _param_sys_type = param_find("MAV_TYPE");
/* welcome user */
printf("[commander] I am in command now!\n");
printf("[cmd] I am in command now!\n");
/* pthreads for command and subsystem info handling */
// pthread_t command_handling_thread;
@ -1176,17 +1251,17 @@ int commander_thread_main(int argc, char *argv[])
/* initialize */
if (led_init() != 0) {
fprintf(stderr, "[commander] ERROR: Failed to initialize leds\n");
fprintf(stderr, "[cmd] ERROR: Failed to initialize leds\n");
}
if (buzzer_init() != 0) {
fprintf(stderr, "[commander] ERROR: Failed to initialize buzzer\n");
fprintf(stderr, "[cmd] ERROR: Failed to initialize buzzer\n");
}
mavlink_fd = open(MAVLINK_LOG_DEVICE, 0);
if (mavlink_fd < 0) {
fprintf(stderr, "[commander] ERROR: Failed to open MAVLink log stream, start mavlink app first.\n");
fprintf(stderr, "[cmd] ERROR: Failed to open MAVLink log stream, start mavlink app first.\n");
}
/* make sure we are in preflight state */
@ -1199,6 +1274,10 @@ int commander_thread_main(int argc, char *argv[])
/* mark all signals lost as long as they haven't been found */
current_status.rc_signal_lost = true;
current_status.offboard_control_signal_lost = true;
/* allow manual override initially */
current_status.flag_external_manual_override_ok = true;
/* flag position info as bad, do not allow auto mode */
current_status.flag_vector_flight_mode_ok = false;
/* advertise to ORB */
stat_pub = orb_advertise(ORB_ID(vehicle_status), &current_status);
@ -1206,11 +1285,11 @@ int commander_thread_main(int argc, char *argv[])
state_machine_publish(stat_pub, &current_status, mavlink_fd);
if (stat_pub < 0) {
printf("[commander] ERROR: orb_advertise for topic vehicle_status failed.\n");
printf("[cmd] ERROR: orb_advertise for topic vehicle_status failed.\n");
exit(ERROR);
}
mavlink_log_info(mavlink_fd, "[commander] system is running");
mavlink_log_info(mavlink_fd, "[cmd] system is running");
/* create pthreads */
pthread_attr_t subsystem_info_attr;
@ -1249,19 +1328,32 @@ int commander_thread_main(int argc, char *argv[])
struct offboard_control_setpoint_s sp_offboard;
memset(&sp_offboard, 0, sizeof(sp_offboard));
int gps_sub = orb_subscribe(ORB_ID(vehicle_gps_position));
struct vehicle_gps_position_s gps;
memset(&gps, 0, sizeof(gps));
int global_position_sub = orb_subscribe(ORB_ID(vehicle_global_position));
struct vehicle_global_position_s global_position;
memset(&global_position, 0, sizeof(global_position));
uint64_t last_global_position_time = 0;
int local_position_sub = orb_subscribe(ORB_ID(vehicle_local_position));
struct vehicle_local_position_s local_position;
memset(&local_position, 0, sizeof(local_position));
uint64_t last_local_position_time = 0;
int sensor_sub = orb_subscribe(ORB_ID(sensor_combined));
struct sensor_combined_s sensors;
memset(&sensors, 0, sizeof(sensors));
sensors.battery_voltage_v = 0.0f;
sensors.battery_voltage_valid = false;
/* Subscribe to command topic */
int cmd_sub = orb_subscribe(ORB_ID(vehicle_command));
struct vehicle_command_s cmd;
memset(&cmd, 0, sizeof(cmd));
/* Subscribe to parameters changed topic */
int param_changed_sub = orb_subscribe(ORB_ID(parameter_update));
struct parameter_update_s param_changed;
memset(&param_changed, 0, sizeof(param_changed));
// uint8_t vehicle_state_previous = current_status.state_machine;
float voltage_previous = 0.0f;
@ -1274,6 +1366,8 @@ int commander_thread_main(int argc, char *argv[])
uint64_t failsave_ll_start_time = 0;
bool state_changed = true;
bool param_init_forced = true;
while (!thread_should_exit) {
@ -1288,8 +1382,13 @@ int commander_thread_main(int argc, char *argv[])
if (new_data) {
orb_copy(ORB_ID(offboard_control_setpoint), sp_offboard_sub, &sp_offboard);
}
orb_copy(ORB_ID(vehicle_gps_position), gps_sub, &gps);
orb_check(sensor_sub, &new_data);
if (new_data) {
orb_copy(ORB_ID(sensor_combined), sensor_sub, &sensors);
} else {
sensors.battery_voltage_valid = false;
}
orb_check(cmd_sub, &new_data);
if (new_data) {
@ -1299,6 +1398,46 @@ int commander_thread_main(int argc, char *argv[])
/* handle it */
handle_command(stat_pub, &current_status, &cmd);
}
/* update parameters */
orb_check(param_changed_sub, &new_data);
if (new_data || param_init_forced) {
param_init_forced = false;
/* parameters changed */
orb_copy(ORB_ID(parameter_update), param_changed_sub, &param_changed);
/* update parameters */
if (!current_status.flag_system_armed) {
if (param_get(_param_sys_type, &(current_status.system_type)) != OK) {
warnx("failed setting new system type");
}
/* disable manual override for all systems that rely on electronic stabilization */
if (current_status.system_type == MAV_TYPE_QUADROTOR ||
current_status.system_type == MAV_TYPE_HEXAROTOR ||
current_status.system_type == MAV_TYPE_OCTOROTOR) {
current_status.flag_external_manual_override_ok = false;
} else {
current_status.flag_external_manual_override_ok = true;
}
} else {
printf("ARMED, rejecting sys type change\n");
}
}
/* update global position estimate */
orb_check(global_position_sub, &new_data);
if (new_data) {
/* position changed */
orb_copy(ORB_ID(vehicle_global_position), global_position_sub, &global_position);
last_global_position_time = global_position.timestamp;
}
/* update local position estimate */
orb_check(local_position_sub, &new_data);
if (new_data) {
/* position changed */
orb_copy(ORB_ID(vehicle_local_position), local_position_sub, &local_position);
last_local_position_time = local_position.timestamp;
}
battery_voltage = sensors.battery_voltage_v;
battery_voltage_valid = sensors.battery_voltage_valid;
@ -1376,14 +1515,18 @@ int commander_thread_main(int argc, char *argv[])
/* Check battery voltage */
/* write to sys_status */
if (battery_voltage_valid) {
current_status.voltage_battery = battery_voltage;
