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Merge branch 'beta' of github.com:PX4/Firmware into paul_estimator

This commit is contained in:
Lorenz Meier 2014-02-21 13:17:29 +01:00
parent 447d159964 c659e0240b
commit 87410b5bde
20 changed files with 964 additions and 746 deletions
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BIN
ROMFS/px4fmu_common/logging/conv.zip
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88
ROMFS/px4fmu_logging/init.d/rcS
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@ -1,88 +0,0 @@
#!nsh
#
# PX4FMU startup script for logging purposes
#
#
# Try to mount the microSD card.
#
echo "[init] looking for microSD..."
if mount -t vfat /dev/mmcsd0 /fs/microsd
then
echo "[init] card mounted at /fs/microsd"
# Start playing the startup tune
tone_alarm start
else
echo "[init] no microSD card found"
# Play SOS
tone_alarm error
fi
uorb start
#
# Start sensor drivers here.
#
ms5611 start
adc start
# mag might be external
if hmc5883 start
then
echo "using HMC5883"
fi
if mpu6000 start
then
echo "using MPU6000"
fi
if l3gd20 start
then
echo "using L3GD20(H)"
fi
if lsm303d start
then
set BOARD fmuv2
else
set BOARD fmuv1
fi
# Start airspeed sensors
if meas_airspeed start
then
echo "using MEAS airspeed sensor"
else
if ets_airspeed start
then
echo "using ETS airspeed sensor (bus 3)"
else
if ets_airspeed start -b 1
then
echo "Using ETS airspeed sensor (bus 1)"
fi
fi
fi
#
# Start the sensor collection task.
# IMPORTANT: this also loads param offsets
# ALWAYS start this task before the
# preflight_check.
#
if sensors start
then
echo "SENSORS STARTED"
fi
sdlog2 start -r 250 -e -b 16
if sercon
then
echo "[init] USB interface connected"
# Try to get an USB console
nshterm /dev/ttyACM0 &
fi

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ROMFS/px4fmu_logging/logging/conv.zip
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0
Tools/README.txt → Tools/sdlog2/README.txt
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1070
Tools/logconv.m → Tools/sdlog2/logconv.m
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0
Tools/sdlog2_dump.py → Tools/sdlog2/sdlog2_dump.py
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2
src/drivers/drv_pwm_output.h
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@ -160,7 +160,7 @@ ORB_DECLARE(output_pwm);
#define DSM2_BIND_PULSES 3 /* DSM_BIND_START ioctl parameter, pulses required to start dsm2 pairing */
#define DSMX_BIND_PULSES 7 /* DSM_BIND_START ioctl parameter, pulses required to start dsmx pairing */
#define DSMX8_BIND_PULSES 10 /* DSM_BIND_START ioctl parameter, pulses required to start 8 or more channel dsmx pairing */
#define DSMX8_BIND_PULSES 10 /* DSM_BIND_START ioctl parameter, pulses required to start 8 or more channel dsmx pairing */
/** power up DSM receiver */
#define DSM_BIND_POWER_UP _IOC(_PWM_SERVO_BASE, 11)

2
src/drivers/mkblctrl/mkblctrl.cpp
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@ -705,7 +705,7 @@ MK::mk_check_for_blctrl(unsigned int count, bool showOutput, bool initI2C)
Motor[i].State |= MOTOR_STATE_PRESENT_MASK; // set present bit;
foundMotorCount++;
if (Motor[i].MaxPWM == 250) {
if ((Motor[i].MaxPWM & 252) == 248) {
Motor[i].Version = BLCTRL_NEW;
} else {

