int fixedwing_att_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[],
struct actuator_controls_s *actuators)
{
static int counter = 0;
static bool initialized = false;
static struct fw_rate_control_params p;
static struct fw_rate_control_param_handles h;
static PID_t roll_rate_controller;
static PID_t pitch_rate_controller;
static PID_t yaw_rate_controller;
static uint64_t last_run = 0;
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
if(!initialized)
{
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the controller layout is with a PI rate controller
pid_init(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0, p.pitchrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the contpitcher layout is with a PI rate contpitcher
pid_init(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, 0, p.yawrate_awu, 1, PID_MODE_DERIVATIV_NONE); // set D part to 0 because the contpitcher layout is with a PI rate contpitcher
initialized = true;
}
/* load new parameters with lower rate */
if (counter % 100 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
pid_set_parameters(&roll_rate_controller, p.rollrate_p, p.rollrate_i, 0, p.rollrate_awu, 1);
pid_set_parameters(&pitch_rate_controller, p.pitchrate_p, p.pitchrate_i, 0, p.pitchrate_awu, 1);
pid_set_parameters(&yaw_rate_controller, p.yawrate_p, p.yawrate_i, 0, p.yawrate_awu, 1);
}
/* 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
counter++;
return 0;
}
void parameters_init()
{
_params_handles.accel_x_offset = param_find("CAL_ACC0_XOFF");
_params_handles.accel_x_scale = param_find("CAL_ACC0_XSCALE");
_params_handles.accel_y_offset = param_find("CAL_ACC0_YOFF");
_params_handles.accel_y_scale = param_find("CAL_ACC0_YSCALE");
_params_handles.accel_z_offset = param_find("CAL_ACC0_ZOFF");
_params_handles.accel_z_scale = param_find("CAL_ACC0_ZSCALE");
_params_handles.gyro_x_offset = param_find("CAL_GYRO0_XOFF");
_params_handles.gyro_x_scale = param_find("CAL_GYRO0_XSCALE");
_params_handles.gyro_y_offset = param_find("CAL_GYRO0_YOFF");
_params_handles.gyro_y_scale = param_find("CAL_GYRO0_YSCALE");
_params_handles.gyro_z_offset = param_find("CAL_GYRO0_ZOFF");
_params_handles.gyro_z_scale = param_find("CAL_GYRO0_ZSCALE");
_params_handles.mag_x_offset = param_find("CAL_MAG0_XOFF");
_params_handles.mag_x_scale = param_find("CAL_MAG0_XSCALE");
_params_handles.mag_y_offset = param_find("CAL_MAG0_YOFF");
_params_handles.mag_y_scale = param_find("CAL_MAG0_YSCALE");
_params_handles.mag_z_offset = param_find("CAL_MAG0_ZOFF");
_params_handles.mag_z_scale = param_find("CAL_MAG0_ZSCALE");
_params_handles.gyro_lpf_enum = param_find("MPU_GYRO_LPF_ENM");
_params_handles.accel_lpf_enum = param_find("MPU_ACC_LPF_ENM");
_params_handles.imu_sample_rate_enum = param_find("MPU_SAMPLE_R_ENM");
parameters_update();
}
estimator_base::estimator_base()
{
_time_to_run = -1;
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_sensor_combined_sub = orb_subscribe(ORB_ID(sensor_combined));
// _airspeed_sub = orb_subscribe(ORB_ID(airspeed));
_gps_sub = orb_subscribe(ORB_ID(vehicle_gps_position));
_gps_init = false;
_baro_init = false;
fds[0].fd = _sensor_combined_sub;
fds[0].events = POLLIN;
poll_error_counter = 0;
memset(&_params, 0, sizeof(_params));
memset(&_sensor_combined, 0, sizeof(_sensor_combined));
memset(&_gps, 0, sizeof(_gps));
memset(&_vehicle_state, 0, sizeof(_vehicle_state));
_params_handles.gravity = param_find("UAVBOOK_GRAVITY");
_params_handles.rho = param_find("UAVBOOK_RHO");
_params_handles.sigma_accel = param_find("UAVBOOK_SIGMA_ACCEL");
_params_handles.sigma_n_gps = param_find("UAVBOOK_SIGMA_N_GPS");
_params_handles.sigma_e_gps = param_find("UAVBOOK_SIGMA_E_GPS");
_params_handles.sigma_Vg_gps = param_find("UAVBOOK_SIGMA_VG_GPS");
_params_handles.sigma_course_gps = param_find("UAVBOOK_SIGMA_COURSE_GPS");
parameters_update();
_vehicle_state_pub = orb_advertise(ORB_ID(vehicle_state), &_vehicle_state);
}
int fixedwing_att_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att,
struct vehicle_rates_setpoint_s *rates_sp)
{
static int counter = 0;
static bool initialized = false;
static struct fw_att_control_params p;
static struct fw_pos_control_param_handles h;
static PID_t roll_controller;
static PID_t pitch_controller;
if(!initialized)
{
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim, PID_MODE_DERIVATIV_NONE); //P Controller
pid_init(&pitch_controller, p.pitch_p, 0, 0, 0, p.pitchrate_lim, PID_MODE_DERIVATIV_NONE); //P Controller
initialized = true;
}
/* load new parameters with lower rate */
if (counter % 100 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
pid_set_parameters(&roll_controller, p.roll_p, 0, 0, 0, p.rollrate_lim);
pid_set_parameters(&pitch_controller, p.pitch_p, 0, 0, 0, p.pitchrate_lim);
}
/* Roll (P) */
rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_tait_bryan, att->roll, 0, 0);
/* Pitch (P) */
float pitch_sp_rollcompensation = att_sp->pitch_tait_bryan + p.pitch_roll_compensation_p * att_sp->roll_tait_bryan;
rates_sp->pitch = pid_calculate(&pitch_controller, pitch_sp_rollcompensation, att->pitch, 0, 0);
/* Yaw (from coordinated turn constraint or lateral force) */
//TODO
counter++;
return 0;
}
void path_follower_base::parameter_update_poll()
{
bool updated;
/* Check if param status has changed */
orb_check(_params_sub, &updated);
if (updated) {
struct parameter_update_s param_update;
orb_copy(ORB_ID(parameter_update), _params_sub, ¶m_update);
parameters_update();
}
}
void
MulticopterAttitudeControl::parameter_update_poll()
{
bool updated;
/* Check HIL state if vehicle status has changed */
orb_check(_params_sub, &updated);
if (updated) {
struct parameter_update_s param_update;
orb_copy(ORB_ID(parameter_update), _params_sub, ¶m_update);
parameters_update();
}
}
/**
* Check for parameter updates.
*/
void
VtolAttitudeControl::parameters_update_poll()
{
bool updated;
/* Check if parameters have changed */
orb_check(_params_sub, &updated);
if (updated) {
struct parameter_update_s param_update;
orb_copy(ORB_ID(parameter_update), _params_sub, ¶m_update);
parameters_update();
}
}
GroundRoverAttitudeControl::GroundRoverAttitudeControl() :
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "gnda_dt")),
_nonfinite_input_perf(perf_alloc(PC_COUNT, "gnda_nani")),
_nonfinite_output_perf(perf_alloc(PC_COUNT, "gnda_nano"))
{
_parameter_handles.w_p = param_find("GND_WR_P");
_parameter_handles.w_i = param_find("GND_WR_I");
_parameter_handles.w_d = param_find("GND_WR_D");
_parameter_handles.w_imax = param_find("GND_WR_IMAX");
_parameter_handles.trim_yaw = param_find("TRIM_YAW");
_parameter_handles.man_yaw_scale = param_find("GND_MAN_Y_SC");
_parameter_handles.bat_scale_en = param_find("GND_BAT_SCALE_EN");
/* fetch initial parameter values */
parameters_update();
}
/**
* Constructor
*/
VtolAttitudeControl::VtolAttitudeControl()
{
_vtol_vehicle_status.vtol_in_rw_mode = true; /* start vtol in rotary wing mode*/
_params.idle_pwm_mc = PWM_DEFAULT_MIN;
_params.vtol_motor_count = 0;
_params_handles.idle_pwm_mc = param_find("VT_IDLE_PWM_MC");
_params_handles.vtol_motor_count = param_find("VT_MOT_COUNT");
_params_handles.vtol_fw_permanent_stab = param_find("VT_FW_PERM_STAB");
_params_handles.fw_pitch_trim = param_find("VT_FW_PITCH_TRIM");
_params_handles.vtol_type = param_find("VT_TYPE");
_params_handles.elevons_mc_lock = param_find("VT_ELEV_MC_LOCK");
_params_handles.fw_min_alt = param_find("VT_FW_MIN_ALT");
_params_handles.fw_alt_err = param_find("VT_FW_ALT_ERR");
_params_handles.fw_qc_max_pitch = param_find("VT_FW_QC_P");
_params_handles.fw_qc_max_roll = param_find("VT_FW_QC_R");
_params_handles.front_trans_time_openloop = param_find("VT_F_TR_OL_TM");
_params_handles.front_trans_time_min = param_find("VT_TRANS_MIN_TM");
_params_handles.wv_takeoff = param_find("VT_WV_TKO_EN");
_params_handles.wv_land = param_find("VT_WV_LND_EN");
_params_handles.wv_loiter = param_find("VT_WV_LTR_EN");
/* fetch initial parameter values */
parameters_update();
if (_params.vtol_type == vtol_type::TAILSITTER) {
_vtol_type = new Tailsitter(this);
} else if (_params.vtol_type == vtol_type::TILTROTOR) {
_vtol_type = new Tiltrotor(this);
} else if (_params.vtol_type == vtol_type::STANDARD) {
_vtol_type = new Standard(this);
} else {
_task_should_exit = true;
}
}
path_follower_base::path_follower_base()
{
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_vehicle_state_sub = orb_subscribe(ORB_ID(vehicle_state));
_current_path_sub = orb_subscribe(ORB_ID(current_path));
fds[0].fd = _vehicle_state_sub;
fds[0].events = POLLIN;
poll_error_counter = 0;
memset(&_vehicle_state, 0, sizeof(_vehicle_state));
memset(&_current_path, 0, sizeof(_current_path));
memset(&_controller_commands, 0, sizeof(_controller_commands));
memset(&_params, 0, sizeof(_params));
_params_handles.chi_infty = param_find("UAVBOOK_CHI_INFTY");
_params_handles.k_path = param_find("UAVBOOK_K_PATH");
_params_handles.k_orbit = param_find("UAVBOOK_K_ORBIT");
parameters_update();
_controller_commands_pub = orb_advertise(ORB_ID(controller_commands), &_controller_commands);
}
void
FixedwingAttitudeControl::task_main()
{
/* inform about start */
warnx("Initializing..");
fflush(stdout);
/*
* do subscriptions
*/
_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
_accel_sub = orb_subscribe(ORB_ID(sensor_accel));
_airspeed_sub = orb_subscribe(ORB_ID(airspeed));
_vcontrol_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
/* rate limit vehicle status updates to 5Hz */
orb_set_interval(_vcontrol_mode_sub, 200);
/* rate limit attitude control to 50 Hz (with some margin, so 17 ms) */
orb_set_interval(_att_sub, 17);
parameters_update();
/* get an initial update for all sensor and status data */
vehicle_airspeed_poll();
vehicle_setpoint_poll();
vehicle_accel_poll();
vehicle_control_mode_poll();
vehicle_manual_poll();
/* wakeup source(s) */
struct pollfd fds[2];
/* Setup of loop */
fds[0].fd = _params_sub;
fds[0].events = POLLIN;
fds[1].fd = _att_sub;
fds[1].events = POLLIN;
while (!_task_should_exit) {
static int loop_counter = 0;
/* wait for up to 500ms for data */
int pret = poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);
/* timed out - periodic check for _task_should_exit, etc. */
if (pret == 0)
continue;
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
continue;
}
perf_begin(_loop_perf);
/* 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), _params_sub, &update);
/* update parameters from storage */
parameters_update();
}
/* only run controller if attitude changed */
if (fds[1].revents & POLLIN) {
static uint64_t last_run = 0;
float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* guard against too large deltaT's */
if (deltaT > 1.0f)
deltaT = 0.01f;
/* load local copies */
orb_copy(ORB_ID(vehicle_attitude), _att_sub, &_att);
vehicle_airspeed_poll();
vehicle_setpoint_poll();
vehicle_accel_poll();
vehicle_control_mode_poll();
vehicle_manual_poll();
global_pos_poll();
/* lock integrator until control is started */
bool lock_integrator;
if (_vcontrol_mode.flag_control_attitude_enabled) {
lock_integrator = false;
} else {
lock_integrator = true;
}
/* Simple handling of failsafe: deploy parachute if failsafe is on */
if (_vcontrol_mode.flag_control_termination_enabled) {
_actuators_airframe.control[1] = 1.0f;
// warnx("_actuators_airframe.control[1] = 1.0f;");
} else {
_actuators_airframe.control[1] = 0.0f;
// warnx("_actuators_airframe.control[1] = -1.0f;");
}
/* decide if in stabilized or full manual control */
if (_vcontrol_mode.flag_control_attitude_enabled) {
/* scale around tuning airspeed */
float airspeed;
/* if airspeed is not updating, we assume the normal average speed */
if (bool nonfinite = !isfinite(_airspeed.true_airspeed_m_s) ||
hrt_elapsed_time(&_airspeed.timestamp) > 1e6) {
airspeed = _parameters.airspeed_trim;
if (nonfinite) {
perf_count(_nonfinite_input_perf);
}
} else {
airspeed = _airspeed.true_airspeed_m_s;
}
/*
* For scaling our actuators using anything less than the min (close to stall)
* speed doesn't make any sense - its the strongest reasonable deflection we
* want to do in flight and its the baseline a human pilot would choose.
*
* Forcing the scaling to this value allows reasonable handheld tests.
*/
float airspeed_scaling = _parameters.airspeed_trim / ((airspeed < _parameters.airspeed_min) ? _parameters.airspeed_min : airspeed);
float roll_sp = _parameters.rollsp_offset_rad;
float pitch_sp = _parameters.pitchsp_offset_rad;
float throttle_sp = 0.0f;
if (_vcontrol_mode.flag_control_velocity_enabled || _vcontrol_mode.flag_control_position_enabled) {
/* read in attitude setpoint from attitude setpoint uorb topic */
roll_sp = _att_sp.roll_body + _parameters.rollsp_offset_rad;
pitch_sp = _att_sp.pitch_body + _parameters.pitchsp_offset_rad;
throttle_sp = _att_sp.thrust;
/* reset integrals where needed */
if (_att_sp.roll_reset_integral) {
_roll_ctrl.reset_integrator();
}
if (_att_sp.pitch_reset_integral) {
_pitch_ctrl.reset_integrator();
}
if (_att_sp.yaw_reset_integral) {
_yaw_ctrl.reset_integrator();
}
} else {
/*
* Scale down roll and pitch as the setpoints are radians
* and a typical remote can only do around 45 degrees, the mapping is
* -1..+1 to -man_roll_max rad..+man_roll_max rad (equivalent for pitch)
*
* With this mapping the stick angle is a 1:1 representation of
* the commanded attitude.
*
* The trim gets subtracted here from the manual setpoint to get
* the intended attitude setpoint. Later, after the rate control step the
* trim is added again to the control signal.
*/
roll_sp = (_manual.y * _parameters.man_roll_max - _parameters.trim_roll)
+ _parameters.rollsp_offset_rad;
pitch_sp = -(_manual.x * _parameters.man_pitch_max - _parameters.trim_pitch)
+ _parameters.pitchsp_offset_rad;
throttle_sp = _manual.z;
_actuators.control[4] = _manual.flaps;
/*
* in manual mode no external source should / does emit attitude setpoints.
* emit the manual setpoint here to allow attitude controller tuning
* in attitude control mode.