} else {
current_status.voltage_battery = 0.0f;
}
/* if battery voltage is getting lower, warn using buzzer, etc. */
if (battery_voltage_valid && (bat_remain < 0.15f /* XXX MAGIC NUMBER */) && (false == low_battery_voltage_actions_done)) { //TODO: add filter, or call emergency after n measurements < VOLTAGE_BATTERY_MINIMAL_MILLIVOLTS
if (low_voltage_counter > LOW_VOLTAGE_BATTERY_COUNTER_LIMIT) {
low_battery_voltage_actions_done = true;
mavlink_log_critical(mavlink_fd, "[commander] WARNING! LOW BATTERY!");
mavlink_log_critical(mavlink_fd, "[cmd] WARNING! LOW BATTERY!");
}
low_voltage_counter++;
@ -1393,7 +1536,7 @@ int commander_thread_main(int argc, char *argv[])
else if (battery_voltage_valid && (bat_remain < 0.1f /* XXX MAGIC NUMBER */) && (false == critical_battery_voltage_actions_done && true == low_battery_voltage_actions_done)) {
if (critical_voltage_counter > CRITICAL_VOLTAGE_BATTERY_COUNTER_LIMIT) {
critical_battery_voltage_actions_done = true;
mavlink_log_critical(mavlink_fd, "[commander] EMERGENCY! CRITICAL BATTERY!");
mavlink_log_critical(mavlink_fd, "[cmd] EMERGENCY! CRITICAL BATTERY!");
state_machine_emergency(stat_pub, &current_status, mavlink_fd);
}
@ -1406,6 +1549,76 @@ int commander_thread_main(int argc, char *argv[])
/* End battery voltage check */
/*
* Check for valid position information.
*
* If the system has a valid position source from an onboard
* position estimator, it is safe to operate it autonomously.
* The flag_vector_flight_mode_ok flag indicates that a minimum
* set of position measurements is available.
*/
/* store current state to reason later about a state change */
bool vector_flight_mode_ok = current_status.flag_vector_flight_mode_ok;
bool global_pos_valid = current_status.flag_global_position_valid;
bool local_pos_valid = current_status.flag_local_position_valid;
/* check for global or local position updates, set a timeout of 2s */
if (hrt_absolute_time() - last_global_position_time < 2000000) {
current_status.flag_global_position_valid = true;
// XXX check for controller status and home position as well
} else {
current_status.flag_global_position_valid = false;
}
if (hrt_absolute_time() - last_local_position_time < 2000000) {
current_status.flag_local_position_valid = true;
// XXX check for controller status and home position as well
} else {
current_status.flag_local_position_valid = false;
}
/*
* Consolidate global position and local position valid flags
* for vector flight mode.
*/
if (current_status.flag_local_position_valid ||
current_status.flag_global_position_valid) {
current_status.flag_vector_flight_mode_ok = true;
} else {
current_status.flag_vector_flight_mode_ok = false;
}
/* consolidate state change, flag as changed if required */
if (vector_flight_mode_ok != current_status.flag_vector_flight_mode_ok ||
global_pos_valid != current_status.flag_global_position_valid ||
local_pos_valid != current_status.flag_local_position_valid) {
state_changed = true;
}
/*
* Mark the position of the first position lock as return to launch (RTL)
* position. The MAV will return here on command or emergency.
*
* Conditions:
*
* 1) The system aquired position lock just now
* 2) The system has not aquired position lock before
* 3) The system is not armed (on the ground)
*/
if (!current_status.flag_valid_launch_position &&
!vector_flight_mode_ok && current_status.flag_vector_flight_mode_ok &&
!current_status.flag_system_armed) {
/* first time a valid position, store it and emit it */
// XXX implement storage and publication of RTL position
current_status.flag_valid_launch_position = true;
current_status.flag_auto_flight_mode_ok = true;
state_changed = true;
}
/* Check if last transition deserved an audio event */
// #warning This code depends on state that is no longer? maintained
// #if 0
@ -1471,8 +1684,97 @@ int commander_thread_main(int argc, char *argv[])
if ((hrt_absolute_time() - sp_man.timestamp) < 100000) {
/* check if left stick is in lower left position --> switch to standby state */
if ((sp_man.yaw < -STICK_ON_OFF_LIMIT) && sp_man.throttle < STICK_THRUST_RANGE*0.2f) { //TODO: remove hardcoded values
// /*
// * Check if manual control modes have to be switched
// */
// if (!isfinite(sp_man.manual_mode_switch)) {
// printf("man mode sw not finite\n");
// /* this switch is not properly mapped, set default */
// if ((current_status.system_type == MAV_TYPE_QUADROTOR) ||
// (current_status.system_type == MAV_TYPE_HEXAROTOR) ||
// (current_status.system_type == MAV_TYPE_OCTOROTOR)) {
// /* assuming a rotary wing, fall back 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, fall back 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;
// }
// } else if (sp_man.manual_mode_switch < -STICK_ON_OFF_LIMIT) {
// /* bottom stick position, set direct mode for vehicles supporting it */
// if ((current_status.system_type == MAV_TYPE_QUADROTOR) ||
// (current_status.system_type == MAV_TYPE_HEXAROTOR) ||
// (current_status.system_type == MAV_TYPE_OCTOROTOR)) {
// /* assuming a rotary wing, fall back 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 as requested */
// current_status.manual_control_mode = VEHICLE_MANUAL_CONTROL_MODE_DIRECT;
// current_status.flag_control_attitude_enabled = false;
// current_status.flag_control_rates_enabled = false;
// }
// } else if (sp_man.manual_mode_switch > STICK_ON_OFF_LIMIT) {
// /* top stick position, set SAS for all vehicle types */
// 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 {
// /* center stick position, set rate control */
// current_status.manual_control_mode = VEHICLE_MANUAL_CONTROL_MODE_RATES;
// current_status.flag_control_attitude_enabled = false;
// current_status.flag_control_rates_enabled = true;
// }