57
src/drivers/px4io/px4io.cpp
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@ -244,8 +244,7 @@ private:
volatile int _task; ///< worker task id
volatile bool _task_should_exit; ///< worker terminate flag
int _mavlink_fd; ///< mavlink file descriptor. This is opened by class instantiation and Doesn't appear to be usable in main thread.
int _thread_mavlink_fd; ///< mavlink file descriptor for thread.
int _mavlink_fd; ///< mavlink file descriptor.
perf_counter_t _perf_update; ///<local performance counter for status updates
perf_counter_t _perf_write; ///<local performance counter for PWM control writes
@ -474,7 +473,6 @@ PX4IO::PX4IO(device::Device *interface) :
_task(-1),
_task_should_exit(false),
_mavlink_fd(-1),
_thread_mavlink_fd(-1),
_perf_update(perf_alloc(PC_ELAPSED, "io update")),
_perf_write(perf_alloc(PC_ELAPSED, "io write")),
_perf_chan_count(perf_alloc(PC_COUNT, "io rc #")),
@ -507,9 +505,6 @@ PX4IO::PX4IO(device::Device *interface) :
/* we need this potentially before it could be set in task_main */
g_dev = this;
/* open MAVLink text channel */
_mavlink_fd = ::open(MAVLINK_LOG_DEVICE, 0);
_debug_enabled = false;
_servorail_status.rssi_v = 0;
}
@ -785,7 +780,7 @@ PX4IO::task_main()
hrt_abstime poll_last = 0;
hrt_abstime orb_check_last = 0;
_thread_mavlink_fd = ::open(MAVLINK_LOG_DEVICE, 0);
_mavlink_fd = ::open(MAVLINK_LOG_DEVICE, 0);
/*
* Subscribe to the appropriate PWM output topic based on whether we are the
@ -880,6 +875,10 @@ PX4IO::task_main()
/* run at 5Hz */
orb_check_last = now;
/* try to claim the MAVLink log FD */
if (_mavlink_fd < 0)
_mavlink_fd = ::open(MAVLINK_LOG_DEVICE, 0);
/* check updates on uORB topics and handle it */
bool updated = false;
@ -1275,16 +1274,14 @@ void
PX4IO::dsm_bind_ioctl(int dsmMode)
{
if (!(_status & PX4IO_P_STATUS_FLAGS_SAFETY_OFF)) {
/* 0: dsm2, 1:dsmx */
if ((dsmMode == 0) || (dsmMode == 1)) {
mavlink_log_info(_thread_mavlink_fd, "[IO] binding dsm%s rx", (dsmMode == 0) ? "2" : ((dsmMode == 1) ? "x" : "x8"));
ioctl(nullptr, DSM_BIND_START, (dsmMode == 0) ? DSM2_BIND_PULSES : ((dsmMode == 1) ? DSMX_BIND_PULSES : DSMX8_BIND_PULSES));
} else {
mavlink_log_info(_thread_mavlink_fd, "[IO] invalid dsm bind mode, bind request rejected");
}
mavlink_log_info(_mavlink_fd, "[IO] binding DSM%s RX", (dsmMode == 0) ? "2" : ((dsmMode == 1) ? "-X" : "-X8"));
int ret = ioctl(nullptr, DSM_BIND_START, (dsmMode == 0) ? DSM2_BIND_PULSES : ((dsmMode == 1) ? DSMX_BIND_PULSES : DSMX8_BIND_PULSES));
if (ret)
mavlink_log_critical(_mavlink_fd, "binding failed.");
} else {
mavlink_log_info(_thread_mavlink_fd, "[IO] system armed, bind request rejected");
mavlink_log_info(_mavlink_fd, "[IO] system armed, bind request rejected");
}
}
@ -2115,14 +2112,24 @@ PX4IO::ioctl(file * /*filep*/, int cmd, unsigned long arg)
break;
case DSM_BIND_START:
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_power_down);
usleep(500000);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_set_rx_out);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_power_up);
usleep(72000);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_send_pulses | (arg << 4));
usleep(50000);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_reinit_uart);
/* only allow DSM2, DSM-X and DSM-X with more than 7 channels */
if (arg == DSM2_BIND_PULSES ||
arg == DSMX_BIND_PULSES ||
arg == DSMX8_BIND_PULSES) {
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_power_down);
usleep(500000);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_set_rx_out);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_power_up);
usleep(72000);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_send_pulses | (arg << 4));
usleep(50000);
io_reg_set(PX4IO_PAGE_SETUP, PX4IO_P_SETUP_DSM, dsm_bind_reinit_uart);
ret = OK;
} else {
ret = -EINVAL;
}
break;
case DSM_BIND_POWER_UP:
@ -2615,7 +2622,7 @@ bind(int argc, char *argv[])
#endif
if (argc < 3)
errx(0, "needs argument, use dsm2 or dsmx");
errx(0, "needs argument, use dsm2, dsmx or dsmx8");
if (!strcmp(argv[2], "dsm2"))
pulses = DSM2_BIND_PULSES;
@ -2624,7 +2631,7 @@ bind(int argc, char *argv[])
else if (!strcmp(argv[2], "dsmx8"))
pulses = DSMX8_BIND_PULSES;
else
errx(1, "unknown parameter %s, use dsm2 or dsmx", argv[2]);
errx(1, "unknown parameter %s, use dsm2, dsmx or dsmx8", argv[2]);
// Test for custom pulse parameter
if (argc > 3)
pulses = atoi(argv[3]);