*/
struct vehicle_attitude_setpoint_s att_sp;
att_sp.timestamp = hrt_absolute_time();
att_sp.roll_body = roll_sp;
att_sp.pitch_body = pitch_sp;
att_sp.yaw_body = 0.0f - _parameters.trim_yaw;
att_sp.thrust = throttle_sp;
/* lazily publish the setpoint only once available */
if (_attitude_sp_pub > 0) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_attitude_setpoint), _attitude_sp_pub, &att_sp);
} else {
/* advertise and publish */
_attitude_sp_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &att_sp);
}
}
/* Prepare speed_body_u and speed_body_w */
float speed_body_u = 0.0f;
float speed_body_v = 0.0f;
float speed_body_w = 0.0f;
if(_att.R_valid) {
speed_body_u = _att.R[0][0] * _global_pos.vel_n + _att.R[1][0] * _global_pos.vel_e + _att.R[2][0] * _global_pos.vel_d;
speed_body_v = _att.R[0][1] * _global_pos.vel_n + _att.R[1][1] * _global_pos.vel_e + _att.R[2][1] * _global_pos.vel_d;
speed_body_w = _att.R[0][2] * _global_pos.vel_n + _att.R[1][2] * _global_pos.vel_e + _att.R[2][2] * _global_pos.vel_d;
} else {
if (loop_counter % 10 == 0) {
warnx("Did not get a valid R\n");
}
}
/* Run attitude controllers */
if (isfinite(roll_sp) && isfinite(pitch_sp)) {
_roll_ctrl.control_attitude(roll_sp, _att.roll);
_pitch_ctrl.control_attitude(pitch_sp, _att.roll, _att.pitch, airspeed);
_yaw_ctrl.control_attitude(_att.roll, _att.pitch,
speed_body_u, speed_body_v, speed_body_w,
_roll_ctrl.get_desired_rate(), _pitch_ctrl.get_desired_rate()); //runs last, because is depending on output of roll and pitch attitude
/* Run attitude RATE controllers which need the desired attitudes from above, add trim */
float roll_u = _roll_ctrl.control_bodyrate(_att.pitch,
_att.rollspeed, _att.yawspeed,
_yaw_ctrl.get_desired_rate(),
_parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator);
_actuators.control[0] = (isfinite(roll_u)) ? roll_u + _parameters.trim_roll : _parameters.trim_roll;
if (!isfinite(roll_u)) {
_roll_ctrl.reset_integrator();
perf_count(_nonfinite_output_perf);
if (loop_counter % 10 == 0) {
warnx("roll_u %.4f", (double)roll_u);
}
}
float pitch_u = _pitch_ctrl.control_bodyrate(_att.roll, _att.pitch,
_att.pitchspeed, _att.yawspeed,
_yaw_ctrl.get_desired_rate(),
_parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator);
_actuators.control[1] = (isfinite(pitch_u)) ? pitch_u + _parameters.trim_pitch : _parameters.trim_pitch;
if (!isfinite(pitch_u)) {
_pitch_ctrl.reset_integrator();
perf_count(_nonfinite_output_perf);
if (loop_counter % 10 == 0) {
warnx("pitch_u %.4f, _yaw_ctrl.get_desired_rate() %.4f,"
" airspeed %.4f, airspeed_scaling %.4f,"
" roll_sp %.4f, pitch_sp %.4f,"
" _roll_ctrl.get_desired_rate() %.4f,"
" _pitch_ctrl.get_desired_rate() %.4f"
" att_sp.roll_body %.4f",
(double)pitch_u, (double)_yaw_ctrl.get_desired_rate(),
(double)airspeed, (double)airspeed_scaling,
(double)roll_sp, (double)pitch_sp,
(double)_roll_ctrl.get_desired_rate(),
(double)_pitch_ctrl.get_desired_rate(),
(double)_att_sp.roll_body);
}
}
float yaw_u = _yaw_ctrl.control_bodyrate(_att.roll, _att.pitch,
_att.pitchspeed, _att.yawspeed,
_pitch_ctrl.get_desired_rate(),
_parameters.airspeed_min, _parameters.airspeed_max, airspeed, airspeed_scaling, lock_integrator);
_actuators.control[2] = (isfinite(yaw_u)) ? yaw_u + _parameters.trim_yaw : _parameters.trim_yaw;
if (!isfinite(yaw_u)) {
_yaw_ctrl.reset_integrator();
perf_count(_nonfinite_output_perf);
if (loop_counter % 10 == 0) {
warnx("yaw_u %.4f", (double)yaw_u);
}
}
/* throttle passed through */
_actuators.control[3] = (isfinite(throttle_sp)) ? throttle_sp : 0.0f;
if (!isfinite(throttle_sp)) {
if (loop_counter % 10 == 0) {
warnx("throttle_sp %.4f", (double)throttle_sp);
}
}
} else {
perf_count(_nonfinite_input_perf);
if (loop_counter % 10 == 0) {
warnx("Non-finite setpoint roll_sp: %.4f, pitch_sp %.4f", (double)roll_sp, (double)pitch_sp);
}
}
/*
* Lazily publish the rate setpoint (for analysis, the actuators are published below)
* only once available
*/
vehicle_rates_setpoint_s rates_sp;
rates_sp.roll = _roll_ctrl.get_desired_rate();
rates_sp.pitch = _pitch_ctrl.get_desired_rate();
rates_sp.yaw = _yaw_ctrl.get_desired_rate();
rates_sp.timestamp = hrt_absolute_time();
if (_rate_sp_pub > 0) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_rates_setpoint), _rate_sp_pub, &rates_sp);
} else {
/* advertise and publish */
_rate_sp_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint), &rates_sp);
}
} else {
/* manual/direct control */
_actuators.control[0] = _manual.y;
_actuators.control[1] = -_manual.x;
_actuators.control[2] = _manual.r;
_actuators.control[3] = _manual.z;
_actuators.control[4] = _manual.flaps;
}
_actuators.control[5] = _manual.aux1;
_actuators.control[6] = _manual.aux2;
_actuators.control[7] = _manual.aux3;
/* lazily publish the setpoint only once available */
_actuators.timestamp = hrt_absolute_time();
_actuators_airframe.timestamp = hrt_absolute_time();
if (_actuators_0_pub > 0) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(actuator_controls_0), _actuators_0_pub, &_actuators);
} else {
/* advertise and publish */
_actuators_0_pub = orb_advertise(ORB_ID(actuator_controls_0), &_actuators);
}
if (_actuators_1_pub > 0) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(actuator_controls_1), _actuators_1_pub, &_actuators_airframe);
// warnx("%.2f %.2f %.2f %.2f %.2f %.2f %.2f %.2f",
// (double)_actuators_airframe.control[0], (double)_actuators_airframe.control[1], (double)_actuators_airframe.control[2],
// (double)_actuators_airframe.control[3], (double)_actuators_airframe.control[4], (double)_actuators_airframe.control[5],
// (double)_actuators_airframe.control[6], (double)_actuators_airframe.control[7]);
} else {
/* advertise and publish */
_actuators_1_pub = orb_advertise(ORB_ID(actuator_controls_1), &_actuators_airframe);
}
}
loop_counter++;
perf_end(_loop_perf);
}
warnx("exiting.\n");
_control_task = -1;
_exit(0);
}
MulticopterAttitudeControl::MulticopterAttitudeControl() :
_task_should_exit(false),
_control_task(-1),
/* subscriptions */
_v_att_sub(-1),
_v_att_sp_sub(-1),
_v_control_mode_sub(-1),
_params_sub(-1),
_manual_control_sp_sub(-1),
_armed_sub(-1),
/* publications */
_att_sp_pub(-1),
_v_rates_sp_pub(-1),
_actuators_0_pub(-1),
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "mc_att_control"))
{
memset(&_v_att, 0, sizeof(_v_att));
memset(&_v_att_sp, 0, sizeof(_v_att_sp));
memset(&_v_rates_sp, 0, sizeof(_v_rates_sp));
memset(&_manual_control_sp, 0, sizeof(_manual_control_sp));
memset(&_v_control_mode, 0, sizeof(_v_control_mode));
memset(&_actuators, 0, sizeof(_actuators));
memset(&_armed, 0, sizeof(_armed));
_params.att_p.zero();
_params.rate_p.zero();
_params.rate_i.zero();
_params.rate_d.zero();
_params.yaw_ff = 0.0f;
_params.yaw_rate_max = 0.0f;
_params.man_roll_max = 0.0f;
_params.man_pitch_max = 0.0f;
_params.man_yaw_max = 0.0f;
_rates_prev.zero();
_rates_sp.zero();
_rates_int.zero();
_thrust_sp = 0.0f;
_att_control.zero();
_I.identity();
_params_handles.roll_p = param_find("MC_ROLL_P");
_params_handles.roll_rate_p = param_find("MC_ROLLRATE_P");
_params_handles.roll_rate_i = param_find("MC_ROLLRATE_I");
_params_handles.roll_rate_d = param_find("MC_ROLLRATE_D");
_params_handles.pitch_p = param_find("MC_PITCH_P");
_params_handles.pitch_rate_p = param_find("MC_PITCHRATE_P");
_params_handles.pitch_rate_i = param_find("MC_PITCHRATE_I");
_params_handles.pitch_rate_d = param_find("MC_PITCHRATE_D");
_params_handles.yaw_p = param_find("MC_YAW_P");
_params_handles.yaw_rate_p = param_find("MC_YAWRATE_P");
_params_handles.yaw_rate_i = param_find("MC_YAWRATE_I");
_params_handles.yaw_rate_d = param_find("MC_YAWRATE_D");
_params_handles.yaw_ff = param_find("MC_YAW_FF");
_params_handles.yaw_rate_max = param_find("MC_YAWRATE_MAX");
_params_handles.man_roll_max = param_find("MC_MAN_R_MAX");
_params_handles.man_pitch_max = param_find("MC_MAN_P_MAX");
_params_handles.man_yaw_max = param_find("MC_MAN_Y_MAX");
/* fetch initial parameter values */
parameters_update();
}
/*
* EKF Attitude Estimator main function.
*
* Estimates the attitude recursively once started.
*
* @param argc number of commandline arguments (plus command name)
* @param argv strings containing the arguments
*/
int attitude_estimator_ekf_thread_main(int argc, char *argv[])
{
const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
float dt = 0.005f;
/* state vector x has the following entries [ax,ay,az||mx,my,mz||wox,woy,woz||wx,wy,wz]' */
float z_k[9] = {0.0f, 0.0f, 0.0f, 0.0f, 0.0f, 9.81f, 0.2f, -0.2f, 0.2f}; /**< Measurement vector */
float x_aposteriori_k[12]; /**< states */
float P_aposteriori_k[144] = {100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 100.0f, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 100.0f, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 0, 100.0f,
}; /**< init: diagonal matrix with big values */
float x_aposteriori[12];
float P_aposteriori[144];
/* output euler angles */
float euler[3] = {0.0f, 0.0f, 0.0f};
float Rot_matrix[9] = {1.f, 0, 0,
0, 1.f, 0,
0, 0, 1.f
}; /**< init: identity matrix */
// print text
printf("Extended Kalman Filter Attitude Estimator initialized..\n\n");
fflush(stdout);
int overloadcounter = 19;
/* Initialize filter */
attitudeKalmanfilter_initialize();
/* store start time to guard against too slow update rates */
uint64_t last_run = hrt_absolute_time();
struct sensor_combined_s raw;
memset(&raw, 0, sizeof(raw));
struct vehicle_gps_position_s gps;
memset(&gps, 0, sizeof(gps));
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_control_mode_s control_mode;
memset(&control_mode, 0, sizeof(control_mode));
struct vehicle_vicon_position_s vicon_pos; // Added by Ross Allen
memset(&vicon_pos, 0, sizeof(vicon_pos));
uint64_t last_data = 0;
uint64_t last_measurement = 0;
uint64_t last_vel_t = 0;
/* Vicon parameters - Added by Ross Allen */
bool vicon_valid = false;
//~ static const hrt_abstime vicon_topic_timeout = 500000; // vicon topic timeout = 0.25s
/* current velocity */
math::Vector<3> vel;
vel.zero();
/* previous velocity */
math::Vector<3> vel_prev;
vel_prev.zero();
/* actual acceleration (by GPS velocity) in body frame */
math::Vector<3> acc;
acc.zero();
/* rotation matrix */
math::Matrix<3, 3> R;
R.identity();
/* subscribe to raw data */
int sub_raw = orb_subscribe(ORB_ID(sensor_combined));
/* rate-limit raw data updates to 333 Hz (sensors app publishes at 200, so this is just paranoid) */
orb_set_interval(sub_raw, 3);
/* subscribe to GPS */
int sub_gps = orb_subscribe(ORB_ID(vehicle_gps_position));
/* subscribe to GPS */
int sub_global_pos = orb_subscribe(ORB_ID(vehicle_global_position));
/* subscribe to param changes */
int sub_params = orb_subscribe(ORB_ID(parameter_update));
/* subscribe to control mode*/
int sub_control_mode = orb_subscribe(ORB_ID(vehicle_control_mode));
/* subscribe to vicon position */
int vehicle_vicon_position_sub = orb_subscribe(ORB_ID(vehicle_vicon_position)); // Added by Ross Allen
/* advertise attitude */
orb_advert_t pub_att = orb_advertise(ORB_ID(vehicle_attitude), &att);
int loopcounter = 0;
thread_running = true;
/* advertise debug value */
// struct debug_key_value_s dbg = { .key = "", .value = 0.0f };
// orb_advert_t pub_dbg = -1;
/* keep track of sensor updates */
uint64_t sensor_last_timestamp[3] = {0, 0, 0};
struct attitude_estimator_ekf_params ekf_params;
struct attitude_estimator_ekf_param_handles ekf_param_handles;
/* initialize parameter handles */
parameters_init(&ekf_param_handles);
bool initialized = false;
float gyro_offsets[3] = { 0.0f, 0.0f, 0.0f };
/* magnetic declination, in radians */
float mag_decl = 0.0f;
/* rotation matrix for magnetic declination */
math::Matrix<3, 3> R_decl;
R_decl.identity();
/* register the perf counter */
perf_counter_t ekf_loop_perf = perf_alloc(PC_ELAPSED, "attitude_estimator_ekf");
/* Main loop*/
while (!thread_should_exit) {
struct pollfd fds[2];
fds[0].fd = sub_raw;
fds[0].events = POLLIN;
fds[1].fd = sub_params;
fds[1].events = POLLIN;
int ret = poll(fds, 2, 1000);
/* Added by Ross Allen */
//~ hrt_abstime t = hrt_absolute_time();
bool updated;
if (ret < 0) {
/* XXX this is seriously bad - should be an emergency */
} else if (ret == 0) {
/* check if we're in HIL - not getting sensor data is fine then */
orb_copy(ORB_ID(vehicle_control_mode), sub_control_mode, &control_mode);
if (!control_mode.flag_system_hil_enabled) {
fprintf(stderr,
"[att ekf] WARNING: Not getting sensors - sensor app running?\n");
}
} else {
/* only update parameters if they changed */
if (fds[1].revents & POLLIN) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), sub_params, &update);
/* update parameters */
parameters_update(&ekf_param_handles, &ekf_params);
}
/* only run filter if sensor values changed */
if (fds[0].revents & POLLIN) {
/* get latest measurements */
orb_copy(ORB_ID(sensor_combined), sub_raw, &raw);
bool gps_updated;
orb_check(sub_gps, &gps_updated);
if (gps_updated) {
orb_copy(ORB_ID(vehicle_gps_position), sub_gps, &gps);
if (gps.eph < 20.0f && hrt_elapsed_time(&gps.timestamp_position) < 1000000) {
mag_decl = math::radians(get_mag_declination(gps.lat / 1e7f, gps.lon / 1e7f));
/* update mag declination rotation matrix */
R_decl.from_euler(0.0f, 0.0f, mag_decl);
}
}
bool global_pos_updated;
orb_check(sub_global_pos, &global_pos_updated);
if (global_pos_updated) {
orb_copy(ORB_ID(vehicle_global_position), sub_global_pos, &global_pos);