// printf("man ctrl mode: %d\n", (int)current_status.manual_control_mode);
/*
* Check if manual stability control modes have to be switched
*/
if (!isfinite(sp_man.manual_sas_switch)) {
/* this switch is not properly mapped, set default */
current_status.manual_sas_mode = VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_ABS;
} else if (sp_man.manual_sas_switch < -STICK_ON_OFF_LIMIT) {
/* bottom stick position, set altitude hold */
current_status.manual_sas_mode = VEHICLE_MANUAL_SAS_MODE_ALTITUDE;
} else if (sp_man.manual_sas_switch > STICK_ON_OFF_LIMIT) {
/* top stick position */
current_status.manual_sas_mode = VEHICLE_MANUAL_SAS_MODE_SIMPLE;
} else {
/* center stick position, set default */
current_status.manual_sas_mode = VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_ABS;
}
/*
* Check if left stick is in lower left position --> switch to standby state.
* Do this only for multirotors, not for fixed wing aircraft.
*/
if (((current_status.system_type == MAV_TYPE_QUADROTOR) ||
(current_status.system_type == MAV_TYPE_HEXAROTOR) ||
(current_status.system_type == MAV_TYPE_OCTOROTOR)
) &&
((sp_man.yaw < -STICK_ON_OFF_LIMIT)) &&
(sp_man.throttle < STICK_THRUST_RANGE * 0.2f)) {
if (stick_off_counter > STICK_ON_OFF_COUNTER_LIMIT) {
update_state_machine_disarm(stat_pub, &current_status, mavlink_fd);
stick_on_counter = 0;
@ -1484,7 +1786,7 @@ int commander_thread_main(int argc, char *argv[])
}
/* check if left stick is in lower right position --> arm */
if (sp_man.yaw > STICK_ON_OFF_LIMIT && sp_man.throttle < STICK_THRUST_RANGE*0.2f) { //TODO: remove hardcoded values
if (sp_man.yaw > STICK_ON_OFF_LIMIT && sp_man.throttle < STICK_THRUST_RANGE * 0.2f) {
if (stick_on_counter > STICK_ON_OFF_COUNTER_LIMIT) {
update_state_machine_arm(stat_pub, &current_status, mavlink_fd);
stick_on_counter = 0;
@ -1494,24 +1796,36 @@ int commander_thread_main(int argc, char *argv[])
stick_off_counter = 0;
}
}
//printf("RC: y:%i/t:%i s:%i chans: %i\n", rc_yaw_scale, rc_throttle_scale, mode_switch_rc_value, rc.chan_count);
if (sp_man.override_mode_switch > STICK_ON_OFF_LIMIT) {
/* check manual override switch - switch to manual or auto mode */
if (sp_man.manual_override_switch > STICK_ON_OFF_LIMIT) {
/* enable manual override */
update_state_machine_mode_manual(stat_pub, &current_status, mavlink_fd);
} else if (sp_man.manual_override_switch < -STICK_ON_OFF_LIMIT) {
/* check auto mode switch for correct mode */
if (sp_man.auto_mode_switch > STICK_ON_OFF_LIMIT) {
/* enable stabilized mode */
update_state_machine_mode_stabilized(stat_pub, &current_status, mavlink_fd);
} else if (sp_man.override_mode_switch < -STICK_ON_OFF_LIMIT) {
} else if (sp_man.auto_mode_switch < -STICK_ON_OFF_LIMIT) {
update_state_machine_mode_auto(stat_pub, &current_status, mavlink_fd);
} else {
update_state_machine_mode_stabilized(stat_pub, &current_status, mavlink_fd);
update_state_machine_mode_hold(stat_pub, &current_status, mavlink_fd);
}
} else {
/* center stick position, set SAS for all vehicle types */
current_status.manual_control_mode = VEHICLE_MANUAL_CONTROL_MODE_SAS;
current_status.flag_control_attitude_enabled = true;
current_status.flag_control_rates_enabled = true;
}
/* handle the case where RC signal was regained */
if (!current_status.rc_signal_found_once) {
current_status.rc_signal_found_once = true;
mavlink_log_critical(mavlink_fd, "[commander] DETECTED RC SIGNAL FIRST TIME.");
mavlink_log_critical(mavlink_fd, "[cmd] DETECTED RC SIGNAL FIRST TIME.");
} else {
if (current_status.rc_signal_lost) mavlink_log_critical(mavlink_fd, "[commander] RECOVERY - RC SIGNAL GAINED!");
if (current_status.rc_signal_lost) mavlink_log_critical(mavlink_fd, "[cmd] RECOVERY - RC SIGNAL GAINED!");
}
current_status.rc_signal_cutting_off = false;
@ -1524,7 +1838,7 @@ int commander_thread_main(int argc, char *argv[])
if (!current_status.rc_signal_cutting_off || ((hrt_absolute_time() - last_print_time) > 5000000)) {
/* only complain if the offboard control is NOT active */
current_status.rc_signal_cutting_off = true;
mavlink_log_critical(mavlink_fd, "[commander] CRITICAL - NO REMOTE SIGNAL!");
mavlink_log_critical(mavlink_fd, "[cmd] CRITICAL - NO REMOTE SIGNAL!");
last_print_time = hrt_absolute_time();
}
/* flag as lost and update interval since when the signal was lost (to initiate RTL after some time) */
@ -1583,10 +1897,10 @@ int commander_thread_main(int argc, char *argv[])
state_changed = true;
tune_confirm();
mavlink_log_critical(mavlink_fd, "[commander] DETECTED OFFBOARD CONTROL SIGNAL FIRST");
mavlink_log_critical(mavlink_fd, "[cmd] DETECTED OFFBOARD CONTROL SIGNAL FIRST");
} else {
if (current_status.offboard_control_signal_lost) {
mavlink_log_critical(mavlink_fd, "[commander] OK:RECOVERY OFFBOARD CONTROL");
mavlink_log_critical(mavlink_fd, "[cmd] OK:RECOVERY OFFBOARD CONTROL");
state_changed = true;
tune_confirm();
}
@ -1610,7 +1924,7 @@ int commander_thread_main(int argc, char *argv[])
/* print error message for first RC glitch and then every 5 s / 5000 ms) */
if (!current_status.offboard_control_signal_weak || ((hrt_absolute_time() - last_print_time) > 5000000)) {
current_status.offboard_control_signal_weak = true;
mavlink_log_critical(mavlink_fd, "[commander] CRIT:NO OFFBOARD CONTROL!");
mavlink_log_critical(mavlink_fd, "[cmd] CRIT:NO OFFBOARD CONTROL!");
last_print_time = hrt_absolute_time();
}
/* flag as lost and update interval since when the signal was lost (to initiate RTL after some time) */
@ -1669,11 +1983,11 @@ int commander_thread_main(int argc, char *argv[])
buzzer_deinit();
close(sp_man_sub);
close(sp_offboard_sub);
close(gps_sub);
close(global_position_sub);
close(sensor_sub);
close(cmd_sub);
printf("[commander] exiting..\n");
printf("[cmd] exiting..\n");
fflush(stdout);
thread_running = false;