6
src/modules/commander/commander.cpp
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@ -430,7 +430,7 @@ bool handle_command(struct vehicle_status_s *status, const struct safety_s *safe
arming_res = TRANSITION_NOT_CHANGED;
if (base_mode & MAV_MODE_FLAG_SAFETY_ARMED) {
if ((safety->safety_switch_available && !safety->safety_off) && status->hil_state == HIL_STATE_OFF) {
if (safety->safety_switch_available && !safety->safety_off && status->hil_state == HIL_STATE_OFF) {
print_reject_arm("NOT ARMING: Press safety switch first.");
arming_res = TRANSITION_DENIED;
@ -516,7 +516,7 @@ bool handle_command(struct vehicle_status_s *status, const struct safety_s *safe
transition_result_t arming_res = TRANSITION_NOT_CHANGED;
if (!armed->armed && ((int)(cmd->param1 + 0.5f)) == 1) {
if (safety->safety_switch_available && !safety->safety_off) {
if (safety->safety_switch_available && !safety->safety_off && status->hil_state == HIL_STATE_OFF) {
print_reject_arm("NOT ARMING: Press safety switch first.");
arming_res = TRANSITION_DENIED;
@ -1156,7 +1156,7 @@ int commander_thread_main(int argc, char *argv[])
if (status.arming_state == ARMING_STATE_STANDBY &&
sp_man.yaw > STICK_ON_OFF_LIMIT && sp_man.throttle < STICK_THRUST_RANGE * 0.1f) {
if (stick_on_counter > STICK_ON_OFF_COUNTER_LIMIT) {
if (safety.safety_switch_available && !safety.safety_off) {
if (safety.safety_switch_available && !safety.safety_off && status.hil_state == HIL_STATE_OFF) {
print_reject_arm("NOT ARMING: Press safety switch first.");
} else if (status.main_state != MAIN_STATE_MANUAL) {