}
if (!initialized) {
// XXX disabling init for now
initialized = true;
// gyro_offsets[0] += raw.gyro_rad_s[0];
// gyro_offsets[1] += raw.gyro_rad_s[1];
// gyro_offsets[2] += raw.gyro_rad_s[2];
// offset_count++;
// if (hrt_absolute_time() - start_time > 3000000LL) {
// initialized = true;
// gyro_offsets[0] /= offset_count;
// gyro_offsets[1] /= offset_count;
// gyro_offsets[2] /= offset_count;
// }
} else {
perf_begin(ekf_loop_perf);
/* Calculate data time difference in seconds */
dt = (raw.timestamp - last_measurement) / 1000000.0f;
last_measurement = raw.timestamp;
uint8_t update_vect[3] = {0, 0, 0};
/* Fill in gyro measurements */
if (sensor_last_timestamp[0] != raw.timestamp) {
update_vect[0] = 1;
// sensor_update_hz[0] = 1e6f / (raw.timestamp - sensor_last_timestamp[0]);
sensor_last_timestamp[0] = raw.timestamp;
}
z_k[0] = raw.gyro_rad_s[0] - gyro_offsets[0];
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_timestamp[1] != raw.accelerometer_timestamp) {
update_vect[1] = 1;
// sensor_update_hz[1] = 1e6f / (raw.timestamp - sensor_last_timestamp[1]);
sensor_last_timestamp[1] = raw.accelerometer_timestamp;
}
hrt_abstime vel_t = 0;
bool vel_valid = false;
if (ekf_params.acc_comp == 1 && gps.fix_type >= 3 && gps.eph < 10.0f && gps.vel_ned_valid && hrt_absolute_time() < gps.timestamp_velocity + 500000) {
vel_valid = true;
if (gps_updated) {
vel_t = gps.timestamp_velocity;
vel(0) = gps.vel_n_m_s;
vel(1) = gps.vel_e_m_s;
vel(2) = gps.vel_d_m_s;
}
} else if (ekf_params.acc_comp == 2 && gps.eph < 5.0f && global_pos.timestamp != 0 && hrt_absolute_time() < global_pos.timestamp + 20000) {
vel_valid = true;
if (global_pos_updated) {
vel_t = global_pos.timestamp;
vel(0) = global_pos.vel_n;
vel(1) = global_pos.vel_e;
vel(2) = global_pos.vel_d;
}
}
if (vel_valid) {
/* velocity is valid */
if (vel_t != 0) {
/* velocity updated */
if (last_vel_t != 0 && vel_t != last_vel_t) {
float vel_dt = (vel_t - last_vel_t) / 1000000.0f;
/* calculate acceleration in body frame */
acc = R.transposed() * ((vel - vel_prev) / vel_dt);
}
last_vel_t = vel_t;
vel_prev = vel;
}
} else {
/* velocity is valid, reset acceleration */
acc.zero();
vel_prev.zero();
last_vel_t = 0;
}
z_k[3] = raw.accelerometer_m_s2[0] - acc(0);
z_k[4] = raw.accelerometer_m_s2[1] - acc(1);
z_k[5] = raw.accelerometer_m_s2[2] - acc(2);
/* update magnetometer measurements */
if (sensor_last_timestamp[2] != raw.magnetometer_timestamp) {
update_vect[2] = 1;
// sensor_update_hz[2] = 1e6f / (raw.timestamp - sensor_last_timestamp[2]);
sensor_last_timestamp[2] = raw.magnetometer_timestamp;
}
z_k[6] = raw.magnetometer_ga[0];
z_k[7] = raw.magnetometer_ga[1];
z_k[8] = raw.magnetometer_ga[2];
uint64_t now = hrt_absolute_time();
unsigned int time_elapsed = now - last_run;
last_run = now;
if (time_elapsed > loop_interval_alarm) {
//TODO: add warning, cpu overload here
// if (overloadcounter == 20) {
// printf("CPU OVERLOAD DETECTED IN ATTITUDE ESTIMATOR EKF (%lu > %lu)\n", time_elapsed, loop_interval_alarm);
// overloadcounter = 0;
// }
overloadcounter++;
}
static bool const_initialized = false;
/* initialize with good values once we have a reasonable dt estimate */
if (!const_initialized && dt < 0.05f && dt > 0.001f) {
dt = 0.005f;
parameters_update(&ekf_param_handles, &ekf_params);
/* update mag declination rotation matrix */
if (gps.eph < 20.0f && hrt_elapsed_time(&gps.timestamp_position) < 1000000) {
mag_decl = math::radians(get_mag_declination(gps.lat / 1e7f, gps.lon / 1e7f));
} else {
mag_decl = ekf_params.mag_decl;
}
/* update mag declination rotation matrix */
R_decl.from_euler(0.0f, 0.0f, mag_decl);
x_aposteriori_k[0] = z_k[0];
x_aposteriori_k[1] = z_k[1];
x_aposteriori_k[2] = z_k[2];
x_aposteriori_k[3] = 0.0f;
x_aposteriori_k[4] = 0.0f;
x_aposteriori_k[5] = 0.0f;
x_aposteriori_k[6] = z_k[3];
x_aposteriori_k[7] = z_k[4];
x_aposteriori_k[8] = z_k[5];
x_aposteriori_k[9] = z_k[6];
x_aposteriori_k[10] = z_k[7];
x_aposteriori_k[11] = z_k[8];
const_initialized = true;
}
/* do not execute the filter if not initialized */
if (!const_initialized) {
continue;
}
attitudeKalmanfilter(update_vect, dt, z_k, x_aposteriori_k, P_aposteriori_k, ekf_params.q, ekf_params.r,
euler, Rot_matrix, x_aposteriori, P_aposteriori);
/* swap values for next iteration, check for fatal inputs */
if (isfinite(euler[0]) && isfinite(euler[1]) && isfinite(euler[2])) {
memcpy(P_aposteriori_k, P_aposteriori, sizeof(P_aposteriori_k));
memcpy(x_aposteriori_k, x_aposteriori, sizeof(x_aposteriori_k));
} else {
/* due to inputs or numerical failure the output is invalid, skip it */
continue;
}
if (last_data > 0 && raw.timestamp - last_data > 30000)
printf("[attitude estimator ekf] sensor data missed! (%llu)\n", raw.timestamp - last_data);
last_data = raw.timestamp;
/* Check Vicon for attitude data*/
/* Added by Ross Allen */
orb_check(vehicle_vicon_position_sub, &updated);
if (updated) {
orb_copy(ORB_ID(vehicle_vicon_position), vehicle_vicon_position_sub, &vicon_pos);
vicon_valid = vicon_pos.valid;
}
//~ if (vicon_valid && (t > (vicon_pos.timestamp + vicon_topic_timeout))) {
//~ vicon_valid = false;
//~ warnx("VICON timeout");
//~ }
/* send out */
att.timestamp = raw.timestamp;
att.roll = euler[0];
att.pitch = euler[1];
att.yaw = euler[2] + mag_decl;
/* Use vicon yaw if valid and just overwrite*/
/* Added by Ross Allen */
if(vicon_valid) {
att.yaw = vicon_pos.yaw;
}
att.rollspeed = x_aposteriori[0];
att.pitchspeed = x_aposteriori[1];
att.yawspeed = x_aposteriori[2];
att.rollacc = x_aposteriori[3];
att.pitchacc = x_aposteriori[4];
att.yawacc = x_aposteriori[5];
att.g_comp[0] = raw.accelerometer_m_s2[0] - acc(0);
att.g_comp[1] = raw.accelerometer_m_s2[1] - acc(1);
att.g_comp[2] = raw.accelerometer_m_s2[2] - acc(2);
/* copy offsets */
memcpy(&att.rate_offsets, &(x_aposteriori[3]), sizeof(att.rate_offsets));
/* magnetic declination */
math::Matrix<3, 3> R_body = (&Rot_matrix[0]);
R = R_decl * R_body;
/* copy rotation matrix */
memcpy(&att.R[0][0], &R.data[0][0], sizeof(att.R));
att.R_valid = true;
if (isfinite(att.roll) && isfinite(att.pitch) && isfinite(att.yaw)) {
// Broadcast
orb_publish(ORB_ID(vehicle_attitude), pub_att, &att);
} else {
warnx("NaN in roll/pitch/yaw estimate!");
}
perf_end(ekf_loop_perf);
}
}
}
loopcounter++;
}
thread_running = false;
return 0;
}
void Tiltrotor::update_vtol_state()
{
parameters_update();
/* simple logic using a two way switch to perform transitions.
* after flipping the switch the vehicle will start tilting rotors, picking up
* forward speed. After the vehicle has picked up enough speed the rotors are tilted
* forward completely. For the backtransition the motors simply rotate back.
*/
if (!_attc->is_fixed_wing_requested()) {
// plane is in multicopter mode
switch (_vtol_schedule.flight_mode) {
case MC_MODE:
break;
case FW_MODE:
_vtol_schedule.flight_mode = TRANSITION_BACK;
_vtol_schedule.transition_start = hrt_absolute_time();
break;
case TRANSITION_FRONT_P1:
// failsafe into multicopter mode
_vtol_schedule.flight_mode = MC_MODE;
break;
case TRANSITION_FRONT_P2:
// failsafe into multicopter mode
_vtol_schedule.flight_mode = MC_MODE;
break;
case TRANSITION_BACK:
if (_tilt_control <= _params_tiltrotor.tilt_mc) {
_vtol_schedule.flight_mode = MC_MODE;
}
break;
}
} else {
switch (_vtol_schedule.flight_mode) {
case MC_MODE:
// initialise a front transition
_vtol_schedule.flight_mode = TRANSITION_FRONT_P1;
_vtol_schedule.transition_start = hrt_absolute_time();
break;
case FW_MODE:
break;
case TRANSITION_FRONT_P1:
// check if we have reached airspeed to switch to fw mode
if (_airspeed->true_airspeed_m_s >= _params_tiltrotor.airspeed_trans) {
_vtol_schedule.flight_mode = TRANSITION_FRONT_P2;
_vtol_schedule.transition_start = hrt_absolute_time();
}
break;
case TRANSITION_FRONT_P2:
// if the rotors have been tilted completely we switch to fw mode
if (_tilt_control >= _params_tiltrotor.tilt_fw) {
_vtol_schedule.flight_mode = FW_MODE;
_tilt_control = _params_tiltrotor.tilt_fw;
}
break;
case TRANSITION_BACK:
// failsafe into fixed wing mode
_vtol_schedule.flight_mode = FW_MODE;
break;
}
}
// map tiltrotor specific control phases to simple control modes
switch (_vtol_schedule.flight_mode) {
case MC_MODE:
_vtol_mode = ROTARY_WING;
break;
case FW_MODE:
_vtol_mode = FIXED_WING;
break;
case TRANSITION_FRONT_P1:
case TRANSITION_FRONT_P2:
case TRANSITION_BACK:
_vtol_mode = TRANSITION;
break;
}
}
Sensors::Sensors() :
_fd_adc(-1),
_last_adc(0),
_task_should_exit(false),
_sensors_task(-1),
_hil_enabled(false),
_publishing(true),
/* subscriptions */
_gyro_sub(-1),
_accel_sub(-1),
_mag_sub(-1),
_rc_sub(-1),
_baro_sub(-1),
_vcontrol_mode_sub(-1),
_params_sub(-1),
_manual_control_sub(-1),
/* publications */
_sensor_pub(-1),
_manual_control_pub(-1),
_actuator_group_3_pub(-1),
_rc_pub(-1),
_battery_pub(-1),
_airspeed_pub(-1),
_diff_pres_pub(-1),
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "sensor task update")),
_mag_is_external(false),
_battery_discharged(0),
_battery_current_timestamp(0)
{
memset(&_rc, 0, sizeof(_rc));
/* basic r/c parameters */
for (unsigned i = 0; i < _rc_max_chan_count; i++) {
char nbuf[16];
/* min values */
sprintf(nbuf, "RC%d_MIN", i + 1);
_parameter_handles.min[i] = param_find(nbuf);
/* trim values */
sprintf(nbuf, "RC%d_TRIM", i + 1);
_parameter_handles.trim[i] = param_find(nbuf);
/* max values */
sprintf(nbuf, "RC%d_MAX", i + 1);
_parameter_handles.max[i] = param_find(nbuf);
/* channel reverse */
sprintf(nbuf, "RC%d_REV", i + 1);
_parameter_handles.rev[i] = param_find(nbuf);
/* channel deadzone */
sprintf(nbuf, "RC%d_DZ", i + 1);
_parameter_handles.dz[i] = param_find(nbuf);
}
/* 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_failsafe = param_find("RC_MAP_FAILSAFE");
/* mandatory mode switches, mapped to channel 5 and 6 per default */
_parameter_handles.rc_map_mode_sw = param_find("RC_MAP_MODE_SW");
_parameter_handles.rc_map_return_sw = param_find("RC_MAP_RETURN_SW");
_parameter_handles.rc_map_flaps = param_find("RC_MAP_FLAPS");
/* optional mode switches, not mapped per default */
_parameter_handles.rc_map_posctl_sw = param_find("RC_MAP_POSCTL_SW");
_parameter_handles.rc_map_loiter_sw = param_find("RC_MAP_LOITER_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");
/* RC thresholds */
_parameter_handles.rc_fails_thr = param_find("RC_FAILS_THR");
_parameter_handles.rc_assist_th = param_find("RC_ASSIST_TH");
_parameter_handles.rc_auto_th = param_find("RC_AUTO_TH");
_parameter_handles.rc_posctl_th = param_find("RC_POSCTL_TH");
_parameter_handles.rc_return_th = param_find("RC_RETURN_TH");
_parameter_handles.rc_loiter_th = param_find("RC_LOITER_TH");
/* gyro offsets */
_parameter_handles.gyro_offset[0] = param_find("SENS_GYRO_XOFF");
_parameter_handles.gyro_offset[1] = param_find("SENS_GYRO_YOFF");
_parameter_handles.gyro_offset[2] = param_find("SENS_GYRO_ZOFF");
_parameter_handles.gyro_scale[0] = param_find("SENS_GYRO_XSCALE");
_parameter_handles.gyro_scale[1] = param_find("SENS_GYRO_YSCALE");
_parameter_handles.gyro_scale[2] = param_find("SENS_GYRO_ZSCALE");
/* accel offsets */
_parameter_handles.accel_offset[0] = param_find("SENS_ACC_XOFF");
_parameter_handles.accel_offset[1] = param_find("SENS_ACC_YOFF");
_parameter_handles.accel_offset[2] = param_find("SENS_ACC_ZOFF");
_parameter_handles.accel_scale[0] = param_find("SENS_ACC_XSCALE");
_parameter_handles.accel_scale[1] = param_find("SENS_ACC_YSCALE");
_parameter_handles.accel_scale[2] = param_find("SENS_ACC_ZSCALE");
/* mag offsets */
_parameter_handles.mag_offset[0] = param_find("SENS_MAG_XOFF");
_parameter_handles.mag_offset[1] = param_find("SENS_MAG_YOFF");
_parameter_handles.mag_offset[2] = param_find("SENS_MAG_ZOFF");
_parameter_handles.mag_scale[0] = param_find("SENS_MAG_XSCALE");
_parameter_handles.mag_scale[1] = param_find("SENS_MAG_YSCALE");
_parameter_handles.mag_scale[2] = param_find("SENS_MAG_ZSCALE");
/* Differential pressure offset */
_parameter_handles.diff_pres_offset_pa = param_find("SENS_DPRES_OFF");
_parameter_handles.diff_pres_analog_enabled = param_find("SENS_DPRES_ANA");
_parameter_handles.battery_voltage_scaling = param_find("BAT_V_SCALING");
_parameter_handles.battery_current_scaling = param_find("BAT_C_SCALING");
/* rotations */
_parameter_handles.board_rotation = param_find("SENS_BOARD_ROT");
_parameter_handles.external_mag_rotation = param_find("SENS_EXT_MAG_ROT");
/* fetch initial parameter values */
parameters_update();
}
/****************************************************************************
* main
****************************************************************************/
int position_estimator_inav_thread_main(int argc, char *argv[])
{
warnx("started");
int mavlink_fd;
mavlink_fd = open(MAVLINK_LOG_DEVICE, 0);
mavlink_log_info(mavlink_fd, "[inav] started");
float x_est[2] = { 0.0f, 0.0f }; // pos, vel
float y_est[2] = { 0.0f, 0.0f }; // pos, vel
float z_est[2] = { 0.0f, 0.0f }; // pos, vel
float est_buf[EST_BUF_SIZE][3][2]; // estimated position buffer
float R_buf[EST_BUF_SIZE][3][3]; // rotation matrix buffer
float R_gps[3][3]; // rotation matrix for GPS correction moment
memset(est_buf, 0, sizeof(est_buf));
memset(R_buf, 0, sizeof(R_buf));
memset(R_gps, 0, sizeof(R_gps));
int buf_ptr = 0;
static const float min_eph_epv = 2.0f; // min EPH/EPV, used for weight calculation