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_ */

171
apps/commander/state_machine_helper.c
View File

@ -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!");
fprintf(stderr, "[cmd] EMERGENCY LANDING!\n");
mavlink_log_critical(mavlink_fd, "[cmd] 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!");
fprintf(stderr, "[cmd] EMERGENCY MOTOR CUTOFF!\n");
mavlink_log_critical(mavlink_fd, "[cmd] EMERGENCY MOTOR CUTOFF!");
break;
case SYSTEM_STATE_GROUND_ERROR:
@ -114,8 +114,8 @@ 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");
fprintf(stderr, "[cmd] GROUND ERROR, locking down propulsion system\n");
mavlink_log_critical(mavlink_fd, "[cmd] GROUND ERROR, locking down propulsion system");
break;
case SYSTEM_STATE_PREFLIGHT:
@ -123,10 +123,10 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
|| 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, "[cmd] 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, "[cmd] REFUSED to switch to PREFLIGHT state");
}
break;
@ -136,13 +136,13 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
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, "[cmd] 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, "[cmd] REFUSED to REBOOT");
}
break;
@ -152,7 +152,7 @@ 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, "[cmd] Switched to STANDBY state");
break;
case SYSTEM_STATE_GROUND_READY:
@ -162,7 +162,7 @@ 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, "[cmd] Switched to GROUND READY state");
break;
case SYSTEM_STATE_AUTO:
@ -172,7 +172,7 @@ 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, "[cmd] Switched to FLYING / AUTO mode");
break;
case SYSTEM_STATE_STABILIZED:
@ -180,7 +180,7 @@ 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, "[cmd] Switched to FLYING / STABILIZED mode");
break;
case SYSTEM_STATE_MANUAL:
@ -188,7 +188,7 @@ 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, "[cmd] Switched to FLYING / MANUAL mode");
break;
default:
@ -203,7 +203,7 @@ int do_state_update(int status_pub, struct vehicle_status_s *current_status, con
ret = OK;
}
if (invalid_state) {
mavlink_log_critical(mavlink_fd, "[commander] REJECTING invalid state transition");
mavlink_log_critical(mavlink_fd, "[cmd] REJECTING invalid state transition");
ret = ERROR;
}
return ret;
@ -232,7 +232,7 @@ 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) {
@ -250,7 +250,7 @@ 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");
fprintf(stderr, "[cmd] 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) {
@ -262,7 +262,7 @@ void state_machine_emergency_always_critical(int status_pub, struct vehicle_stat
//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);
fprintf(stderr, "[cmd] Unknown system state: #%d\n", current_status->state_machine);
}
}
@ -272,7 +272,7 @@ 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 +497,7 @@ 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 +505,11 @@ 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 +518,126 @@ 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 == MAV_TYPE_QUADROTOR) ||
(current_status.system_type == MAV_TYPE_HEXAROTOR) ||
(current_status.system_type == MAV_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)
{
if (!current_status->flag_vector_flight_mode_ok) {
mavlink_log_critical(mavlink_fd, "NO POS LOCK, REJ. STAB 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("[cmd] stabilized mode\n");
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_STABILIZED;
current_status->flag_control_manual_enabled = true;
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_hold(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. HOLD MODE");
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] stabilized mode\n");
int old_mode = current_status->flight_mode;
current_status->flight_mode = VEHICLE_FLIGHT_MODE_HOLD;
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, "[cmd] REJECTING HIL, disarm first!")
} else {
mavlink_log_critical(mavlink_fd, "[cmd] 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_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 +645,7 @@ 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 +655,14 @@ 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");
fprintf(stderr, "[cmd] DENYING request to switch off HIL. Please power cycle (safety reasons)\n");
mavlink_log_critical(mavlink_fd, "[cmd] Power-cycle to exit HIL");
ret = ERROR;
}
@ -627,7 +687,8 @@ 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, "[cmd] 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 hold
*
* @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_hold(int status_pub, struct vehicle_status_s *current_status, const int mavlink_fd);
/**
* Handle state machine if mode switch is auto
*

4
apps/drivers/boards/px4fmu/px4fmu_adc.c
View File

@ -67,10 +67,10 @@
/* Identifying number of each ADC channel: Variable Resistor. */
#ifdef CONFIG_STM32_ADC3
static const uint8_t g_chanlist[ADC3_NCHANNELS] = {10, 11};// , 12, 13}; ADC12 and 13 are used by MPU on v1.5 boards
static const uint8_t g_chanlist[ADC3_NCHANNELS] = {10, 11, 12, 13};
/* Configurations of pins used byte each ADC channels */
static const uint32_t g_pinlist[ADC3_NCHANNELS] = {GPIO_ADC3_IN10, GPIO_ADC3_IN11}; // ADC12 and 13 are used by MPU on v1.5 boards, GPIO_ADC3_IN12, GPIO_ADC3_IN13};
static const uint32_t g_pinlist[ADC3_NCHANNELS] = {GPIO_ADC3_IN10, GPIO_ADC3_IN11, GPIO_ADC3_IN12, GPIO_ADC3_IN13};
#endif
/************************************************************************************

12
apps/drivers/boards/px4fmu/px4fmu_init.c
View File

@ -150,9 +150,7 @@ __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
@ -160,8 +158,6 @@ __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;
@ -177,10 +173,6 @@ __EXPORT int nsh_archinitialize(void)
ts_to_abstime(&ts),
(hrt_callout)stm32_serial_dma_poll,
NULL);
}
#endif
message("\r\n");
// initial LED state
drv_led_start();
@ -209,8 +201,7 @@ __EXPORT int nsh_archinitialize(void)
message("[boot] Successfully initialized SPI port 1\r\n");
#if defined(CONFIG_STM32_SPI3)
/* Get the SPI port */
/* Get the SPI port for the microsd slot */
message("[boot] Initializing SPI port 3\n");
spi3 = up_spiinitialize(3);
@ -233,7 +224,6 @@ __EXPORT int nsh_archinitialize(void)
}
message("[boot] Successfully bound SPI port 3 to the MMCSD driver\n");
#endif /* SPI3 */
#ifdef CONFIG_ADC
int adc_state = adc_devinit();

27
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++) {
/* 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]);
/* output to the servo */
// up_pwm_servo_set(i, 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);
}
}

45
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++) {
/* 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 */