61
src/modules/mc_att_control/mc_att_control_main.cpp
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@ -53,11 +53,9 @@
#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>
@ -71,7 +69,6 @@
#include <uORB/topics/parameter_update.h>
#include <systemlib/param/param.h>
#include <systemlib/err.h>
#include <systemlib/pid/pid.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
#include <mathlib/mathlib.h>
@ -84,9 +81,9 @@
*/
extern "C" __EXPORT int mc_att_control_main(int argc, char *argv[]);
#define MIN_TAKEOFF_THROTTLE 0.3f
#define YAW_DEADZONE 0.05f
#define RATES_I_LIMIT 0.5f
#define MIN_TAKEOFF_THRUST 0.2f
#define RATES_I_LIMIT 0.3f
class MulticopterAttitudeControl
{
@ -135,15 +132,13 @@ private:
perf_counter_t _loop_perf; /**< loop performance counter */
math::Matrix<3, 3> _R_sp; /**< attitude setpoint rotation matrix */
math::Matrix<3, 3> _R; /**< rotation matrix for current state */
math::Vector<3> _rates_prev; /**< angular rates on previous step */
math::Vector<3> _rates_sp; /**< angular rates setpoint */
math::Vector<3> _rates_int; /**< angular rates integral error */
float _thrust_sp; /**< thrust setpoint */
math::Vector<3> _att_control; /**< attitude control vector */
math::Matrix<3, 3> I; /**< identity matrix */
math::Matrix<3, 3> _I; /**< identity matrix */
bool _reset_yaw_sp; /**< reset yaw setpoint flag */
@ -262,7 +257,7 @@ MulticopterAttitudeControl::MulticopterAttitudeControl() :
_actuators_0_pub(-1),
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "fw att control"))
_loop_perf(perf_alloc(PC_ELAPSED, "mc_att_control"))
{
memset(&_v_att, 0, sizeof(_v_att));
@ -276,15 +271,13 @@ MulticopterAttitudeControl::MulticopterAttitudeControl() :
_params.rate_i.zero();
_params.rate_d.zero();
_R_sp.identity();
_R.identity();
_rates_prev.zero();
_rates_sp.zero();
_rates_int.zero();
_thrust_sp = 0.0f;
_att_control.zero();
I.identity();
_I.identity();
_params_handles.roll_p = param_find("MC_ROLL_P");
_params_handles.roll_rate_p = param_find("MC_ROLLRATE_P");
@ -535,16 +528,18 @@ MulticopterAttitudeControl::control_attitude(float dt)
_thrust_sp = _v_att_sp.thrust;
/* construct attitude setpoint rotation matrix */
math::Matrix<3, 3> R_sp;
if (_v_att_sp.R_valid) {
/* rotation matrix in _att_sp is valid, use it */
_R_sp.set(&_v_att_sp.R_body[0][0]);
R_sp.set(&_v_att_sp.R_body[0][0]);
} else {
/* rotation matrix in _att_sp is not valid, use euler angles instead */
_R_sp.from_euler(_v_att_sp.roll_body, _v_att_sp.pitch_body, _v_att_sp.yaw_body);
R_sp.from_euler(_v_att_sp.roll_body, _v_att_sp.pitch_body, _v_att_sp.yaw_body);
/* copy rotation matrix back to setpoint struct */
memcpy(&_v_att_sp.R_body[0][0], &_R_sp.data[0][0], sizeof(_v_att_sp.R_body));
memcpy(&_v_att_sp.R_body[0][0], &R_sp.data[0][0], sizeof(_v_att_sp.R_body));
_v_att_sp.R_valid = true;
}
@ -561,23 +556,24 @@ MulticopterAttitudeControl::control_attitude(float dt)
}
/* rotation matrix for current state */
_R.set(_v_att.R);
math::Matrix<3, 3> R;
R.set(_v_att.R);
/* all input data is ready, run controller itself */
/* try to move thrust vector shortest way, because yaw response is slower than roll/pitch */
math::Vector<3> R_z(_R(0, 2), _R(1, 2), _R(2, 2));
math::Vector<3> R_sp_z(_R_sp(0, 2), _R_sp(1, 2), _R_sp(2, 2));
math::Vector<3> R_z(R(0, 2), R(1, 2), R(2, 2));
math::Vector<3> R_sp_z(R_sp(0, 2), R_sp(1, 2), R_sp(2, 2));
/* axis and sin(angle) of desired rotation */
math::Vector<3> e_R = _R.transposed() * (R_z % R_sp_z);
math::Vector<3> e_R = R.transposed() * (R_z % R_sp_z);
/* calculate angle error */
float e_R_z_sin = e_R.length();
float e_R_z_cos = R_z * R_sp_z;
/* calculate weight for yaw control */
float yaw_w = _R_sp(2, 2) * _R_sp(2, 2);
float yaw_w = R_sp(2, 2) * R_sp(2, 2);
/* calculate rotation matrix after roll/pitch only rotation */
math::Matrix<3, 3> R_rp;
@ -600,15 +596,15 @@ MulticopterAttitudeControl::control_attitude(float dt)
e_R_cp(2, 1) = e_R_z_axis(0);
/* rotation matrix for roll/pitch only rotation */
R_rp = _R * (I + e_R_cp * e_R_z_sin + e_R_cp * e_R_cp * (1.0f - e_R_z_cos));
R_rp = R * (_I + e_R_cp * e_R_z_sin + e_R_cp * e_R_cp * (1.0f - e_R_z_cos));
} else {
/* zero roll/pitch rotation */
R_rp = _R;
R_rp = R;
}
/* R_rp and _R_sp has the same Z axis, calculate yaw error */
math::Vector<3> R_sp_x(_R_sp(0, 0), _R_sp(1, 0), _R_sp(2, 0));
/* R_rp and R_sp has the same Z axis, calculate yaw error */
math::Vector<3> R_sp_x(R_sp(0, 0), R_sp(1, 0), R_sp(2, 0));
math::Vector<3> R_rp_x(R_rp(0, 0), R_rp(1, 0), R_rp(2, 0));
e_R(2) = atan2f((R_rp_x % R_sp_x) * R_sp_z, R_rp_x * R_sp_x) * yaw_w;
@ -616,7 +612,7 @@ MulticopterAttitudeControl::control_attitude(float dt)
/* for large thrust vector rotations use another rotation method:
* calculate angle and axis for R -> R_sp rotation directly */
math::Quaternion q;
q.from_dcm(_R.transposed() * _R_sp);
q.from_dcm(R.transposed() * R_sp);
math::Vector<3> e_R_d = q.imag();
e_R_d.normalize();
e_R_d *= 2.0f * atan2f(e_R_d.length(), q(0));
@ -658,7 +654,7 @@ MulticopterAttitudeControl::control_attitude_rates(float dt)
_rates_prev = rates;
/* update integral only if not saturated on low limit */
if (_thrust_sp > 0.1f) {
if (_thrust_sp > MIN_TAKEOFF_THRUST) {
for (int i = 0; i < 3; i++) {
if (fabsf(_att_control(i)) < _thrust_sp) {
float rate_i = _rates_int(i) + _params.rate_i(i) * rates_err(i) * dt;
@ -695,9 +691,6 @@ MulticopterAttitudeControl::task_main()
_manual_control_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
/* rate limit attitude updates to 200Hz, failsafe against spam, normally runs at the same rate as attitude estimator */
orb_set_interval(_v_att_sub, 5);
/* initialize parameters cache */
parameters_update();
@ -767,10 +760,12 @@ MulticopterAttitudeControl::task_main()
}
} else {
/* attitude controller disabled */
// TODO poll 'attitude_rates_setpoint' topic
_rates_sp.zero();
_thrust_sp = 0.0f;
/* attitude controller disabled, poll rates setpoint topic */
vehicle_rates_setpoint_poll();
_rates_sp(0) = _v_rates_sp.roll;
_rates_sp(1) = _v_rates_sp.pitch;
_rates_sp(2) = _v_rates_sp.yaw;
_thrust_sp = _v_rates_sp.thrust;
}
if (_v_control_mode.flag_control_rates_enabled) {