static const float max_eph_epv = 20.0f; // max EPH/EPV acceptable for estimation
float eph = max_eph_epv;
float epv = 1.0f;
float eph_flow = 1.0f;
float eph_vision = 0.5f;
float epv_vision = 0.5f;
float x_est_prev[2], y_est_prev[2], z_est_prev[2];
memset(x_est_prev, 0, sizeof(x_est_prev));
memset(y_est_prev, 0, sizeof(y_est_prev));
memset(z_est_prev, 0, sizeof(z_est_prev));
int baro_init_cnt = 0;
int baro_init_num = 200;
float baro_offset = 0.0f; // baro offset for reference altitude, initialized on start, then adjusted
float surface_offset = 0.0f; // ground level offset from reference altitude
float surface_offset_rate = 0.0f; // surface offset change rate
float alt_avg = 0.0f;
bool landed = true;
hrt_abstime landed_time = 0;
hrt_abstime accel_timestamp = 0;
hrt_abstime baro_timestamp = 0;
bool ref_inited = false;
hrt_abstime ref_init_start = 0;
const hrt_abstime ref_init_delay = 1000000; // wait for 1s after 3D fix
struct map_projection_reference_s ref;
memset(&ref, 0, sizeof(ref));
hrt_abstime home_timestamp = 0;
uint16_t accel_updates = 0;
uint16_t baro_updates = 0;
uint16_t gps_updates = 0;
uint16_t attitude_updates = 0;
uint16_t flow_updates = 0;
hrt_abstime updates_counter_start = hrt_absolute_time();
hrt_abstime pub_last = hrt_absolute_time();
hrt_abstime t_prev = 0;
/* store error when sensor updates, but correct on each time step to avoid jumps in estimated value */
float acc[] = { 0.0f, 0.0f, 0.0f }; // N E D
float acc_bias[] = { 0.0f, 0.0f, 0.0f }; // body frame
float corr_baro = 0.0f; // D
float corr_gps[3][2] = {
{ 0.0f, 0.0f }, // N (pos, vel)
{ 0.0f, 0.0f }, // E (pos, vel)
{ 0.0f, 0.0f }, // D (pos, vel)
};
float w_gps_xy = 1.0f;
float w_gps_z = 1.0f;
float corr_vision[3][2] = {
{ 0.0f, 0.0f }, // N (pos, vel)
{ 0.0f, 0.0f }, // E (pos, vel)
{ 0.0f, 0.0f }, // D (pos, vel)
};
float corr_sonar = 0.0f;
float corr_sonar_filtered = 0.0f;
float corr_flow[] = { 0.0f, 0.0f }; // N E
float w_flow = 0.0f;
float sonar_prev = 0.0f;
hrt_abstime flow_prev = 0; // time of last flow measurement
hrt_abstime sonar_time = 0; // time of last sonar measurement (not filtered)
hrt_abstime sonar_valid_time = 0; // time of last sonar measurement used for correction (filtered)
bool gps_valid = false; // GPS is valid
bool sonar_valid = false; // sonar is valid
bool flow_valid = false; // flow is valid
bool flow_accurate = false; // flow should be accurate (this flag not updated if flow_valid == false)
bool vision_valid = false;
/* declare and safely initialize all structs */
struct actuator_controls_s actuator;
memset(&actuator, 0, sizeof(actuator));
struct actuator_armed_s armed;
memset(&armed, 0, sizeof(armed));
struct sensor_combined_s sensor;
memset(&sensor, 0, sizeof(sensor));
struct vehicle_gps_position_s gps;
memset(&gps, 0, sizeof(gps));
struct home_position_s home;
memset(&home, 0, sizeof(home));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_local_position_s local_pos;
memset(&local_pos, 0, sizeof(local_pos));
struct optical_flow_s flow;
memset(&flow, 0, sizeof(flow));
struct vision_position_estimate vision;
memset(&vision, 0, sizeof(vision));
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
/* subscribe */
int parameter_update_sub = orb_subscribe(ORB_ID(parameter_update));
int actuator_sub = orb_subscribe(ORB_ID_VEHICLE_ATTITUDE_CONTROLS);
int armed_sub = orb_subscribe(ORB_ID(actuator_armed));
int sensor_combined_sub = orb_subscribe(ORB_ID(sensor_combined));
int vehicle_attitude_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int optical_flow_sub = orb_subscribe(ORB_ID(optical_flow));
int vehicle_gps_position_sub = orb_subscribe(ORB_ID(vehicle_gps_position));
int vision_position_estimate_sub = orb_subscribe(ORB_ID(vision_position_estimate));
int home_position_sub = orb_subscribe(ORB_ID(home_position));
/* advertise */
orb_advert_t vehicle_local_position_pub = orb_advertise(ORB_ID(vehicle_local_position), &local_pos);
orb_advert_t vehicle_global_position_pub = -1;
struct position_estimator_inav_params params;
struct position_estimator_inav_param_handles pos_inav_param_handles;
/* initialize parameter handles */
parameters_init(&pos_inav_param_handles);
/* first parameters read at start up */
struct parameter_update_s param_update;
orb_copy(ORB_ID(parameter_update), parameter_update_sub, ¶m_update); /* read from param topic to clear updated flag */
/* first parameters update */
parameters_update(&pos_inav_param_handles, ¶ms);
struct pollfd fds_init[1] = {
{ .fd = sensor_combined_sub, .events = POLLIN },
};
void
MulticopterAttitudeControl::task_main()
{
warnx("started");
fflush(stdout);
/*
* do subscriptions
*/
_v_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_v_rates_sp_sub = orb_subscribe(ORB_ID(vehicle_rates_setpoint));
_v_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
_v_control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_control_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
/* initialize parameters cache */
parameters_update();
/* wakeup source: vehicle attitude */
struct pollfd fds[1];
fds[0].fd = _v_att_sub;
fds[0].events = POLLIN;
while (!_task_should_exit) {
/* wait for up to 100ms for data */
int pret = poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);
/* timed out - periodic check for _task_should_exit */
if (pret == 0)
continue;
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
/* sleep a bit before next try */
usleep(100000);
continue;
}
perf_begin(_loop_perf);
/* run controller on attitude changes */
if (fds[0].revents & POLLIN) {
static uint64_t last_run = 0;
float dt = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* guard against too small (< 2ms) and too large (> 20ms) dt's */
if (dt < 0.002f) {
dt = 0.002f;
} else if (dt > 0.02f) {
dt = 0.02f;
}
/* copy attitude topic */
orb_copy(ORB_ID(vehicle_attitude), _v_att_sub, &_v_att);
/* check for updates in other topics */
parameter_update_poll();
vehicle_control_mode_poll();
arming_status_poll();
vehicle_manual_poll();
if (_v_control_mode.flag_control_attitude_enabled) {
control_attitude(dt);
/* publish attitude rates setpoint */
_v_rates_sp.roll = _rates_sp(0);
_v_rates_sp.pitch = _rates_sp(1);
_v_rates_sp.yaw = _rates_sp(2);
_v_rates_sp.thrust = _thrust_sp;
_v_rates_sp.timestamp = hrt_absolute_time();
if (_v_rates_sp_pub > 0) {
orb_publish(ORB_ID(vehicle_rates_setpoint), _v_rates_sp_pub, &_v_rates_sp);
} else {
_v_rates_sp_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint), &_v_rates_sp);
}
} else {
/* 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) {
control_attitude_rates(dt);
/* publish actuator controls */
_actuators.control[0] = (isfinite(_att_control(0))) ? _att_control(0) : 0.0f;
_actuators.control[1] = (isfinite(_att_control(1))) ? _att_control(1) : 0.0f;
_actuators.control[2] = (isfinite(_att_control(2))) ? _att_control(2) : 0.0f;
_actuators.control[3] = (isfinite(_thrust_sp)) ? _thrust_sp : 0.0f;
_actuators.timestamp = hrt_absolute_time();
if (_actuators_0_pub > 0) {
orb_publish(ORB_ID(actuator_controls_0), _actuators_0_pub, &_actuators);
} else {
_actuators_0_pub = orb_advertise(ORB_ID(actuator_controls_0), &_actuators);
}
}
}
perf_end(_loop_perf);
}
warnx("exit");
_control_task = -1;
_exit(0);
}
FixedwingAttitudeControl::FixedwingAttitudeControl() :
_task_should_exit(false),
_control_task(-1),
/* subscriptions */
_att_sub(-1),
_accel_sub(-1),
_airspeed_sub(-1),
_vcontrol_mode_sub(-1),
_params_sub(-1),
_manual_sub(-1),
_global_pos_sub(-1),
/* publications */
_rate_sp_pub(-1),
_attitude_sp_pub(-1),
_actuators_0_pub(-1),
_actuators_1_pub(-1),
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "fw att control")),
_nonfinite_input_perf(perf_alloc(PC_COUNT, "fw att control nonfinite input")),
_nonfinite_output_perf(perf_alloc(PC_COUNT, "fw att control nonfinite output")),
/* states */
_setpoint_valid(false)
{
/* safely initialize structs */
_att = {};
_accel = {};
_att_sp = {};
_manual = {};
_airspeed = {};
_vcontrol_mode = {};
_actuators = {};
_actuators_airframe = {};
_global_pos = {};
_parameter_handles.tconst = param_find("FW_ATT_TC");
_parameter_handles.p_p = param_find("FW_PR_P");
_parameter_handles.p_i = param_find("FW_PR_I");
_parameter_handles.p_ff = param_find("FW_PR_FF");
_parameter_handles.p_rmax_pos = param_find("FW_P_RMAX_POS");
_parameter_handles.p_rmax_neg = param_find("FW_P_RMAX_NEG");
_parameter_handles.p_integrator_max = param_find("FW_PR_IMAX");
_parameter_handles.p_roll_feedforward = param_find("FW_P_ROLLFF");
_parameter_handles.r_p = param_find("FW_RR_P");
_parameter_handles.r_i = param_find("FW_RR_I");
_parameter_handles.r_ff = param_find("FW_RR_FF");
_parameter_handles.r_integrator_max = param_find("FW_RR_IMAX");
_parameter_handles.r_rmax = param_find("FW_R_RMAX");
_parameter_handles.y_p = param_find("FW_YR_P");
_parameter_handles.y_i = param_find("FW_YR_I");
_parameter_handles.y_ff = param_find("FW_YR_FF");
_parameter_handles.y_integrator_max = param_find("FW_YR_IMAX");
_parameter_handles.y_rmax = param_find("FW_Y_RMAX");
_parameter_handles.airspeed_min = param_find("FW_AIRSPD_MIN");
_parameter_handles.airspeed_trim = param_find("FW_AIRSPD_TRIM");
_parameter_handles.airspeed_max = param_find("FW_AIRSPD_MAX");
_parameter_handles.y_coordinated_min_speed = param_find("FW_YCO_VMIN");
_parameter_handles.trim_roll = param_find("TRIM_ROLL");
_parameter_handles.trim_pitch = param_find("TRIM_PITCH");
_parameter_handles.trim_yaw = param_find("TRIM_YAW");
_parameter_handles.rollsp_offset_deg = param_find("FW_RSP_OFF");
_parameter_handles.pitchsp_offset_deg = param_find("FW_PSP_OFF");
_parameter_handles.man_roll_max = param_find("FW_MAN_R_MAX");
_parameter_handles.man_pitch_max = param_find("FW_MAN_P_MAX");
/* fetch initial parameter values */
parameters_update();
}
void
MulticopterAttitudeControl::task_main()
{
/*
* do subscriptions
*/
_v_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_v_rates_sp_sub = orb_subscribe(ORB_ID(vehicle_rates_setpoint));
_ctrl_state_sub = orb_subscribe(ORB_ID(control_state));
_v_control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_control_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
_vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
_motor_limits_sub = orb_subscribe(ORB_ID(multirotor_motor_limits));
/* initialize parameters cache */
parameters_update();
/* wakeup source: vehicle attitude */
px4_pollfd_struct_t fds[1];
fds[0].fd = _ctrl_state_sub;
fds[0].events = POLLIN;
while (!_task_should_exit) {
/* wait for up to 100ms for data */
int pret = px4_poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);
/* timed out - periodic check for _task_should_exit */
if (pret == 0) {
continue;
}
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
/* sleep a bit before next try */
usleep(100000);
continue;
}
perf_begin(_loop_perf);
/* run controller on attitude changes */
if (fds[0].revents & POLLIN) {
static uint64_t last_run = 0;
float dt = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* guard against too small (< 2ms) and too large (> 20ms) dt's */
if (dt < 0.002f) {
dt = 0.002f;
} else if (dt > 0.02f) {
dt = 0.02f;
}
/* copy attitude and control state topics */
orb_copy(ORB_ID(control_state), _ctrl_state_sub, &_ctrl_state);
/* check for updates in other topics */
parameter_update_poll();
vehicle_control_mode_poll();
arming_status_poll();
vehicle_manual_poll();
vehicle_status_poll();
vehicle_motor_limits_poll();
/* Check if we are in rattitude mode and the pilot is above the threshold on pitch
* or roll (yaw can rotate 360 in normal att control). If both are true don't
* even bother running the attitude controllers */
if (_vehicle_status.main_state == vehicle_status_s::MAIN_STATE_RATTITUDE) {
if (fabsf(_manual_control_sp.y) > _params.rattitude_thres ||
fabsf(_manual_control_sp.x) > _params.rattitude_thres) {
_v_control_mode.flag_control_attitude_enabled = false;
}
}
if (_v_control_mode.flag_control_attitude_enabled) {
if (_ts_opt_recovery == nullptr) {
// the tailsitter recovery instance has not been created, thus, the vehicle
// is not a tailsitter, do normal attitude control
control_attitude(dt);
} else {
vehicle_attitude_setpoint_poll();
_thrust_sp = _v_att_sp.thrust;
math::Quaternion q(_ctrl_state.q[0], _ctrl_state.q[1], _ctrl_state.q[2], _ctrl_state.q[3]);
math::Quaternion q_sp(&_v_att_sp.q_d[0]);
_ts_opt_recovery->setAttGains(_params.att_p, _params.yaw_ff);
_ts_opt_recovery->calcOptimalRates(q, q_sp, _v_att_sp.yaw_sp_move_rate, _rates_sp);
/* limit rates */
for (int i = 0; i < 3; i++) {
_rates_sp(i) = math::constrain(_rates_sp(i), -_params.mc_rate_max(i), _params.mc_rate_max(i));
}
}
/* publish attitude rates setpoint */
_v_rates_sp.roll = _rates_sp(0);
_v_rates_sp.pitch = _rates_sp(1);
_v_rates_sp.yaw = _rates_sp(2);
_v_rates_sp.thrust = _thrust_sp;
_v_rates_sp.timestamp = hrt_absolute_time();
if (_v_rates_sp_pub != nullptr) {
orb_publish(_rates_sp_id, _v_rates_sp_pub, &_v_rates_sp);
} else if (_rates_sp_id) {
_v_rates_sp_pub = orb_advertise(_rates_sp_id, &_v_rates_sp);
}
//}
} else {
/* attitude controller disabled, poll rates setpoint topic */
if (_v_control_mode.flag_control_manual_enabled) {
/* manual rates control - ACRO mode */
_rates_sp = math::Vector<3>(_manual_control_sp.y, -_manual_control_sp.x,
_manual_control_sp.r).emult(_params.acro_rate_max);
_thrust_sp = math::min(_manual_control_sp.z, MANUAL_THROTTLE_MAX_MULTICOPTER);
/* publish attitude rates setpoint */