140
apps/drivers/px4io/px4io.cpp
View File

@ -55,12 +55,14 @@
#include <unistd.h>
#include <termios.h>
#include <fcntl.h>
#include <math.h>
#include <arch/board/board.h>
#include <drivers/device/device.h>
#include <drivers/drv_rc_input.h>
#include <drivers/drv_pwm_output.h>
#include <drivers/drv_gpio.h>
#include <drivers/drv_hrt.h>
#include <drivers/drv_mixer.h>
@ -69,9 +71,12 @@
#include <systemlib/hx_stream.h>
#include <systemlib/err.h>
#include <systemlib/systemlib.h>
#include <systemlib/scheduling_priorities.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 <px4io/protocol.h>
@ -88,10 +93,17 @@ 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:
static const unsigned _max_actuators = PX4IO_OUTPUT_CHANNELS;
int _update_rate; ///< serial send rate in Hz
int _serial_fd; ///< serial interface to PX4IO
hx_stream_t _io_stream; ///< HX protocol stream
@ -103,8 +115,13 @@ 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
@ -116,6 +133,8 @@ private:
bool _primary_pwm_device; ///< true if we are the default PWM output
uint32_t _relays; ///< state of the PX4IO relays, one bit per relay
volatile bool _switch_armed; ///< PX4IO switch armed state
// XXX how should this work?
@ -178,16 +197,20 @@ 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),
_mixers(nullptr),
_primary_pwm_device(false),
_relays(0),
_switch_armed(false),
_send_needed(false),
_config_needed(false)
@ -237,7 +260,7 @@ 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);
return -errno;
@ -259,6 +282,17 @@ 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[])
{
@ -269,6 +303,7 @@ void
PX4IO::task_main()
{
log("starting");
int update_rate_in_ms;
/* open the serial port */
_serial_fd = ::open("/dev/ttyS2", O_RDWR);
@ -306,12 +341,20 @@ 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 = int(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),
@ -322,13 +365,15 @@ PX4IO::task_main()
_to_input_rc = orb_advertise(ORB_ID(input_rc), &_input_rc);
/* 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;
log("ready");
@ -357,16 +402,37 @@ PX4IO::task_main()
if (fds[1].revents & POLLIN) {
/* get controls */
orb_copy(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, _t_actuators, &_controls);
orb_copy(_primary_pwm_device ? ORB_ID_VEHICLE_ATTITUDE_CONTROLS :
ORB_ID(actuator_controls_1), _t_actuators, &_controls);
/* mix */
if (_mixers != nullptr) {
/* XXX is this the right count? */
_mixers->mix(&_outputs.output[0], _max_actuators);
_outputs.timestamp = hrt_absolute_time();
_outputs.noutputs = _mixers->mix(&_outputs.output[0], _max_actuators);
// 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);
/* convert to PWM values */
for (unsigned i = 0; i < _max_actuators; i++)
for (unsigned i = 0; i < _max_actuators; 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;
}
}
/* and flag for update */
_send_needed = true;
@ -378,6 +444,11 @@ PX4IO::task_main()
orb_copy(ORB_ID(actuator_armed), _t_armed, &_armed);
_send_needed = true;
}
if (fds[3].revents & POLLIN) {
orb_copy(ORB_ID(vehicle_status), _t_vstatus, &_vstatus);
_send_needed = true;
}
}
/* send an update to IO if required */
@ -508,12 +579,22 @@ PX4IO::io_send()
cmd.servo_command[i] = _outputs.output[i];
/* publish as we send */
orb_publish(ORB_ID_VEHICLE_CONTROLS, _t_outputs, &_outputs);
_outputs.timestamp = hrt_absolute_time();
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), _t_outputs, &_outputs);
// XXX relays
/* armed and not locked down */
/* 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 -> 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)
@ -572,6 +653,30 @@ PX4IO::ioctl(file *filep, int cmd, unsigned long arg)
*(servo_position_t *)arg = _outputs.output[cmd - PWM_SERVO_GET(0)];
break;
case GPIO_RESET:
_relays = 0;
_send_needed = true;
break;
case GPIO_SET:
case GPIO_CLEAR:
/* make sure only valid bits are being set */
if ((arg & ((1UL << PX4IO_RELAY_CHANNELS) - 1)) != arg) {
ret = EINVAL;
break;
}
if (cmd == GPIO_SET) {
_relays |= arg;
} else {
_relays &= ~arg;
}
_send_needed = true;
break;
case GPIO_GET:
*(uint32_t *)arg = _relays;
break;
case MIXERIOCGETOUTPUTCOUNT:
*(unsigned *)arg = _max_actuators;
break;
@ -678,7 +783,7 @@ test(void)
void
monitor(void)
{
unsigned cancels = 4;
unsigned cancels = 3;
printf("Hit <enter> three times to exit monitor mode\n");
for (;;) {
@ -699,6 +804,7 @@ monitor(void)
g_dev->dump_one = true;
}
}
}
int
@ -720,6 +826,16 @@ 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);
}

16
apps/fixedwing_att_control/fixedwing_att_control_att.c
View File

@ -113,6 +113,7 @@ 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,
const float speed_body[],
struct vehicle_rates_setpoint_s *rates_sp)
{
static int counter = 0;
@ -145,12 +146,21 @@ 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++;

2
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,
const float speed_body[],
struct vehicle_rates_setpoint_s *rates_sp);
#endif /* FIXEDWING_ATT_CONTROL_ATT_H_ */

203
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.
@ -126,7 +102,7 @@ int fixedwing_att_control_thread_main(int argc, char *argv[])
}
/* welcome user */
printf("[fixedwing att_control] started\n");
printf("[fixedwing att control] started\n");
/* declare and safely initialize all structs */
struct vehicle_attitude_s att;
@ -135,14 +111,13 @@ int fixedwing_att_control_thread_main(int argc, char *argv[])
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));
// static struct debug_key_value_s debug_output;
// memset(&debug_output, 0, sizeof(debug_output));
/* output structs */
struct actuator_controls_s actuators;
memset(&actuators, 0, sizeof(actuators));
@ -153,18 +128,18 @@ int fixedwing_att_control_thread_main(int argc, char *argv[])
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';
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)
@ -172,9 +147,35 @@ int fixedwing_att_control_thread_main(int argc, char *argv[])
/* 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");
}
}
orb_copy(ORB_ID(manual_control_setpoint), manual_sp_sub, &manual_sp);
orb_copy(ORB_ID(vehicle_status), vstatus_sub, &vstatus);
@ -182,34 +183,143 @@ int fixedwing_att_control_thread_main(int argc, char *argv[])
gyro[1] = att.pitchspeed;
gyro[2] = att.yawspeed;
/* Control */
/* control */
if (vstatus.state_machine == SYSTEM_STATE_AUTO) {
/* Attitude Control */
fixedwing_att_control_attitude(&att_sp,
&att,
&rates_sp);
/* attitude control */
fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
/* Attitude Rate Control */
/* 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;
/* set flaps to zero */
actuators.control[4] = 0.0f;
} else if (vstatus.state_machine == SYSTEM_STATE_STABILIZED) {
/* if the RC signal is lost, try to stay level and go slowly back down to ground */
if (vstatus.rc_signal_lost) {
// XXX define failsafe throttle param
//param_get(failsafe_throttle_handle, &failsafe_throttle);
att_sp.roll_body = 0.3f;
att_sp.pitch_body = 0.0f;
att_sp.yaw_body = 0;
/* limit throttle to 60 % of last value */
if (isfinite(manual_sp.throttle)) {
att_sp.thrust = 0.6f * manual_sp.throttle;
} else {
att_sp.thrust = 0.0f;
}
// XXX disable yaw control, loiter
} 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();
// XXX: Stop copying setpoint / reference from bus, instead keep position
// and mix RC inputs in.
// XXX: For now just stabilize attitude, not anything else
// proper implementation should do stabilization in position controller
// and just check for stabilized or auto state
/* attitude control */
fixedwing_att_control_attitude(&att_sp, &att, speed_body, &rates_sp);
/* angular rate control */
fixedwing_att_control_rates(&rates_sp, gyro, &actuators);
/* pass through throttle */
actuators.control[3] = att_sp.thrust;
/* set flaps to zero */
actuators.control[4] = 0.0f;
// 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) {
if (vstatus.manual_control_mode == VEHICLE_MANUAL_CONTROL_MODE_SAS) {
/* if the RC signal is lost, try to stay level and go slowly back down to ground */
if (vstatus.rc_signal_lost) {
// XXX define failsafe throttle param
//param_get(failsafe_throttle_handle, &failsafe_throttle);
att_sp.roll_body = 0.3f;
att_sp.pitch_body = 0.0f;
/* limit throttle to 60 % of last value */
if (isfinite(manual_sp.throttle)) {
att_sp.thrust = 0.6f * manual_sp.throttle;
} else {
att_sp.thrust = 0.0f;
}
att_sp.yaw_body = 0;
// XXX disable yaw control, loiter
} 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);
/* pass through throttle */
actuators.control[3] = att_sp.thrust;
/* 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;
if (isfinite(manual_sp.flaps)) {
actuators.control[4] = manual_sp.flaps;
} else {
actuators.control[4] = 0.0f;
}
}
}
/* publish output */
/* publish rates */
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_pub, &rates_sp);
/* 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);
}
}
printf("[fixedwing_att_control] exiting, stopping all motors.\n");
thread_running = false;
@ -224,6 +334,7 @@ int fixedwing_att_control_thread_main(int argc, char *argv[])
close(att_sub);
close(actuator_pub);
close(rates_pub);
fflush(stdout);
exit(0);
@ -268,7 +379,7 @@ 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;