119
src/modules/mc_att_control/mc_att_control_params.c
View File

@ -41,16 +41,135 @@
#include <systemlib/param/param.h>
/**
* Roll P gain
*
* Roll proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLL_P, 6.0f);
/**
* Roll rate P gain
*
* Roll rate proportional gain, i.e. control output for angular speed error 1 rad/s.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLLRATE_P, 0.1f);
/**
* Roll rate I gain
*
* Roll rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLLRATE_I, 0.0f);
/**
* Roll rate D gain
*
* Roll rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_ROLLRATE_D, 0.002f);
/**
* Pitch P gain
*
* Pitch proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
*
* @unit 1/s
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCH_P, 6.0f);
/**
* Pitch rate P gain
*
* Pitch rate proportional gain, i.e. control output for angular speed error 1 rad/s.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCHRATE_P, 0.1f);
/**
* Pitch rate I gain
*
* Pitch rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCHRATE_I, 0.0f);
/**
* Pitch rate D gain
*
* Pitch rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_PITCHRATE_D, 0.002f);
/**
* Yaw P gain
*
* Yaw proportional gain, i.e. desired angular speed in rad/s for error 1 rad.
*
* @unit 1/s
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAW_P, 2.0f);
/**
* Yaw rate P gain
*
* Yaw rate proportional gain, i.e. control output for angular speed error 1 rad/s.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAWRATE_P, 0.3f);
/**
* Yaw rate I gain
*
* Yaw rate integral gain. Can be set to compensate static thrust difference or gravity center offset.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAWRATE_I, 0.0f);
/**
* Yaw rate D gain
*
* Yaw rate differential gain. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAWRATE_D, 0.0f);
/**
* Yaw feed forward
*
* Feed forward weight for manual yaw control. 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
*
* @min 0.0
* @max 1.0
* @group Multicopter Attitude Control
*/
PARAM_DEFINE_FLOAT(MC_YAW_FF, 0.5f);