_v_rates_sp.roll = _rates_sp(0);
_v_rates_sp.pitch = _rates_sp(1);
_v_rates_sp.yaw = _rates_sp(2);
_v_rates_sp.thrust = _thrust_sp;
_v_rates_sp.timestamp = hrt_absolute_time();
if (_v_rates_sp_pub != nullptr) {
orb_publish(_rates_sp_id, _v_rates_sp_pub, &_v_rates_sp);
} else if (_rates_sp_id) {
_v_rates_sp_pub = orb_advertise(_rates_sp_id, &_v_rates_sp);
}
} else {
/* 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) {
control_attitude_rates(dt);
/* publish actuator controls */
_actuators.control[0] = (PX4_ISFINITE(_att_control(0))) ? _att_control(0) : 0.0f;
_actuators.control[1] = (PX4_ISFINITE(_att_control(1))) ? _att_control(1) : 0.0f;
_actuators.control[2] = (PX4_ISFINITE(_att_control(2))) ? _att_control(2) : 0.0f;
_actuators.control[3] = (PX4_ISFINITE(_thrust_sp)) ? _thrust_sp : 0.0f;
_actuators.timestamp = hrt_absolute_time();
_actuators.timestamp_sample = _ctrl_state.timestamp;
_controller_status.roll_rate_integ = _rates_int(0);
_controller_status.pitch_rate_integ = _rates_int(1);
_controller_status.yaw_rate_integ = _rates_int(2);
_controller_status.timestamp = hrt_absolute_time();
if (!_actuators_0_circuit_breaker_enabled) {
if (_actuators_0_pub != nullptr) {
orb_publish(_actuators_id, _actuators_0_pub, &_actuators);
perf_end(_controller_latency_perf);
} else if (_actuators_id) {
_actuators_0_pub = orb_advertise(_actuators_id, &_actuators);
}
}
/* publish controller status */
if (_controller_status_pub != nullptr) {
orb_publish(ORB_ID(mc_att_ctrl_status), _controller_status_pub, &_controller_status);
} else {
_controller_status_pub = orb_advertise(ORB_ID(mc_att_ctrl_status), &_controller_status);
}
}
}
perf_end(_loop_perf);
}
_control_task = -1;
return;
}
MulticopterAttitudeControl::MulticopterAttitudeControl() :
_task_should_exit(false),
_control_task(-1),
/* subscriptions */
_ctrl_state_sub(-1),
_v_att_sp_sub(-1),
_v_control_mode_sub(-1),
_params_sub(-1),
_manual_control_sp_sub(-1),
_armed_sub(-1),
_vehicle_status_sub(-1),
/* publications */
_v_rates_sp_pub(nullptr),
_actuators_0_pub(nullptr),
_controller_status_pub(nullptr),
_rates_sp_id(0),
_actuators_id(0),
_actuators_0_circuit_breaker_enabled(false),
/* performance counters */
_loop_perf(perf_alloc(PC_ELAPSED, "mc_att_control")),
_controller_latency_perf(perf_alloc_once(PC_ELAPSED, "ctrl_latency")),
_ts_opt_recovery(nullptr)
{
memset(&_ctrl_state, 0, sizeof(_ctrl_state));
memset(&_v_att_sp, 0, sizeof(_v_att_sp));
memset(&_v_rates_sp, 0, sizeof(_v_rates_sp));
memset(&_manual_control_sp, 0, sizeof(_manual_control_sp));
memset(&_v_control_mode, 0, sizeof(_v_control_mode));
memset(&_actuators, 0, sizeof(_actuators));
memset(&_armed, 0, sizeof(_armed));
memset(&_vehicle_status, 0, sizeof(_vehicle_status));
memset(&_motor_limits, 0, sizeof(_motor_limits));
memset(&_controller_status, 0, sizeof(_controller_status));
_vehicle_status.is_rotary_wing = true;
_params.att_p.zero();
_params.rate_p.zero();
_params.rate_i.zero();
_params.rate_d.zero();
_params.rate_ff.zero();
_params.yaw_ff = 0.0f;
_params.roll_rate_max = 0.0f;
_params.pitch_rate_max = 0.0f;
_params.yaw_rate_max = 0.0f;
_params.mc_rate_max.zero();
_params.acro_rate_max.zero();
_params.rattitude_thres = 1.0f;
_rates_prev.zero();
_rates_sp.zero();
_rates_sp_prev.zero();
_rates_int.zero();
_thrust_sp = 0.0f;
_att_control.zero();
_I.identity();
_params_handles.roll_p = param_find("MC_ROLL_P");
_params_handles.roll_rate_p = param_find("MC_ROLLRATE_P");
_params_handles.roll_rate_i = param_find("MC_ROLLRATE_I");
_params_handles.roll_rate_d = param_find("MC_ROLLRATE_D");
_params_handles.roll_rate_ff = param_find("MC_ROLLRATE_FF");
_params_handles.pitch_p = param_find("MC_PITCH_P");
_params_handles.pitch_rate_p = param_find("MC_PITCHRATE_P");
_params_handles.pitch_rate_i = param_find("MC_PITCHRATE_I");
_params_handles.pitch_rate_d = param_find("MC_PITCHRATE_D");
_params_handles.pitch_rate_ff = param_find("MC_PITCHRATE_FF");
_params_handles.yaw_p = param_find("MC_YAW_P");
_params_handles.yaw_rate_p = param_find("MC_YAWRATE_P");
_params_handles.yaw_rate_i = param_find("MC_YAWRATE_I");
_params_handles.yaw_rate_d = param_find("MC_YAWRATE_D");
_params_handles.yaw_rate_ff = param_find("MC_YAWRATE_FF");
_params_handles.yaw_ff = param_find("MC_YAW_FF");
_params_handles.roll_rate_max = param_find("MC_ROLLRATE_MAX");
_params_handles.pitch_rate_max = param_find("MC_PITCHRATE_MAX");
_params_handles.yaw_rate_max = param_find("MC_YAWRATE_MAX");
_params_handles.acro_roll_max = param_find("MC_ACRO_R_MAX");
_params_handles.acro_pitch_max = param_find("MC_ACRO_P_MAX");
_params_handles.acro_yaw_max = param_find("MC_ACRO_Y_MAX");
_params_handles.rattitude_thres = param_find("MC_RATT_TH");
_params_handles.vtol_type = param_find("VT_TYPE");
_params_handles.roll_tc = param_find("MC_ROLL_TC");
_params_handles.pitch_tc = param_find("MC_PITCH_TC");
/* fetch initial parameter values */
parameters_update();
if (_params.vtol_type == 0) {
// the vehicle is a tailsitter, use optimal recovery control strategy
_ts_opt_recovery = new TailsitterRecovery();
}
}
void
MulticopterAttitudeControl::task_main()
{
/*
* do subscriptions
*/
_v_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_v_rates_sp_sub = orb_subscribe(ORB_ID(vehicle_rates_setpoint));
_v_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
_v_control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_control_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
_vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
_motor_limits_sub = orb_subscribe(ORB_ID(multirotor_motor_limits));
/* initialize parameters cache */
parameters_update();
/* wakeup source: vehicle attitude */
px4_pollfd_struct_t fds[1];
fds[0].fd = _v_att_sub;
fds[0].events = POLLIN;
while (!_task_should_exit) {
/* wait for up to 100ms for data */
int pret = px4_poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);
/* timed out - periodic check for _task_should_exit */
if (pret == 0)
continue;
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
/* sleep a bit before next try */
usleep(100000);
continue;
}
perf_begin(_loop_perf);
/* run controller on attitude changes */
if (fds[0].revents & POLLIN) {
static uint64_t last_run = 0;
float dt = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* guard against too small (< 2ms) and too large (> 20ms) dt's */
if (dt < 0.002f) {
dt = 0.002f;
} else if (dt > 0.02f) {
dt = 0.02f;
}
/* copy attitude topic */
orb_copy(ORB_ID(vehicle_attitude), _v_att_sub, &_v_att);
/* check for updates in other topics */
parameter_update_poll();
vehicle_control_mode_poll();
arming_status_poll();
vehicle_manual_poll();
vehicle_status_poll();
vehicle_motor_limits_poll();
if (_v_control_mode.flag_control_attitude_enabled) {
control_attitude(dt);
/* publish attitude rates setpoint */
_v_rates_sp.roll = _rates_sp(0);
_v_rates_sp.pitch = _rates_sp(1);
_v_rates_sp.yaw = _rates_sp(2);
_v_rates_sp.thrust = _thrust_sp;
_v_rates_sp.timestamp = hrt_absolute_time();
if (_v_rates_sp_pub != nullptr) {
orb_publish(_rates_sp_id, _v_rates_sp_pub, &_v_rates_sp);
} else if (_rates_sp_id) {
_v_rates_sp_pub = orb_advertise(_rates_sp_id, &_v_rates_sp);
}
} else {
/* attitude controller disabled, poll rates setpoint topic */
if (_v_control_mode.flag_control_manual_enabled) {
/* manual rates control - ACRO mode */
_rates_sp = math::Vector<3>(_manual_control_sp.y, -_manual_control_sp.x, _manual_control_sp.r).emult(_params.acro_rate_max);
_thrust_sp = _manual_control_sp.z;
/* publish attitude rates setpoint */
_v_rates_sp.roll = _rates_sp(0);
_v_rates_sp.pitch = _rates_sp(1);
_v_rates_sp.yaw = _rates_sp(2);
_v_rates_sp.thrust = _thrust_sp;
_v_rates_sp.timestamp = hrt_absolute_time();
if (_v_rates_sp_pub != nullptr) {
orb_publish(_rates_sp_id, _v_rates_sp_pub, &_v_rates_sp);
} else if (_rates_sp_id) {
_v_rates_sp_pub = orb_advertise(_rates_sp_id, &_v_rates_sp);
}
} else {
/* 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) {
control_attitude_rates(dt);
/* publish actuator controls */
_actuators.control[0] = (PX4_ISFINITE(_att_control(0))) ? _att_control(0) : 0.0f;
_actuators.control[1] = (PX4_ISFINITE(_att_control(1))) ? _att_control(1) : 0.0f;
_actuators.control[2] = (PX4_ISFINITE(_att_control(2))) ? _att_control(2) : 0.0f;
_actuators.control[3] = (PX4_ISFINITE(_thrust_sp)) ? _thrust_sp : 0.0f;
_actuators.timestamp = hrt_absolute_time();
_actuators.timestamp_sample = _v_att.timestamp;
_controller_status.roll_rate_integ = _rates_int(0);
_controller_status.pitch_rate_integ = _rates_int(1);
_controller_status.yaw_rate_integ = _rates_int(2);
_controller_status.timestamp = hrt_absolute_time();
if (!_actuators_0_circuit_breaker_enabled) {
if (_actuators_0_pub != nullptr) {
orb_publish(_actuators_id, _actuators_0_pub, &_actuators);
perf_end(_controller_latency_perf);
} else if (_actuators_id) {
_actuators_0_pub = orb_advertise(_actuators_id, &_actuators);
}
}
/* publish controller status */
if(_controller_status_pub != nullptr) {
orb_publish(ORB_ID(mc_att_ctrl_status),_controller_status_pub, &_controller_status);
} else {
_controller_status_pub = orb_advertise(ORB_ID(mc_att_ctrl_status), &_controller_status);
}
}
}
perf_end(_loop_perf);
}
_control_task = -1;
return;
}
void
GroundRoverAttitudeControl::task_main()
{
_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
_vcontrol_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_battery_status_sub = orb_subscribe(ORB_ID(battery_status));
parameters_update();
/* get an initial update for all sensor and status data */
vehicle_attitude_setpoint_poll();
vehicle_control_mode_poll();
manual_control_setpoint_poll();
battery_status_poll();
/* wakeup source */
px4_pollfd_struct_t fds[2];
/* Setup of loop */
fds[0].fd = _params_sub;
fds[0].events = POLLIN;
fds[1].fd = _att_sub;
fds[1].events = POLLIN;
_task_running = true;
while (!_task_should_exit) {
static int loop_counter = 0;
/* wait for up to 500ms for data */
int pret = px4_poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);
/* timed out - periodic check for _task_should_exit, etc. */
if (pret == 0) {
continue;
}
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
continue;
}
perf_begin(_loop_perf);
/* 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), _params_sub, &update);
/* update parameters from storage */
parameters_update();
}
/* only run controller if attitude changed */
if (fds[1].revents & POLLIN) {
static uint64_t last_run = 0;
float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
last_run = hrt_absolute_time();
/* guard against too large deltaT's */
if (deltaT > 1.0f ||
fabsf(deltaT) < 0.00001f ||
!PX4_ISFINITE(deltaT)) {
deltaT = 0.01f;
}
/* load local copies */
orb_copy(ORB_ID(vehicle_attitude), _att_sub, &_att);
vehicle_attitude_setpoint_poll();
vehicle_control_mode_poll();
manual_control_setpoint_poll();
battery_status_poll();
/* decide if in stabilized or full manual control */
if (_vcontrol_mode.flag_control_rates_enabled) {
/* Run attitude controllers */
if (_vcontrol_mode.flag_control_attitude_enabled) {
Eulerf euler_angles(matrix::Quatf(_att.q));
/* Calculate the control output for the steering as yaw */
float yaw_u = pid_calculate(&_steering_ctrl, _att_sp.yaw_body, euler_angles.psi(), _att.yawspeed, deltaT);
float angle_diff = 0.0f;
if (_att_sp.yaw_body * euler_angles.psi() < 0.0f) {
if (_att_sp.yaw_body < 0.0f) {
angle_diff = euler_angles.psi() - _att_sp.yaw_body ;
} else {
angle_diff = _att_sp.yaw_body - euler_angles.psi();
}
// a switch might have happened
if ((double)angle_diff > M_PI) {
yaw_u = -yaw_u;
}
}
math::constrain(yaw_u, -1.0f, 1.0f);
if (PX4_ISFINITE(yaw_u)) {
_actuators.control[actuator_controls_s::INDEX_YAW] = yaw_u + _parameters.trim_yaw;
} else {
_actuators.control[actuator_controls_s::INDEX_YAW] = _parameters.trim_yaw;
perf_count(_nonfinite_output_perf);
if (_debug && loop_counter % 10 == 0) {
warnx("yaw_u %.4f", (double)yaw_u);
}
}
/* throttle passed through if it is finite and if no engine failure was detected */
_actuators.control[actuator_controls_s::INDEX_THROTTLE] = _att_sp.thrust;
/* scale effort by battery status */
if (_parameters.bat_scale_en && _battery_status.scale > 0.0f &&
_actuators.control[actuator_controls_s::INDEX_THROTTLE] > 0.1f) {
_actuators.control[actuator_controls_s::INDEX_THROTTLE] *= _battery_status.scale;
}
}
} else {
/* manual/direct control */
_actuators.control[actuator_controls_s::INDEX_ROLL] = _manual.y;
_actuators.control[actuator_controls_s::INDEX_PITCH] = -_manual.x;
_actuators.control[actuator_controls_s::INDEX_YAW] = _manual.r * _parameters.man_yaw_scale + _parameters.trim_yaw;
_actuators.control[actuator_controls_s::INDEX_THROTTLE] = _manual.z;
}
/* lazily publish the setpoint only once available */
_actuators.timestamp = hrt_absolute_time();
_actuators.timestamp_sample = _att.timestamp;
/* Only publish if any of the proper modes are enabled */
if (_vcontrol_mode.flag_control_attitude_enabled ||
_vcontrol_mode.flag_control_manual_enabled) {
/* publish the actuator controls */
if (_actuators_0_pub != nullptr) {
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, _actuators_0_pub, &_actuators);
} else {
_actuators_0_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &_actuators);
}
}
}
loop_counter++;
perf_end(_loop_perf);
}
warnx("exiting.\n");
_control_task = -1;
_task_running = false;
}
/*
* EKF Attitude Estimator main function.