49
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;
};
@ -109,6 +135,7 @@ static int parameters_init(struct fw_rate_control_param_handles *h)
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;
}
@ -124,7 +151,7 @@ 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;
}
@ -167,12 +194,14 @@ 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++;

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;
}

211
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;
};
@ -136,19 +145,24 @@ 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->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;
}
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));
@ -171,7 +185,7 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
}
/* welcome user */
printf("[fixedwing att_control] started\n");
printf("[fixedwing pos control] started\n");
/* declare and safely initialize all structs */
struct vehicle_global_position_s global_pos;
@ -184,6 +198,8 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
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));
/* output structs */
struct vehicle_attitude_setpoint_s attitude_setpoint;
@ -193,80 +209,107 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
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);
/* 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));
/* Setup of loop */
struct pollfd fds = { .fd = att_sub, .events = POLLIN };
struct pollfd fds[2] = {
{ .fd = param_sub, .events = POLLIN },
{ .fd = att_sub, .events = POLLIN }
};
bool global_sp_updated_set_once = false;
float psi_track = 0.0f;
int counter = 0;
struct fw_pos_control_params p;
struct fw_pos_control_param_handles h;
PID_t heading_controller;
PID_t heading_rate_controller;
PID_t offtrack_controller;
PID_t altitude_controller;
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 */
poll(&fds, 1, 500);
int ret = poll(fds, 2, 500);
static int counter = 0;
static bool initialized = false;
if (ret < 0) {
/* poll error, count it in perf */
perf_count(fw_err_perf);
} else if (ret == 0) {
/* no return value, ignore */
} else {
static struct fw_pos_control_params p;
static struct fw_pos_control_param_handles h;
/* 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);
PID_t heading_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;
}
/* 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 */
/* only run controller if attitude changed */
if (fds[1].revents & POLLIN) {
static uint64_t last_run = 0;
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* 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 */
/* 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) {
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("psi_track: %0.4f\n", (double)psi_track);
printf("next wp direction: %0.4f\n", (double)psi_track);
}
/* Control */
/* 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);
// 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
@ -274,48 +317,88 @@ int fixedwing_pos_control_thread_main(int argc, char *argv[])
(double)start_pos.lat / (double)1e7d, (double)start_pos.lon / (double)1e7d,
(double)global_setpoint.lat / (double)1e7d, (double)global_setpoint.lon / (double)1e7d);
if(!(distance_res != OK || xtrack_err.past_end)) {
// XXX what is xtrack_err.past_end?
if(distance_res == OK /*&& !xtrack_err.past_end*/) {
float delta_psi_c = -p.xtrack_p * xtrack_err.distance; //(-) because z axis points downwards
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 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;
/* shift error to prevent wrapping issues */
/* wrap difference back onto -pi..pi range */
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);
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);
}
else {
if (counter % 100 == 0)
/* 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(global_sp_updated_set_once && pos_updated)
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);
}
/*Publish the attitude setpoint */
// 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?)
}
}
}
}
printf("[fixedwing_pos_control] exiting.\n");
@ -367,7 +450,7 @@ 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;

35
apps/mavlink/mavlink.c
View File

@ -189,12 +189,32 @@ 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 */
@ -225,17 +245,14 @@ 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:
@ -470,14 +487,15 @@ 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 */
@ -745,6 +763,7 @@ int mavlink_main(int argc, char *argv[])
thread_should_exit = true;
while (thread_running) {
usleep(200000);
printf(".");
}
warnx("terminated.");
exit(0);

25
apps/mavlink/mavlink_receiver.c
View File

@ -261,8 +261,8 @@ handle_message(mavlink_message_t *msg)
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.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) {
ml_armed = false;
@ -298,6 +298,26 @@ 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 +325,7 @@ 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);

45
apps/mavlink/orb_listener.c
View File

@ -455,7 +455,7 @@ l_actuator_outputs(struct listener *l)
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;
@ -506,20 +506,19 @@ l_actuator_outputs(struct listener *l)
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 */
// 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);
if (act_outputs.noutputs < 4) {
rudder = 0.0f;
throttle = (act_outputs.output[2] - 900.0f) / 1200.0f;
} 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,
@ -566,28 +565,28 @@ l_manual_control_setpoint(struct listener *l)
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]);
}
}
@ -739,7 +738,7 @@ 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 --- */