3
src/modules/mc_pos_control/mc_pos_control_main.cpp
View File

@ -51,7 +51,6 @@
#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>
@ -68,7 +67,6 @@
#include <uORB/topics/vehicle_global_velocity_setpoint.h>
#include <systemlib/param/param.h>
#include <systemlib/err.h>
#include <systemlib/pid/pid.h>
#include <systemlib/systemlib.h>
#include <mathlib/mathlib.h>
#include <lib/geo/geo.h>
@ -732,7 +730,6 @@ MulticopterPositionControl::task_main()
} else {
/* run position & altitude controllers, calculate velocity setpoint */
math::Vector<3> pos_err;
float err_x, err_y;
get_vector_to_next_waypoint_fast(_global_pos.lat, _global_pos.lon, _lat_sp, _lon_sp, &pos_err.data[0], &pos_err.data[1]);
pos_err(2) = -(_alt_sp - alt);

146
src/modules/mc_pos_control/mc_pos_control_params.c
View File

@ -39,20 +39,164 @@
#include <systemlib/param/param.h>
PARAM_DEFINE_FLOAT(MPC_THR_MIN, 0.0f);
/**
* Minimum thrust
*
* Minimum vertical thrust. It's recommended to set it > 0 to avoid free fall with zero thrust.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_THR_MIN, 0.1f);
/**
* Maximum thrust
*
* Limit max allowed thrust.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_THR_MAX, 1.0f);
/**
* Proportional gain for vertical position error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_P, 1.0f);
/**
* Proportional gain for vertical velocity error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_P, 0.1f);
/**
* Integral gain for vertical velocity error
*
* Non zero value allows hovering thrust estimation on stabilized or autonomous takeoff.
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_I, 0.02f);
/**
* Differential gain for vertical velocity error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_D, 0.0f);
/**
* Maximum vertical velocity
*
* Maximum vertical velocity in AUTO mode and endpoint for stabilized modes (SEATBELT, EASY).
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_VEL_MAX, 5.0f);
/**
* Vertical velocity feed forward
*
* Feed forward weight for altitude control in stabilized modes (SEATBELT, EASY). 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_Z_FF, 0.5f);
/**
* Proportional gain for horizontal position error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_P, 1.0f);
/**
* Proportional gain for horizontal velocity error
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_P, 0.1f);
/**
* Integral gain for horizontal velocity error
*
* Non-zero value allows to resist wind.
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_I, 0.02f);
/**
* Differential gain for horizontal velocity error. Small values help reduce fast oscillations. If value is too big oscillations will appear again.
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_D, 0.01f);
/**
* Maximum horizontal velocity
*
* Maximum horizontal velocity in AUTO mode and endpoint for position stabilized mode (EASY).
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_VEL_MAX, 5.0f);
/**
* Horizontal velocity feed forward
*
* Feed forward weight for position control in position control mode (EASY). 0 will give slow responce and no overshot, 1 - fast responce and big overshot.
*
* @min 0.0
* @max 1.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_XY_FF, 0.5f);
/**
* Maximum tilt
*
* Limits maximum tilt in AUTO and EASY modes.
*
* @min 0.0
* @max 1.57
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_TILT_MAX, 1.0f);
/**
* Landing descend rate
*
* @min 0.0
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_LAND_SPEED, 1.0f);
/**
* Maximum landing tilt
*
* Limits maximum tilt on landing.
*
* @min 0.0
* @max 1.57
* @group Multicopter Position Control
*/
PARAM_DEFINE_FLOAT(MPC_LAND_TILT, 0.3f);