*
* Estimates the attitude recursively once started.
*
* @param argc number of commandline arguments (plus command name)
* @param argv strings containing the arguments
*/
int attitude_estimator_ekf_thread_main(int argc, char *argv[])
{
float dt = 0.005f;
/* state vector x has the following entries [ax,ay,az||mx,my,mz||wox,woy,woz||wx,wy,wz]' */
float z_k[9] = {0.0f, 0.0f, 0.0f, 0.0f, 0.0f, 9.81f, 0.2f, -0.2f, 0.2f}; /**< Measurement vector */
float x_aposteriori_k[12]; /**< states */
float P_aposteriori_k[144] = {100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 100.f, 0, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 100.0f, 0, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 100.0f, 0,
0, 0, 0, 0, 0, 0, 0, 0, 0.0f, 0, 0, 100.0f,
}; /**< init: diagonal matrix with big values */
float x_aposteriori[12];
float P_aposteriori[144];
/* output euler angles */
float euler[3] = {0.0f, 0.0f, 0.0f};
float Rot_matrix[9] = {1.f, 0, 0,
0, 1.f, 0,
0, 0, 1.f
}; /**< init: identity matrix */
float debugOutput[4] = { 0.0f };
/* Initialize filter */
AttitudeEKF_initialize();
struct sensor_combined_s raw;
memset(&raw, 0, sizeof(raw));
struct vehicle_gps_position_s gps;
memset(&gps, 0, sizeof(gps));
gps.eph = 100000;
gps.epv = 100000;
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_control_mode_s control_mode;
memset(&control_mode, 0, sizeof(control_mode));
uint64_t last_data = 0;
uint64_t last_measurement = 0;
uint64_t last_vel_t = 0;
/* current velocity */
math::Vector<3> vel;
vel.zero();
/* previous velocity */
math::Vector<3> vel_prev;
vel_prev.zero();
/* actual acceleration (by GPS velocity) in body frame */
math::Vector<3> acc;
acc.zero();
/* rotation matrix */
math::Matrix<3, 3> R;
R.identity();
/* subscribe to raw data */
int sub_raw = orb_subscribe(ORB_ID(sensor_combined));
/* subscribe to GPS */
int sub_gps = orb_subscribe(ORB_ID(vehicle_gps_position));
/* subscribe to GPS */
int sub_global_pos = orb_subscribe(ORB_ID(vehicle_global_position));
/* subscribe to param changes */
int sub_params = orb_subscribe(ORB_ID(parameter_update));
/* subscribe to control mode */
int sub_control_mode = orb_subscribe(ORB_ID(vehicle_control_mode));
/* subscribe to vision estimate */
int vision_sub = orb_subscribe(ORB_ID(vision_position_estimate));
/* subscribe to mocap data */
int mocap_sub = orb_subscribe(ORB_ID(att_pos_mocap));
/* advertise attitude */
orb_advert_t pub_att = orb_advertise(ORB_ID(vehicle_attitude), &att);
int loopcounter = 0;
thread_running = true;
/* keep track of sensor updates */
uint64_t sensor_last_timestamp[3] = {0, 0, 0};
struct attitude_estimator_ekf_params ekf_params;
memset(&ekf_params, 0, sizeof(ekf_params));
struct attitude_estimator_ekf_param_handles ekf_param_handles = { 0 };
/* initialize parameter handles */
parameters_init(&ekf_param_handles);
bool initialized = false;
float gyro_offsets[3] = { 0.0f, 0.0f, 0.0f };
/* magnetic declination, in radians */
float mag_decl = 0.0f;
/* rotation matrix for magnetic declination */
math::Matrix<3, 3> R_decl;
R_decl.identity();
struct vision_position_estimate_s vision {};
struct att_pos_mocap_s mocap {};
/* register the perf counter */
perf_counter_t ekf_loop_perf = perf_alloc(PC_ELAPSED, "attitude_estimator_ekf");
/* Main loop*/
while (!thread_should_exit) {
px4_pollfd_struct_t fds[2];
fds[0].fd = sub_raw;
fds[0].events = POLLIN;
fds[1].fd = sub_params;
fds[1].events = POLLIN;
int ret = px4_poll(fds, 2, 1000);
if (ret < 0) {
/* XXX this is seriously bad - should be an emergency */
} else if (ret == 0) {
/* check if we're in HIL - not getting sensor data is fine then */
orb_copy(ORB_ID(vehicle_control_mode), sub_control_mode, &control_mode);
if (!control_mode.flag_system_hil_enabled) {
warnx("WARNING: Not getting sensor data - sensor app running?");
}
} else {
/* only update parameters if they changed */
if (fds[1].revents & POLLIN) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), sub_params, &update);
/* update parameters */
parameters_update(&ekf_param_handles, &ekf_params);
}
/* only run filter if sensor values changed */
if (fds[0].revents & POLLIN) {
/* get latest measurements */
orb_copy(ORB_ID(sensor_combined), sub_raw, &raw);
bool gps_updated;
orb_check(sub_gps, &gps_updated);
if (gps_updated) {
orb_copy(ORB_ID(vehicle_gps_position), sub_gps, &gps);
if (gps.eph < 20.0f && hrt_elapsed_time(&gps.timestamp) < 1000000) {
mag_decl = math::radians(get_mag_declination(gps.lat / 1e7f, gps.lon / 1e7f));
/* update mag declination rotation matrix */
R_decl.from_euler(0.0f, 0.0f, mag_decl);
}
}
bool global_pos_updated;
orb_check(sub_global_pos, &global_pos_updated);
if (global_pos_updated) {
orb_copy(ORB_ID(vehicle_global_position), sub_global_pos, &global_pos);
}
if (!initialized) {
// XXX disabling init for now
initialized = true;
// gyro_offsets[0] += raw.gyro_rad_s[0];
// gyro_offsets[1] += raw.gyro_rad_s[1];
// gyro_offsets[2] += raw.gyro_rad_s[2];
// offset_count++;
// if (hrt_absolute_time() - start_time > 3000000LL) {
// initialized = true;
// gyro_offsets[0] /= offset_count;
// gyro_offsets[1] /= offset_count;
// gyro_offsets[2] /= offset_count;
// }
} else {
perf_begin(ekf_loop_perf);
/* Calculate data time difference in seconds */
dt = (raw.timestamp - last_measurement) / 1000000.0f;
last_measurement = raw.timestamp;
uint8_t update_vect[3] = {0, 0, 0};
/* Fill in gyro measurements */
if (sensor_last_timestamp[0] != raw.gyro_timestamp[0]) {
update_vect[0] = 1;
// sensor_update_hz[0] = 1e6f / (raw.timestamp - sensor_last_timestamp[0]);
sensor_last_timestamp[0] = raw.gyro_timestamp[0];
}
z_k[0] = raw.gyro_rad_s[0] - gyro_offsets[0];
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_timestamp[1] != raw.accelerometer_timestamp[0]) {
update_vect[1] = 1;
// sensor_update_hz[1] = 1e6f / (raw.timestamp - sensor_last_timestamp[1]);
sensor_last_timestamp[1] = raw.accelerometer_timestamp[0];
}
hrt_abstime vel_t = 0;
bool vel_valid = false;
if (gps.eph < 5.0f && global_pos.timestamp != 0 && hrt_absolute_time() < global_pos.timestamp + 20000) {
vel_valid = true;
if (global_pos_updated) {
vel_t = global_pos.timestamp;
vel(0) = global_pos.vel_n;
vel(1) = global_pos.vel_e;
vel(2) = global_pos.vel_d;
}
}
if (vel_valid) {
/* velocity is valid */
if (vel_t != 0) {
/* velocity updated */
if (last_vel_t != 0 && vel_t != last_vel_t) {
float vel_dt = (vel_t - last_vel_t) / 1000000.0f;
/* calculate acceleration in body frame */
acc = R.transposed() * ((vel - vel_prev) / vel_dt);
}
last_vel_t = vel_t;
vel_prev = vel;
}
} else {
/* velocity is valid, reset acceleration */
acc.zero();
vel_prev.zero();
last_vel_t = 0;
}
z_k[3] = raw.accelerometer_m_s2[0] - acc(0);
z_k[4] = raw.accelerometer_m_s2[1] - acc(1);
z_k[5] = raw.accelerometer_m_s2[2] - acc(2);
/* update magnetometer measurements */
if (sensor_last_timestamp[2] != raw.magnetometer_timestamp[0] &&
/* check that the mag vector is > 0 */
fabsf(sqrtf(raw.magnetometer_ga[0] * raw.magnetometer_ga[0] +
raw.magnetometer_ga[1] * raw.magnetometer_ga[1] +
raw.magnetometer_ga[2] * raw.magnetometer_ga[2])) > 0.1f) {
update_vect[2] = 1;
// sensor_update_hz[2] = 1e6f / (raw.timestamp - sensor_last_timestamp[2]);
sensor_last_timestamp[2] = raw.magnetometer_timestamp[0];
}
bool vision_updated = false;
orb_check(vision_sub, &vision_updated);
bool mocap_updated = false;
orb_check(mocap_sub, &mocap_updated);
if (vision_updated) {
orb_copy(ORB_ID(vision_position_estimate), vision_sub, &vision);
}
if (mocap_updated) {
orb_copy(ORB_ID(att_pos_mocap), mocap_sub, &mocap);
}
if (mocap.timestamp_boot > 0 && (hrt_elapsed_time(&mocap.timestamp_boot) < 500000)) {
math::Quaternion q(mocap.q);
math::Matrix<3, 3> Rmoc = q.to_dcm();
math::Vector<3> v(1.0f, 0.0f, 0.4f);
math::Vector<3> vn = Rmoc.transposed() * v; //Rmoc is Rwr (robot respect to world) while v is respect to world. Hence Rmoc must be transposed having (Rwr)' * Vw
// Rrw * Vw = vn. This way we have consistency
z_k[6] = vn(0);
z_k[7] = vn(1);
z_k[8] = vn(2);
}else if (vision.timestamp_boot > 0 && (hrt_elapsed_time(&vision.timestamp_boot) < 500000)) {
math::Quaternion q(vision.q);
math::Matrix<3, 3> Rvis = q.to_dcm();
math::Vector<3> v(1.0f, 0.0f, 0.4f);
math::Vector<3> vn = Rvis.transposed() * v; //Rvis is Rwr (robot respect to world) while v is respect to world. Hence Rvis must be transposed having (Rwr)' * Vw
// Rrw * Vw = vn. This way we have consistency
z_k[6] = vn(0);
z_k[7] = vn(1);
z_k[8] = vn(2);
} else {
z_k[6] = raw.magnetometer_ga[0];
z_k[7] = raw.magnetometer_ga[1];
z_k[8] = raw.magnetometer_ga[2];
}
static bool const_initialized = false;
/* initialize with good values once we have a reasonable dt estimate */
if (!const_initialized && dt < 0.05f && dt > 0.001f) {
dt = 0.005f;
parameters_update(&ekf_param_handles, &ekf_params);
/* update mag declination rotation matrix */
if (gps.eph < 20.0f && hrt_elapsed_time(&gps.timestamp) < 1000000) {
mag_decl = math::radians(get_mag_declination(gps.lat / 1e7f, gps.lon / 1e7f));
}
/* update mag declination rotation matrix */
R_decl.from_euler(0.0f, 0.0f, mag_decl);
x_aposteriori_k[0] = z_k[0];
x_aposteriori_k[1] = z_k[1];
x_aposteriori_k[2] = z_k[2];
x_aposteriori_k[3] = 0.0f;
x_aposteriori_k[4] = 0.0f;
x_aposteriori_k[5] = 0.0f;
x_aposteriori_k[6] = z_k[3];
x_aposteriori_k[7] = z_k[4];
x_aposteriori_k[8] = z_k[5];
x_aposteriori_k[9] = z_k[6];
x_aposteriori_k[10] = z_k[7];
x_aposteriori_k[11] = z_k[8];
const_initialized = true;
}
/* do not execute the filter if not initialized */
if (!const_initialized) {
continue;
}
/* Call the estimator */
AttitudeEKF(false, // approx_prediction
(unsigned char)ekf_params.use_moment_inertia,
update_vect,
dt,
z_k,
ekf_params.q[0], // q_rotSpeed,
ekf_params.q[1], // q_rotAcc
ekf_params.q[2], // q_acc
ekf_params.q[3], // q_mag
ekf_params.r[0], // r_gyro
ekf_params.r[1], // r_accel
ekf_params.r[2], // r_mag
ekf_params.moment_inertia_J,
x_aposteriori,
P_aposteriori,
Rot_matrix,
euler,
debugOutput);
/* swap values for next iteration, check for fatal inputs */
if (PX4_ISFINITE(euler[0]) && PX4_ISFINITE(euler[1]) && PX4_ISFINITE(euler[2])) {
memcpy(P_aposteriori_k, P_aposteriori, sizeof(P_aposteriori_k));
memcpy(x_aposteriori_k, x_aposteriori, sizeof(x_aposteriori_k));
} else {
/* due to inputs or numerical failure the output is invalid, skip it */
continue;
}
if (last_data > 0 && raw.timestamp - last_data > 30000) {
warnx("sensor data missed! (%llu)\n", static_cast<unsigned long long>(raw.timestamp - last_data));
}
last_data = raw.timestamp;
/* send out */
att.timestamp = raw.timestamp;
att.roll = euler[0];
att.pitch = euler[1];
att.yaw = euler[2] + mag_decl;
att.rollspeed = x_aposteriori[0];
att.pitchspeed = x_aposteriori[1];
att.yawspeed = x_aposteriori[2];
att.rollacc = x_aposteriori[3];
att.pitchacc = x_aposteriori[4];
att.yawacc = x_aposteriori[5];
att.g_comp[0] = raw.accelerometer_m_s2[0] - acc(0);
att.g_comp[1] = raw.accelerometer_m_s2[1] - acc(1);
att.g_comp[2] = raw.accelerometer_m_s2[2] - acc(2);
/* copy offsets */
memcpy(&att.rate_offsets, &(x_aposteriori[3]), sizeof(att.rate_offsets));
/* magnetic declination */
math::Matrix<3, 3> R_body = (&Rot_matrix[0]);
R = R_decl * R_body;
math::Quaternion q;
q.from_dcm(R);
/* copy rotation matrix */
memcpy(&att.R[0], &R.data[0][0], sizeof(att.R));
memcpy(&att.q[0],&q.data[0],sizeof(att.q));
att.R_valid = true;
if (PX4_ISFINITE(att.q[0]) && PX4_ISFINITE(att.q[1])
&& PX4_ISFINITE(att.q[2]) && PX4_ISFINITE(att.q[3])) {
// Broadcast
orb_publish(ORB_ID(vehicle_attitude), pub_att, &att);
} else {
warnx("ERR: NaN estimate!");
}
perf_end(ekf_loop_perf);
}
}
}
loopcounter++;
}
thread_running = false;
return 0;
}
void Standard::update_vtol_state()
{
parameters_update();
/* After flipping the switch the vehicle will start the pusher (or tractor) motor, picking up
* forward speed. After the vehicle has picked up enough speed the rotors shutdown.
* For the back transition the pusher motor is immediately stopped and rotors reactivated.