66
apps/multirotor_att_control/multirotor_att_control_main.c
View File

@ -232,19 +232,9 @@ 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) {
@ -258,12 +248,25 @@ mc_thread_main(int argc, char *argv[])
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;
/*
* 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
@ -285,9 +288,23 @@ 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 (state.manual_sas_mode == VEHICLE_MANUAL_SAS_MODE_ROLL_PITCH_ABS_YAW_RATE) {
rates_sp.yaw = manual.yaw;
control_yaw_position = false;
} else {
/*
* 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;
@ -299,16 +316,14 @@ mc_thread_main(int argc, char *argv[])
}
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 */
/* STEP 2: publish the controller output */
orb_publish(ORB_ID(vehicle_attitude_setpoint), att_sp_pub, &att_sp);
if (motor_test_mode) {
@ -322,6 +337,19 @@ mc_thread_main(int argc, char *argv[])
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 */

9
apps/multirotor_att_control/multirotor_attitude_control.c
View File

@ -197,7 +197,7 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
}
/* 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);
@ -206,6 +206,13 @@ 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 */

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>
@ -132,8 +133,9 @@ 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;
@ -171,26 +173,64 @@ comms_handle_command(const void *buffer, size_t length)
irqstate_t flags = irqsave();
/* fetch new PWM output values */
for (unsigned i = 0; i < PX4IO_OUTPUT_CHANNELS; i++)
for (unsigned i = 0; i < PX4IO_OUTPUT_CHANNELS; i++) {
system_state.fmu_channel_data[i] = cmd->servo_command[i];
}
/* if the IO is armed and the FMU gets disarmed, the IO must also disarm */
/* if IO is armed and FMU gets disarmed, IO must also disarm */
if (system_state.arm_ok && !cmd->arm_ok) {
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();
/* set PWM update rate if changed (after limiting) */
uint16_t new_servo_rate = cmd->servo_rate;
/* handle changes signalled by FMU */
// if (!system_state.arm_ok && system_state.armed)
// system_state.armed = false;
/* 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;
}
/* XXX do relay changes here */
for (unsigned i = 0; i < PX4IO_RELAY_CHANNELS; i++)
system_state.relays[i] = cmd->relay_state[i];
/*
* 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;
}
}
}
irqrestore(flags);
}

43
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
@ -88,11 +92,23 @@ 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;
/*
* Track if any input got an update in this round
*/
bool rc_updated;
if (fds[0].revents & POLLIN)
locked |= dsm_input();
if (fds[1].revents & POLLIN)
locked |= sbus_input();
locked |= sbus_input(fds[1].fd, PX4IO_INPUT_CHANNELS, &system_state.rc_channel_data,
&system_state.rc_channels, &system_state.rc_channels_timestamp, &rc_updated);
/*
* If we don't have lock from one of the serial receivers,
@ -107,6 +123,15 @@ 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.
@ -115,14 +140,20 @@ controls_main(void)
/* 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;
rc_updated = true;
}
/* XXX do bypass mode, etc. here */
/*
* If there was a RC update OR the RC signal status (lost / present) has
* just changed, request an update immediately.
*/
system_state.fmu_report_due |= rc_updated;
/* 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();
}
}

59
apps/px4io/mixer.cpp
View File

@ -48,7 +48,11 @@
#include <unistd.h>
#include <fcntl.h>
#include <debug.h>
#include <drivers/drv_pwm_output.h>
#include <drivers/drv_hrt.h>
#include <systemlib/mixer/mixer.h>
extern "C" {
@ -56,10 +60,9 @@ 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
/* current servo arm/disarm state */
bool mixer_servos_armed = false;
@ -80,39 +83,47 @@ 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("\nRX timeout\n");
}
/*
* Decide which set of inputs we're using.
*/
if (system_state.mixer_use_fmu) {
/* 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_OUTPUT_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++;
/* 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;
}
} else {
fmu_input_drops = 0;
system_state.fmu_data_received = false;
}
/* when override is on or the fmu is not available */
} 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];
} else {
/* we have no control input */
/* XXX builtin failsafe would activate here */
/* we have no control input (no FMU, no RC) */
// XXX builtin failsafe would activate here
control_count = 0;
}
/* this is for multicopters, etc. where manual override does not make sense */
} else {
/* if the fmu is available whe are good */
if(system_state.mixer_fmu_available) {
control_count = PX4IO_OUTPUT_CHANNELS;
control_values = &system_state.fmu_channel_data[0];
/* we better shut everything off */
} else {
control_count = 0;
}
}
/*
* Run the mixers if we have any control data at all.
*/
@ -144,7 +155,9 @@ mixer_tick(void)
/*
* 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) {

9
apps/px4io/protocol.h
View File

@ -54,9 +54,12 @@ struct px4io_command {
uint16_t f2i_magic;
#define F2I_MAGIC 0x636d
uint16_t servo_command[PX4IO_OUTPUT_CHANNELS];
bool relay_state[PX4IO_RELAY_CHANNELS];
bool arm_ok;
uint16_t servo_command[PX4IO_OUTPUT_CHANNELS]; /**< servo output channels */
uint16_t servo_rate; /**< 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 */
};
/**

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();

57
apps/px4io/px4io.h
View File

@ -70,49 +70,75 @@ 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 */
/*
/**
* 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_OUTPUT_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;
};
extern struct sys_state_s system_state;
@ -140,8 +166,8 @@ extern volatile int timers[TIMER_NUM_TIMERS];
#define LED_SAFETY(_s) stm32_gpiowrite(GPIO_LED3, !(_s))
#define POWER_SERVO(_s) stm32_gpiowrite(GPIO_SERVO_PWR_EN, (_s))
#define POWER_ACC1(_s) stm32_gpiowrite(GPIO_SERVO_ACC1_EN, (_s))
#define POWER_ACC2(_s) stm32_gpiowrite(GPIO_SERVO_ACC2_EN, (_s))
#define POWER_ACC1(_s) stm32_gpiowrite(GPIO_ACC1_PWR_EN, (_s))
#define POWER_ACC2(_s) stm32_gpiowrite(GPIO_ACC2_PWR_EN, (_s))
#define POWER_RELAY1(_s) stm32_gpiowrite(GPIO_RELAY1_EN, (_s))
#define POWER_RELAY2(_s) stm32_gpiowrite(GPIO_RELAY2_EN, (_s))
@ -172,7 +198,8 @@ extern void controls_main(void);
extern int dsm_init(const char *device);
extern bool dsm_input(void);
extern int sbus_init(const char *device);
extern bool sbus_input(void);
extern bool sbus_input(int fd, unsigned max_channels, uint16_t *channel_data, unsigned *channel_count,
uint64_t *receive_time, bool *updated);
/*
* Assertion codes

42
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 +159,8 @@ 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 +187,7 @@ 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 {

56
apps/px4io/sbus.c
View File

@ -49,14 +49,11 @@
#define DEBUG
#include "px4io.h"
#include "protocol.h"
#include "debug.h"
#define SBUS_FRAME_SIZE 25
#define SBUS_INPUT_CHANNELS 16
static int sbus_fd = -1;
static hrt_abstime last_rx_time;
static hrt_abstime last_frame_time;
@ -66,11 +63,14 @@ static unsigned partial_frame_count;
unsigned sbus_frame_drops;
static void sbus_decode(hrt_abstime frame_time);
static int sbus_decode(hrt_abstime frame_time, unsigned max_channels,
uint16_t *channel_data, unsigned *channel_count, uint64_t *receive_time);
int
sbus_init(const char *device)
{
static int sbus_fd = -1;
if (sbus_fd < 0)
sbus_fd = open(device, O_RDONLY);
@ -97,7 +97,8 @@ sbus_init(const char *device)
}
bool
sbus_input(void)
sbus_input(int fd, unsigned max_channels, uint16_t *channel_data, unsigned *channel_count,
uint64_t *receive_time, bool *updated)
{
ssize_t ret;
hrt_abstime now;
@ -130,7 +131,7 @@ sbus_input(void)
* Fetch bytes, but no more than we would need to complete
* the current frame.
*/
ret = read(sbus_fd, &frame[partial_frame_count], SBUS_FRAME_SIZE - partial_frame_count);
ret = read(fd, &frame[partial_frame_count], SBUS_FRAME_SIZE - partial_frame_count);
/* if the read failed for any reason, just give up here */
if (ret < 1)
@ -151,9 +152,9 @@ sbus_input(void)
/*
* Great, it looks like we might have a frame. Go ahead and
* decode it.
* decode it, report if the receiver got something.
*/
sbus_decode(now);
*updated = (sbus_decode(now, max_channels, channel_data, channel_count, receive_time) == OK);
partial_frame_count = 0;
out:
@ -199,25 +200,32 @@ static const struct sbus_bit_pick sbus_decoder[SBUS_INPUT_CHANNELS][3] = {
/* 15 */ { {20, 5, 0x07, 0}, {21, 0, 0xff, 3}, { 0, 0, 0x00, 0} }
};
static void
sbus_decode(hrt_abstime frame_time)
static int
sbus_decode(hrt_abstime frame_time, unsigned max_channels, uint16_t *channel_data, unsigned *channel_count, uint64_t *receive_time)
{
/* check frame boundary markers to avoid out-of-sync cases */
if ((frame[0] != 0x0f) || (frame[24] != 0x00)) {
sbus_frame_drops++;
return;
return 1;
}
/* if the failsafe bit is set, we consider the frame invalid */
if (frame[23] & (1 << 4)) {
return;
/* 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 */
/* actively announce signal loss */
*channel_count = 0;
return 1;
}
/* decode failsafe and RC status */
/* we have received something we think is a frame */
last_frame_time = frame_time;
unsigned chancount = (PX4IO_INPUT_CHANNELS > SBUS_INPUT_CHANNELS) ?
SBUS_INPUT_CHANNELS : PX4IO_INPUT_CHANNELS;
unsigned chancount = (max_channels > SBUS_INPUT_CHANNELS) ?
SBUS_INPUT_CHANNELS : max_channels;
/* use the decoder matrix to extract channel data */
for (unsigned channel = 0; channel < chancount; channel++) {
@ -240,17 +248,19 @@ sbus_decode(hrt_abstime frame_time)
system_state.rc_channel_data[channel] = (value / 2) + 998;
}
if (PX4IO_INPUT_CHANNELS >= 18) {
chancount = 18;
/* XXX decode the two switch channels */
/* decode switch channels if data fields are wide enough */
if (chancount > 17) {
/* channel 17 (index 16) */
system_state.rc_channel_data[16] = (frame[23] & (1 << 0)) * 1000 + 998;
/* channel 18 (index 17) */
system_state.rc_channel_data[17] = (frame[23] & (1 << 1)) * 1000 + 998;
}
/* note the number of channels decoded */
system_state.rc_channels = chancount;
*channel_count = chancount;
/* and note that we have received data from the R/C controller */
system_state.rc_channels_timestamp = frame_time;
*receive_time = frame_time;
/* trigger an immediate report to the FMU */
system_state.fmu_report_due = true;
return 0;
}

83
apps/sensors/sensor_params.c
View File

@ -69,58 +69,100 @@ 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(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(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(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(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(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(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(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_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(RC9_EXP, 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(RC10_EXP, 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(RC11_EXP, 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(RC12_EXP, 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(RC13_EXP, 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_FLOAT(RC12_EXP, 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 +171,23 @@ 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);

315
apps/sensors/sensors.cpp
View File

@ -95,6 +95,8 @@
#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
*
@ -123,7 +125,7 @@ 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 */
@ -167,7 +169,7 @@ 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];
@ -182,11 +184,27 @@ 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 */
@ -197,9 +215,11 @@ 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];
@ -210,11 +230,27 @@ 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 */
@ -377,22 +413,43 @@ 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);
// /* 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");
// _parameter_handles.rc_demix = param_find("RC_DEMIX");
/* 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");
@ -449,10 +506,10 @@ 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);
@ -469,25 +526,27 @@ 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);
}
// 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) {
@ -507,8 +566,44 @@ 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) {
@ -520,6 +615,31 @@ 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]));
@ -879,7 +999,7 @@ Sensors::ppm_poll()
*/
if (ppm_decoded_channels > 4 && hrt_absolute_time() - _ppm_last_valid < PPM_INPUT_TIMEOUT_INTERVAL) {
for (int i = 0; i < ppm_decoded_channels; i++) {
for (unsigned int i = 0; i < ppm_decoded_channels; i++) {
raw.values[i] = ppm_buffer[i];
}
@ -905,8 +1025,23 @@ 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)
@ -954,44 +1089,99 @@ 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;
}
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);
}
}
}
@ -1040,7 +1230,7 @@ Sensors::task_main()
memset(&raw, 0, sizeof(raw));
raw.timestamp = hrt_absolute_time();
raw.battery_voltage_v = BAT_VOL_INITIAL;
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.battery_voltage_counter = 0;
@ -1057,27 +1247,6 @@ 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];

89
apps/systemlib/conversions.c
View File

@ -55,3 +55,92 @@ 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;
}

22
apps/systemlib/conversions.h
View File

@ -44,6 +44,8 @@
#include <float.h>
#include <stdint.h>
#define CONSTANTS_ONE_G 9.80665f
__BEGIN_DECLS
/**
@ -56,6 +58,26 @@ __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]);
__END_DECLS
#endif /* CONVERSIONS_H_ */

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 */

32
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 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. */
/**

39
apps/uORB/topics/vehicle_status.h
View File

@ -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 +87,23 @@ 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_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 */
};
/**
@ -115,10 +122,9 @@ 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 MAV_TYPE enum */
/* system flags - these represent the state predicates */
@ -164,9 +170,12 @@ 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 */
};
/**