68
src/modules/navigator/navigator_main.cpp
View File

@ -305,6 +305,12 @@ private:
void start_land();
void start_land_home();
/**
* Fork for state transitions
*/
void request_loiter_or_ready();
void request_mission_if_available();
/**
* Guards offboard mission
*/
@ -699,24 +705,17 @@ Navigator::task_main()
} else {
/* MISSION switch */
if (_vstatus.mission_switch == MISSION_SWITCH_LOITER) {
dispatch(EVENT_LOITER_REQUESTED);
request_loiter_or_ready();
stick_mode = true;
} else if (_vstatus.mission_switch == MISSION_SWITCH_MISSION) {
/* switch to mission only if available */
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_mission_if_available();
stick_mode = true;
}
if (!stick_mode && _vstatus.return_switch == RETURN_SWITCH_NORMAL && myState == NAV_STATE_RTL) {
/* RETURN switch is in normal mode, no MISSION switch mapped, interrupt if in RTL state */
dispatch(EVENT_LOITER_REQUESTED);
request_mission_if_available();
stick_mode = true;
}
}
@ -733,17 +732,11 @@ Navigator::task_main()
break;
case NAV_STATE_LOITER:
dispatch(EVENT_LOITER_REQUESTED);
request_loiter_or_ready();
break;
case NAV_STATE_MISSION:
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_mission_if_available();
break;
case NAV_STATE_RTL:
@ -770,12 +763,7 @@ Navigator::task_main()
} else {
/* on first switch to AUTO try mission by default, if none is available fallback to loiter */
if (myState == NAV_STATE_NONE) {
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_mission_if_available();
}
}
}
@ -1071,7 +1059,7 @@ Navigator::start_loiter()
float min_alt_amsl = _parameters.min_altitude + _home_pos.alt;
/* use current altitude if above min altitude set by parameter */
if (_global_pos.alt < min_alt_amsl) {
if (_global_pos.alt < min_alt_amsl && !_vstatus.is_rotary_wing) {
_pos_sp_triplet.current.alt = min_alt_amsl;
mavlink_log_info(_mavlink_fd, "[navigator] loiter %.1fm higher", (double)(min_alt_amsl - _global_pos.alt));
@ -1397,6 +1385,28 @@ Navigator::set_rtl_item()
_pos_sp_triplet_updated = true;
}
void
Navigator::request_loiter_or_ready()
{
if (_vstatus.condition_landed) {
dispatch(EVENT_READY_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
}
void
Navigator::request_mission_if_available()
{
if (_mission.current_mission_available()) {
dispatch(EVENT_MISSION_REQUESTED);
} else {
request_loiter_or_ready();
}
}
void
Navigator::position_setpoint_from_mission_item(position_setpoint_s *sp, mission_item_s *item)
{
@ -1555,13 +1565,7 @@ Navigator::on_mission_item_reached()
/* loiter at last waypoint */
_reset_loiter_pos = false;
mavlink_log_info(_mavlink_fd, "[navigator] mission completed");
if (_vstatus.condition_landed) {
dispatch(EVENT_READY_REQUESTED);
} else {
dispatch(EVENT_LOITER_REQUESTED);
}
request_loiter_or_ready();
}
} else if (myState == NAV_STATE_RTL) {

47
src/modules/navigator/navigator_params.c
View File

@ -53,68 +53,87 @@
*/
/**
* Minimum altitude
* Minimum altitude (fixed wing only)
*
* Minimum altitude above home for LOITER.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_MIN_ALT, 50.0f);
/**
* Waypoint acceptance radius.
* Waypoint acceptance radius
*
* Default value of acceptance radius (if not specified in mission item).
*
* @unit meters
* @min 0.0
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_ACCEPT_RAD, 10.0f);
/**
* Loiter radius.
* Loiter radius (fixed wing only)
*
* Default value of loiter radius (if not specified in mission item).
*
* @unit meters
* @min 0.0
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_LOITER_RAD, 50.0f);
/**
* Enable onboard mission
*
* @group Navigation
*/
PARAM_DEFINE_INT32(NAV_ONB_MIS_EN, 0);
/**
* Default take-off altitude.
* Take-off altitude
*
* Even if first waypoint has altitude less then NAV_TAKEOFF_ALT above home position, system will climb to NAV_TAKEOFF_ALT on takeoff, then go to waypoint.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_TAKEOFF_ALT, 10.0f); // default TAKEOFF altitude
PARAM_DEFINE_FLOAT(NAV_TAKEOFF_ALT, 10.0f);
/**
* Landing altitude.
* Landing altitude
*
* Slowly descend from this altitude when landing.
* Stay at this altitude above home position after RTL descending. Land (i.e. slowly descend) from this altitude if autolanding allowed.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_LAND_ALT, 5.0f); // slow descend from this altitude when landing
PARAM_DEFINE_FLOAT(NAV_LAND_ALT, 5.0f);
/**
* Return-to-land altitude.
* Return-To-Launch altitude
*
* Minimum altitude for going home in RTL mode.
* Minimum altitude above home position for going home in RTL mode.
*
* @unit meters
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_RTL_ALT, 30.0f); // min altitude for going home in RTL mode
PARAM_DEFINE_FLOAT(NAV_RTL_ALT, 30.0f);
/**
* Return-to-land delay.
* Return-To-Launch delay
*
* Delay after descend before landing.
* Delay after descend before landing in RTL mode.
* If set to -1 the system will not land but loiter at NAV_LAND_ALT.
*
* @unit seconds
* @group Navigation
*/
PARAM_DEFINE_FLOAT(NAV_RTL_LAND_T, -1.0f);
/**
* Enable parachute deployment.
* Enable parachute deployment
*
* @group Navigation
*/