*/
if (!_attc->is_fixed_wing_requested()) {
// the transition to fw mode switch is off
if (_vtol_schedule.flight_mode == MC_MODE) {
// in mc mode
_vtol_schedule.flight_mode = MC_MODE;
_mc_roll_weight = 1.0f;
_mc_pitch_weight = 1.0f;
_mc_yaw_weight = 1.0f;
_mc_throttle_weight = 1.0f;
} else if (_vtol_schedule.flight_mode == FW_MODE) {
// transition to mc mode
if (_vtol_vehicle_status->vtol_transition_failsafe == true) {
// Failsafe event, engage mc motors immediately
_vtol_schedule.flight_mode = MC_MODE;
_flag_enable_mc_motors = true;
} else {
// Regular backtransition
_vtol_schedule.flight_mode = TRANSITION_TO_MC;
_flag_enable_mc_motors = true;
_vtol_schedule.transition_start = hrt_absolute_time();
}
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_FW) {
// failsafe back to mc mode
_vtol_schedule.flight_mode = MC_MODE;
_mc_roll_weight = 1.0f;
_mc_pitch_weight = 1.0f;
_mc_yaw_weight = 1.0f;
_mc_throttle_weight = 1.0f;
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_MC) {
// transition to MC mode if transition time has passed
// XXX: base this on XY hold velocity of MC
if (hrt_elapsed_time(&_vtol_schedule.transition_start) >
(_params_standard.back_trans_dur * 1000000.0f)) {
_vtol_schedule.flight_mode = MC_MODE;
}
}
// the pusher motor should never be powered when in or transitioning to mc mode
_pusher_throttle = 0.0f;
} else {
// the transition to fw mode switch is on
if (_vtol_schedule.flight_mode == MC_MODE || _vtol_schedule.flight_mode == TRANSITION_TO_MC) {
// start transition to fw mode
/* NOTE: The failsafe transition to fixed-wing was removed because it can result in an
* unsafe flying state. */
_vtol_schedule.flight_mode = TRANSITION_TO_FW;
_vtol_schedule.transition_start = hrt_absolute_time();
} else if (_vtol_schedule.flight_mode == FW_MODE) {
// in fw mode
_vtol_schedule.flight_mode = FW_MODE;
_mc_roll_weight = 0.0f;
_mc_pitch_weight = 0.0f;
_mc_yaw_weight = 0.0f;
_mc_throttle_weight = 0.0f;
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_FW) {
// continue the transition to fw mode while monitoring airspeed for a final switch to fw mode
if (((_params_standard.airspeed_mode == control_state_s::AIRSPD_MODE_DISABLED ||
_airspeed->indicated_airspeed_m_s >= _params_standard.airspeed_trans) &&
(float)hrt_elapsed_time(&_vtol_schedule.transition_start)
> (_params_standard.front_trans_time_min * 1000000.0f)) ||
can_transition_on_ground()) {
_vtol_schedule.flight_mode = FW_MODE;
// we can turn off the multirotor motors now
_flag_enable_mc_motors = false;
// don't set pusher throttle here as it's being ramped up elsewhere
_trans_finished_ts = hrt_absolute_time();
}
}
}
// map specific control phases to simple control modes
switch (_vtol_schedule.flight_mode) {
case MC_MODE:
_vtol_mode = mode::ROTARY_WING;
break;
case FW_MODE:
_vtol_mode = mode::FIXED_WING;
break;
case TRANSITION_TO_FW:
_vtol_mode = mode::TRANSITION_TO_MC;
break;
case TRANSITION_TO_MC:
_vtol_mode = mode::TRANSITION_TO_FW;
break;
}
}
/*
* Nonliner Exciplicit complementary filter (ECF), attitude estimator main function.
*
* Estimates the attitude once started.
*
* @param argc number of commandline arguments (plus command name)
* @param argv strings containing the arguments
*/
int unibo_att_esti_ECF_s_thread_main(int argc, char *argv[])
{
const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
//! Time constant
float dt = 0.005f;
/* output euler angles */
float euler[3] = {0.0f, 0.0f, 0.0f};
/* Initialization */
float Rot_matrix[9] = {1.f, 0.0f, 0.0f, 0.0f, 1.f, 0.0f, 0.0f, 0.0f, 1.f }; /**< init: identity matrix */
float acc[3] = {0.0f, 0.0f, 0.0f};
float gyro[3] = {0.0f, 0.0f, 0.0f};
float mag[3] = {0.0f, 0.0f, 0.0f};
warnx("main thread started");
struct sensor_combined_s raw;
memset(&raw, 0, sizeof(raw));
//! Initialize attitude vehicle uORB message.
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_control_mode_s control_mode;
memset(&control_mode, 0, sizeof(control_mode));
uint64_t last_data = 0;
uint64_t last_measurement = 0;
/* subscribe to raw data */
int sub_raw = orb_subscribe(ORB_ID(sensor_combined));
/* rate-limit raw data updates to 333 Hz (sensors app publishes at 200, so this is just paranoid) */
orb_set_interval(sub_raw, 3);
/* subscribe to param changes */
int sub_params = orb_subscribe(ORB_ID(parameter_update));
/* subscribe to control mode */
int sub_control_mode = orb_subscribe(ORB_ID(vehicle_control_mode));
/* advertise attitude */
//orb_advert_t pub_att = orb_advertise(ORB_ID(vehicle_attitude), &att);
//orb_advert_t att_pub = -1;
orb_advert_t att_pub = orb_advertise(ORB_ID(vehicle_attitude), &att);
int loopcounter = 0;
int printcounter = 0;
thread_running = true;
float sensor_update_hz[3] = {0.0f, 0.0f, 0.0f};
// XXX write this out to perf regs
/* keep track of sensor updates */
uint32_t sensor_last_count[3] = {0, 0, 0};
uint64_t sensor_last_timestamp[3] = {0, 0, 0};
struct unibo_att_esti_ECF_s_params so3_comp_params;
struct unibo_att_esti_ECF_s_param_handles so3_comp_param_handles;
/* initialize parameter handles */
parameters_init(&so3_comp_param_handles);
parameters_update(&so3_comp_param_handles, &so3_comp_params);
uint64_t start_time = hrt_absolute_time();
bool initialized = false;
bool state_initialized = false;
float gyro_offsets[3] = { 0.0f, 0.0f, 0.0f };
unsigned offset_count = 0;
/* register the perf counter */
perf_counter_t so3_comp_loop_perf = perf_alloc(PC_ELAPSED, "unibo_att_esti_ECF_s");
/*-----------------------------------------------
* Main loop
* ----------------------------------------------*/
while (!thread_should_exit) {
struct pollfd fds[2];
fds[0].fd = sub_raw;
fds[0].events = POLLIN;
fds[1].fd = sub_params;
fds[1].events = POLLIN;
int ret = poll(fds, 2, 1000);
if (ret < 0) {
/* XXX this is seriously bad - should be an emergency */
} else if (ret == 0) {
/* check if we're in HIL - not getting sensor data is fine then */
orb_copy(ORB_ID(vehicle_control_mode), sub_control_mode, &control_mode);
if (!control_mode.flag_system_hil_enabled) {
warnx("WARNING: Not getting sensors - sensor app running?");
}
} else {
/* only update parameters if they changed */
if (fds[1].revents & POLLIN) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), sub_params, &update);
/* update parameters */
parameters_update(&so3_comp_param_handles, &so3_comp_params);
}
/* only run filter if sensor values changed */
if (fds[0].revents & POLLIN) {
/* get latest measurements */
orb_copy(ORB_ID(sensor_combined), sub_raw, &raw);
if (!initialized) {
gyro_offsets[0] += raw.gyro_rad_s[0];
gyro_offsets[1] += raw.gyro_rad_s[1];
gyro_offsets[2] += raw.gyro_rad_s[2];
offset_count++;
if (hrt_absolute_time() > start_time + 3000000l) {
initialized = true;
gyro_offsets[0] /= offset_count;
gyro_offsets[1] /= offset_count;
gyro_offsets[2] /= offset_count;
warnx("gyro initialized, offsets: %.5f %.5f %.5f", (double)gyro_offsets[0], (double)gyro_offsets[1], (double)gyro_offsets[2]);
}
} else {
perf_begin(so3_comp_loop_perf);
/* Calculate data time difference in seconds */
dt = (raw.timestamp - last_measurement) / 1000000.0f;
last_measurement = raw.timestamp;
uint8_t update_vect[3] = {0, 0, 0};
/* Fill in gyro measurements */
if (sensor_last_timestamp[0] != raw.timestamp) {
update_vect[0] = 1;
sensor_update_hz[0] = 1e6f / (raw.timestamp - sensor_last_timestamp[0]);
sensor_last_timestamp[0] = raw.timestamp;
}
gyro[0] = raw.gyro_rad_s[0] - gyro_offsets[0];
gyro[1] = raw.gyro_rad_s[1] - gyro_offsets[1];
gyro[2] = raw.gyro_rad_s[2] - gyro_offsets[2];
/* update accelerometer measurements */
if (sensor_last_timestamp[1] != raw.accelerometer_timestamp) {
update_vect[1] = 1;
sensor_update_hz[1] = 1e6f / (raw.timestamp - sensor_last_timestamp[1]);
sensor_last_timestamp[1] = raw.accelerometer_timestamp;
}
acc[0] = raw.accelerometer_m_s2[0];
acc[1] = raw.accelerometer_m_s2[1];
acc[2] = raw.accelerometer_m_s2[2];
/* update magnetometer measurements */
if (sensor_last_timestamp[2] != raw.magnetometer_timestamp) {
update_vect[2] = 1;
sensor_update_hz[2] = 1e6f / (raw.timestamp - sensor_last_timestamp[2]);
sensor_last_timestamp[2] = raw.magnetometer_timestamp;
}
mag[0] = raw.magnetometer_ga[0];
mag[1] = raw.magnetometer_ga[1];
mag[2] = raw.magnetometer_ga[2];
/* initialize with good values once we have a reasonable dt estimate */
if (!state_initialized && dt < 0.05f && dt > 0.001f) {
state_initialized = true;
warnx("state initialized");
}
/* do not execute the filter if not initialized */
if (!state_initialized) {
continue;
}
uint64_t timing_start = hrt_absolute_time();
// NOTE : Accelerometer is reversed.
// Because proper mount of PX4 will give you a reversed accelerometer readings.
standardECFnew(gyro[0], gyro[1], gyro[2],
-acc[0], -acc[1], -acc[2],
mag[0], mag[1], mag[2],
so3_comp_params.Ka,
so3_comp_params.Km,
so3_comp_params.Kp,
so3_comp_params.Ki,
dt);
// direction cosine matrix of 1-2-3 sequence
// Resulted Rotation matrix convert from Inertial frame to body frame
Rot_matrix[0] = q0q0 + q1q1 - q2q2 - q3q3; // R11
Rot_matrix[1] = 2.f * (q1*q2 + q0*q3); // R12
Rot_matrix[2] = 2.f * (q1*q3 - q0*q2); // R13
Rot_matrix[3] = 2.f * (q1*q2 - q0*q3); // R21
Rot_matrix[4] = q0q0 - q1q1 + q2q2 - q3q3; // R22
Rot_matrix[5] = 2.f * (q2*q3 + q0*q1); // R23
Rot_matrix[6] = 2.f * (q1*q3 + q0*q2); // R31
Rot_matrix[7] = 2.f * (q2*q3 - q0*q1); // R32
Rot_matrix[8] = q0q0 - q1q1 - q2q2 + q3q3; // R33
// Euler Angles using Unit Quaternions;
euler[0]= atan2f((2.0f*(q2q3+q0q1)),1.0f-2.0f*(q1q1+q2q2)); // Roll
euler[1]= asinf(-2.0f*(q1q3-q0q2)); // Pitch
euler[2]= atan2f((2.0f*(q1q2+q0q3)),1.0f-2.0f*(q2q2+q3q3)); // Yaw
/* swap values for next iteration, check for fatal inputs */
if (isfinite(euler[0]) && isfinite(euler[1]) && isfinite(euler[2])) {
// Publish only finite euler angles
att.roll = euler[0] - so3_comp_params.roll_off;
att.pitch = euler[1] - so3_comp_params.pitch_off;
att.yaw = euler[2] - so3_comp_params.yaw_off;
} else {
/* due to inputs or numerical failure the output is invalid, skip it */
// Due to inputs or numerical failure the output is invalid
warnx("infinite euler angles, rotation matrix:");
warnx("%.3f %.3f %.3f", (double)Rot_matrix[0], (double)Rot_matrix[1], (double)Rot_matrix[2]);
warnx("%.3f %.3f %.3f", (double)Rot_matrix[3], (double)Rot_matrix[4], (double)Rot_matrix[5]);
warnx("%.3f %.3f %.3f", (double)Rot_matrix[6], (double)Rot_matrix[7], (double)Rot_matrix[8]);
// Don't publish anything
continue;
}
if (last_data > 0 && raw.timestamp > last_data + 12000) {
warnx("sensor data missed");
}
last_data = raw.timestamp;
/* send out */
att.timestamp = raw.timestamp;
// Quaternion
att.q[0] = q0;
att.q[1] = q1;
att.q[2] = q2;
att.q[3] = q3;
att.q_valid = true;
// Euler angle rate. But it needs to be investigated again.
/*
att.rollspeed = 2.0f*(-q1*dq0 + q0*dq1 - q3*dq2 + q2*dq3);
att.pitchspeed = 2.0f*(-q2*dq0 + q3*dq1 + q0*dq2 - q1*dq3);
att.yawspeed = 2.0f*(-q3*dq0 -q2*dq1 + q1*dq2 + q0*dq3);
*/
att.rollspeed = gyro[0];
att.pitchspeed = gyro[1];
att.yawspeed = gyro[2];
att.rollacc = 0;
att.pitchacc = 0;
att.yawacc = 0;
/* TODO: Bias estimation required */
memcpy(&att.rate_offsets, &(gyro_bias), sizeof(att.rate_offsets));
/* copy rotation matrix */
memcpy(&att.R, Rot_matrix, sizeof(float)*9);
att.R_valid = true;
// Publish
if (att_pub > 0) {
orb_publish(ORB_ID(vehicle_attitude), att_pub, &att);
} else {
warnx("NaN in roll/pitch/yaw estimate!");
orb_advertise(ORB_ID(vehicle_attitude), &att);
}
perf_end(so3_comp_loop_perf);
}
}
}
loopcounter++;
}
// here the main loop stop
thread_running = false;
return 0;
}
/**
* Constructor
*/
VtolAttitudeControl::VtolAttitudeControl() :
_task_should_exit(false),
_control_task(-1),
//init subscription handlers
_v_att_sub(-1),
_v_att_sp_sub(-1),
_mc_virtual_v_rates_sp_sub(-1),
_fw_virtual_v_rates_sp_sub(-1),
_v_control_mode_sub(-1),
_params_sub(-1),
_manual_control_sp_sub(-1),
_armed_sub(-1),
_local_pos_sub(-1),
_airspeed_sub(-1),
_battery_status_sub(-1),
//init publication handlers
_actuators_0_pub(nullptr),
_actuators_1_pub(nullptr),
_vtol_vehicle_status_pub(nullptr),
_v_rates_sp_pub(nullptr)
{
memset(& _vtol_vehicle_status, 0, sizeof(_vtol_vehicle_status));
_vtol_vehicle_status.vtol_in_rw_mode = true; /* start vtol in rotary wing mode*/
memset(&_v_att, 0, sizeof(_v_att));
memset(&_v_att_sp, 0, sizeof(_v_att_sp));
memset(&_v_rates_sp, 0, sizeof(_v_rates_sp));
memset(&_mc_virtual_v_rates_sp, 0, sizeof(_mc_virtual_v_rates_sp));
memset(&_fw_virtual_v_rates_sp, 0, sizeof(_fw_virtual_v_rates_sp));
memset(&_manual_control_sp, 0, sizeof(_manual_control_sp));
memset(&_v_control_mode, 0, sizeof(_v_control_mode));
memset(&_vtol_vehicle_status, 0, sizeof(_vtol_vehicle_status));
memset(&_actuators_out_0, 0, sizeof(_actuators_out_0));
memset(&_actuators_out_1, 0, sizeof(_actuators_out_1));
memset(&_actuators_mc_in, 0, sizeof(_actuators_mc_in));
memset(&_actuators_fw_in, 0, sizeof(_actuators_fw_in));
memset(&_armed, 0, sizeof(_armed));
memset(&_local_pos,0,sizeof(_local_pos));
memset(&_airspeed,0,sizeof(_airspeed));
memset(&_batt_status,0,sizeof(_batt_status));
_params.idle_pwm_mc = PWM_LOWEST_MIN;
_params.vtol_motor_count = 0;
_params.vtol_fw_permanent_stab = 0;
_params_handles.idle_pwm_mc = param_find("VT_IDLE_PWM_MC");
_params_handles.vtol_motor_count = param_find("VT_MOT_COUNT");
_params_handles.vtol_fw_permanent_stab = param_find("VT_FW_PERM_STAB");
_params_handles.mc_airspeed_min = param_find("VT_MC_ARSPD_MIN");
_params_handles.mc_airspeed_max = param_find("VT_MC_ARSPD_MAX");
_params_handles.mc_airspeed_trim = param_find("VT_MC_ARSPD_TRIM");
_params_handles.fw_pitch_trim = param_find("VT_FW_PITCH_TRIM");
_params_handles.power_max = param_find("VT_POWER_MAX");
_params_handles.prop_eff = param_find("VT_PROP_EFF");
_params_handles.arsp_lp_gain = param_find("VT_ARSP_LP_GAIN");
_params_handles.vtol_type = param_find("VT_TYPE");
_params_handles.elevons_mc_lock = param_find("VT_ELEV_MC_LOCK");
/* fetch initial parameter values */
parameters_update();
if (_params.vtol_type == 0) {
_tailsitter = new Tailsitter(this);
_vtol_type = _tailsitter;
} else if (_params.vtol_type == 1) {
_tiltrotor = new Tiltrotor(this);
_vtol_type = _tiltrotor;
} else {
_task_should_exit = true;
}
}
void Standard::update_vtol_state()
{
parameters_update();
/* After flipping the switch the vehicle will start the pusher (or tractor) motor, picking up
* forward speed. After the vehicle has picked up enough speed the rotors shutdown.
* For the back transition the pusher motor is immediately stopped and rotors reactivated.
*/
if (_manual_control_sp->aux1 < 0.0f) {
// the transition to fw mode switch is off
if (_vtol_schedule.flight_mode == MC_MODE) {
// in mc mode
_vtol_schedule.flight_mode = MC_MODE;
_mc_roll_weight = 1.0f;
_mc_pitch_weight = 1.0f;
_mc_yaw_weight = 1.0f;
} else if (_vtol_schedule.flight_mode == FW_MODE) {
// transition to mc mode
_vtol_schedule.flight_mode = TRANSITION_TO_MC;
_flag_enable_mc_motors = true;
_vtol_schedule.transition_start = hrt_absolute_time();
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_FW) {
// failsafe back to mc mode
_vtol_schedule.flight_mode = MC_MODE;
_mc_roll_weight = 1.0f;
_mc_pitch_weight = 1.0f;
_mc_yaw_weight = 1.0f;
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_MC) {
// keep transitioning to mc mode
_vtol_schedule.flight_mode = MC_MODE;
}
// the pusher motor should never be powered when in or transitioning to mc mode
_pusher_throttle = 0.0f;
} else {
// the transition to fw mode switch is on
if (_vtol_schedule.flight_mode == MC_MODE) {
// start transition to fw mode
_vtol_schedule.flight_mode = TRANSITION_TO_FW;
_vtol_schedule.transition_start = hrt_absolute_time();
} else if (_vtol_schedule.flight_mode == FW_MODE) {
// in fw mode
_vtol_schedule.flight_mode = FW_MODE;
_mc_roll_weight = 0.0f;
_mc_pitch_weight = 0.0f;
_mc_yaw_weight = 0.0f;
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_FW) {
// continue the transition to fw mode while monitoring airspeed for a final switch to fw mode
if (_airspeed->true_airspeed_m_s >= _params_standard.airspeed_trans) {
_vtol_schedule.flight_mode = FW_MODE;
// we can turn off the multirotor motors now
_flag_enable_mc_motors = false;
// don't set pusher throttle here as it's being ramped up elsewhere
}
} else if (_vtol_schedule.flight_mode == TRANSITION_TO_MC) {
// transitioning to mc mode & transition switch on - failsafe back into fw mode
_vtol_schedule.flight_mode = FW_MODE;
}
}
// map specific control phases to simple control modes
switch(_vtol_schedule.flight_mode) {
case MC_MODE:
_vtol_mode = ROTARY_WING;
break;
case FW_MODE:
_vtol_mode = FIXED_WING;
break;
case TRANSITION_TO_FW:
case TRANSITION_TO_MC:
_vtol_mode = TRANSITION;
break;
}
}
void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_sp,
const struct vehicle_attitude_s *att, struct vehicle_rates_setpoint_s *rates_sp, struct actuator_controls_s *actuators)
{
static uint64_t last_run = 0;
static uint64_t last_input = 0;
float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
float dT_input = (hrt_absolute_time() - last_input) / 1000000.0f;
last_run = hrt_absolute_time();
if (last_input != att_sp->timestamp) {
last_input = att_sp->timestamp;
}
static int sensor_delay;
sensor_delay = hrt_absolute_time() - att->timestamp;
static int motor_skip_counter = 0;
static PID_t pitch_controller;
static PID_t roll_controller;
static struct mc_att_control_params p;
static struct mc_att_control_param_handles h;
static bool initialized = false;
/* initialize the pid controllers when the function is called for the first time */
if (initialized == false) {
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&pitch_controller, p.att_p, p.att_i, p.att_d, 1000.0f,
1000.0f, PID_MODE_DERIVATIV_SET);
pid_init(&roll_controller, p.att_p, p.att_i, p.att_d, 1000.0f,
1000.0f, PID_MODE_DERIVATIV_SET);
initialized = true;
}
/* load new parameters with lower rate */
if (motor_skip_counter % 1000 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
//printf("att ctrl: delays: %d us sens->ctrl, rate: %d Hz, input: %d Hz\n", sensor_delay, (int)(1.0f/deltaT), (int)(1.0f/dT_input));
/* apply parameters */
pid_set_parameters(&pitch_controller, p.att_p, p.att_i, p.att_d, 1000.0f, 1000.0f);
pid_set_parameters(&roll_controller, p.att_p, p.att_i, p.att_d, 1000.0f, 1000.0f);
}
/* calculate current control outputs */
/* control pitch (forward) output */
rates_sp->pitch = pid_calculate(&pitch_controller, att_sp->pitch_body ,
att->pitch, att->pitchspeed, deltaT);
/* control roll (left/right) output */
rates_sp->roll = pid_calculate(&roll_controller, att_sp->roll_body ,
att->roll, att->rollspeed, deltaT);
/* control yaw rate */
rates_sp->yaw = p.yaw_p * atan2f(cosf(att->yaw - att_sp->yaw_body), sinf(att->yaw - att_sp->yaw_body)) - (p.yaw_d * att->yawspeed);
rates_sp->thrust = att_sp->thrust;
motor_skip_counter++;
}
void VtolAttitudeControl::task_main()
{
warnx("started");
fflush(stdout);
/* do subscriptions */
_v_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_mc_virtual_v_rates_sp_sub = orb_subscribe(ORB_ID(mc_virtual_rates_setpoint));
_fw_virtual_v_rates_sp_sub = orb_subscribe(ORB_ID(fw_virtual_rates_setpoint));
_v_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
_v_control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_manual_control_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
_local_pos_sub = orb_subscribe(ORB_ID(vehicle_local_position));
_airspeed_sub = orb_subscribe(ORB_ID(airspeed));
_battery_status_sub = orb_subscribe(ORB_ID(battery_status));
_actuator_inputs_mc = orb_subscribe(ORB_ID(actuator_controls_virtual_mc));
_actuator_inputs_fw = orb_subscribe(ORB_ID(actuator_controls_virtual_fw));
parameters_update(); // initialize parameter cache
/* update vtol vehicle status*/
_vtol_vehicle_status.fw_permanent_stab = _params.vtol_fw_permanent_stab == 1 ? true : false;
// make sure we start with idle in mc mode
_vtol_type->set_idle_mc();
/* wakeup source*/
struct pollfd fds[3]; /*input_mc, input_fw, parameters*/
fds[0].fd = _actuator_inputs_mc;
fds[0].events = POLLIN;
fds[1].fd = _actuator_inputs_fw;
fds[1].events = POLLIN;
fds[2].fd = _params_sub;
fds[2].events = POLLIN;
while (!_task_should_exit) {
/*Advertise/Publish vtol vehicle status*/
if (_vtol_vehicle_status_pub != nullptr) {
orb_publish(ORB_ID(vtol_vehicle_status), _vtol_vehicle_status_pub, &_vtol_vehicle_status);
} else {
_vtol_vehicle_status.timestamp = hrt_absolute_time();
_vtol_vehicle_status_pub = orb_advertise(ORB_ID(vtol_vehicle_status), &_vtol_vehicle_status);
}
/* wait for up to 100ms for data */
int pret = poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 100);
/* timed out - periodic check for _task_should_exit */
if (pret == 0) {
continue;
}
/* this is undesirable but not much we can do - might want to flag unhappy status */
if (pret < 0) {
warn("poll error %d, %d", pret, errno);
/* sleep a bit before next try */
usleep(100000);
continue;
}
if (fds[2].revents & POLLIN) { //parameters were updated, read them now
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), _params_sub, &update);
/* update parameters from storage */
parameters_update();
}
_vtol_vehicle_status.fw_permanent_stab = _params.vtol_fw_permanent_stab == 1 ? true : false;
vehicle_control_mode_poll(); //Check for changes in vehicle control mode.
vehicle_manual_poll(); //Check for changes in manual inputs.
arming_status_poll(); //Check for arming status updates.
actuator_controls_mc_poll(); //Check for changes in mc_attitude_control output
actuator_controls_fw_poll(); //Check for changes in fw_attitude_control output
vehicle_rates_sp_mc_poll();
vehicle_rates_sp_fw_poll();
parameters_update_poll();
vehicle_local_pos_poll(); // Check for new sensor values
vehicle_airspeed_poll();
vehicle_battery_poll();
// update the vtol state machine which decides which mode we are in
_vtol_type->update_vtol_state();
// check in which mode we are in and call mode specific functions
if (_vtol_type->get_mode() == ROTARY_WING) {
// vehicle is in rotary wing mode
_vtol_vehicle_status.vtol_in_rw_mode = true;
_vtol_type->update_mc_state();
// got data from mc attitude controller
if (fds[0].revents & POLLIN) {
orb_copy(ORB_ID(actuator_controls_virtual_mc), _actuator_inputs_mc, &_actuators_mc_in);
_vtol_type->process_mc_data();
fill_mc_att_rates_sp();
}
} else if (_vtol_type->get_mode() == FIXED_WING) {
// vehicle is in fw mode
_vtol_vehicle_status.vtol_in_rw_mode = false;
_vtol_type->update_fw_state();
// got data from fw attitude controller
if (fds[1].revents & POLLIN) {
orb_copy(ORB_ID(actuator_controls_virtual_fw), _actuator_inputs_fw, &_actuators_fw_in);
vehicle_manual_poll();
_vtol_type->process_fw_data();
fill_fw_att_rates_sp();
}
} else if (_vtol_type->get_mode() == TRANSITION) {
// vehicle is doing a transition
bool got_new_data = false;
if (fds[0].revents & POLLIN) {
orb_copy(ORB_ID(actuator_controls_virtual_mc), _actuator_inputs_mc, &_actuators_mc_in);
got_new_data = true;
}
if (fds[1].revents & POLLIN) {
orb_copy(ORB_ID(actuator_controls_virtual_fw), _actuator_inputs_fw, &_actuators_fw_in);
got_new_data = true;
}
// update transition state if got any new data
if (got_new_data) {
_vtol_type->update_transition_state();
}
} else if (_vtol_type->get_mode() == EXTERNAL) {
// we are using external module to generate attitude/thrust setpoint
_vtol_type->update_external_state();
}
/* Only publish if the proper mode(s) are enabled */
if(_v_control_mode.flag_control_attitude_enabled ||
_v_control_mode.flag_control_rates_enabled ||
_v_control_mode.flag_control_manual_enabled)
{
if (_actuators_0_pub != nullptr) {
orb_publish(ORB_ID(actuator_controls_0), _actuators_0_pub, &_actuators_out_0);
} else {
_actuators_0_pub = orb_advertise(ORB_ID(actuator_controls_0), &_actuators_out_0);
}
if (_actuators_1_pub != nullptr) {
orb_publish(ORB_ID(actuator_controls_1), _actuators_1_pub, &_actuators_out_1);
} else {
_actuators_1_pub = orb_advertise(ORB_ID(actuator_controls_1), &_actuators_out_1);
}
}
// publish the attitude rates setpoint
if(_v_rates_sp_pub != nullptr) {
orb_publish(ORB_ID(vehicle_rates_setpoint),_v_rates_sp_pub,&_v_rates_sp);
}
else {
_v_rates_sp_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint),&_v_rates_sp);
}
}
warnx("exit");
_control_task = -1;
_exit(0);
}
void
Sensors::parameter_update_poll(bool forced)
{
bool param_updated;
/* Check if any parameter has changed */
orb_check(_params_sub, ¶m_updated);
if (param_updated || forced) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), _params_sub, &update);
/* update parameters */
parameters_update();
/* update sensor offsets */
int fd = open(GYRO_DEVICE_PATH, 0);
struct gyro_scale gscale = {
_parameters.gyro_offset[0],
_parameters.gyro_scale[0],
_parameters.gyro_offset[1],
_parameters.gyro_scale[1],
_parameters.gyro_offset[2],
_parameters.gyro_scale[2],
};
if (OK != ioctl(fd, GYROIOCSSCALE, (long unsigned int)&gscale)) {
warn("WARNING: failed to set scale / offsets for gyro");
}
close(fd);
fd = open(ACCEL_DEVICE_PATH, 0);
struct accel_scale ascale = {
_parameters.accel_offset[0],
_parameters.accel_scale[0],
_parameters.accel_offset[1],
_parameters.accel_scale[1],
_parameters.accel_offset[2],
_parameters.accel_scale[2],
};
if (OK != ioctl(fd, ACCELIOCSSCALE, (long unsigned int)&ascale)) {
warn("WARNING: failed to set scale / offsets for accel");
}
close(fd);
fd = open(MAG_DEVICE_PATH, 0);
struct mag_scale mscale = {
_parameters.mag_offset[0],
_parameters.mag_scale[0],
_parameters.mag_offset[1],
_parameters.mag_scale[1],
_parameters.mag_offset[2],
_parameters.mag_scale[2],
};
if (OK != ioctl(fd, MAGIOCSSCALE, (long unsigned int)&mscale)) {
warn("WARNING: failed to set scale / offsets for mag");
}
close(fd);
fd = open(AIRSPEED_DEVICE_PATH, 0);
/* this sensor is optional, abort without error */
if (fd > 0) {
struct airspeed_scale airscale = {
_parameters.diff_pres_offset_pa,
1.0f,
};
if (OK != ioctl(fd, AIRSPEEDIOCSSCALE, (long unsigned int)&airscale)) {
warn("WARNING: failed to set scale / offsets for airspeed sensor");
}
close(fd);
}
#if 0
printf("CH0: RAW MAX: %d MIN %d S: %d MID: %d FUNC: %d\n", (int)_parameters.max[0], (int)_parameters.min[0], (int)(_rc.chan[0].scaling_factor * 10000), (int)(_rc.chan[0].mid), (int)_rc.function[0]);
printf("CH1: RAW MAX: %d MIN %d S: %d MID: %d FUNC: %d\n", (int)_parameters.max[1], (int)_parameters.min[1], (int)(_rc.chan[1].scaling_factor * 10000), (int)(_rc.chan[1].mid), (int)_rc.function[1]);
printf("MAN: %d %d\n", (int)(_rc.chan[0].scaled * 100), (int)(_rc.chan[1].scaled * 100));
fflush(stdout);
usleep(5000);
#endif
}
}