3
src/modules/position_estimator_inav/position_estimator_inav_main.c
View File

@ -42,14 +42,11 @@
#include <stdio.h>
#include <stdbool.h>
#include <fcntl.h>
#include <float.h>
#include <string.h>
#include <nuttx/config.h>
#include <nuttx/sched.h>
#include <sys/prctl.h>
#include <termios.h>
#include <errno.h>
#include <limits.h>
#include <math.h>
#include <uORB/uORB.h>
#include <uORB/topics/parameter_update.h>

34
src/modules/px4iofirmware/dsm.c
View File

@ -1,6 +1,6 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Copyright (c) 2012-2014 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
@ -162,6 +162,7 @@ dsm_guess_format(bool reset)
0xff, /* 8 channels (DX8) */
0x1ff, /* 9 channels (DX9, etc.) */
0x3ff, /* 10 channels (DX10) */
0x1fff, /* 13 channels (DX10t) */
0x3fff /* 18 channels (DX10) */
};
unsigned votes10 = 0;
@ -368,11 +369,25 @@ dsm_decode(hrt_abstime frame_time, uint16_t *values, uint16_t *num_values)
if (channel >= *num_values)
*num_values = channel + 1;
/* convert 0-1024 / 0-2048 values to 1000-2000 ppm encoding in a very sloppy fashion */
if (dsm_channel_shift == 11)
value /= 2;
/* convert 0-1024 / 0-2048 values to 1000-2000 ppm encoding. */
if (dsm_channel_shift == 10)
value *= 2;
value += 998;
/*
* Spektrum scaling is special. There are these basic considerations
*
* * Midpoint is 1520 us
* * 100% travel channels are +- 400 us
*
* We obey the original Spektrum scaling (so a default setup will scale from
* 1100 - 1900 us), but we do not obey the weird 1520 us center point
* and instead (correctly) center the center around 1500 us. This is in order
* to get something useful without requiring the user to calibrate on a digital
* link for no reason.
*/
/* scaled integer for decent accuracy while staying efficient */
value = ((((int)value - 1024) * 1000) / 1700) + 1500;
/*
* Store the decoded channel into the R/C input buffer, taking into
@ -400,6 +415,15 @@ dsm_decode(hrt_abstime frame_time, uint16_t *values, uint16_t *num_values)
values[channel] = value;
}
/*
* Spektrum likes to send junk in higher channel numbers to fill
* their packets. We don't know about a 13 channel model in their TX
* lines, so if we get a channel count of 13, we'll return 12 (the last
* data index that is stable).
*/
if (*num_values == 13)
*num_values = 12;
if (dsm_channel_shift == 11) {
/* Set the 11-bit data indicator */
*num_values |= 0x8000;

2
src/modules/px4iofirmware/mixer.cpp
View File

@ -179,7 +179,7 @@ mixer_tick(void)
((r_setup_arming & PX4IO_P_SETUP_ARMING_FMU_ARMED)
/* and there is valid input via or mixer */ && (r_status_flags & PX4IO_P_STATUS_FLAGS_MIXER_OK) )
/* or direct PWM is set */ || (r_status_flags & PX4IO_P_STATUS_FLAGS_RAW_PWM)
/* or failsafe was set manually */ || (r_setup_arming & PX4IO_P_SETUP_ARMING_FAILSAFE_CUSTOM)
/* or failsafe was set manually */ || ((r_setup_arming & PX4IO_P_SETUP_ARMING_FAILSAFE_CUSTOM) && !(r_status_flags & PX4IO_P_STATUS_FLAGS_FMU_OK))
)
);

2
src/modules/px4iofirmware/registers.c
View File

@ -566,7 +566,7 @@ registers_set_one(uint8_t page, uint8_t offset, uint16_t value)
break;
case PX4IO_P_SETUP_DSM:
dsm_bind(value & 0x0f, (value >> 4) & 7);
dsm_bind(value & 0x0f, (value >> 4) & 0xF);
break;
default: