int
HMC5883::collect()
{
#pragma pack(push, 1)
struct { /* status register and data as read back from the device */
uint8_t x[2];
uint8_t z[2];
uint8_t y[2];
} hmc_report;
#pragma pack(pop)
struct {
int16_t x, y, z;
} report;
int ret;
uint8_t check_counter;
perf_begin(_sample_perf);
struct mag_report new_report;
bool sensor_is_onboard = false;
float xraw_f;
float yraw_f;
float zraw_f;
/* this should be fairly close to the end of the measurement, so the best approximation of the time */
new_report.timestamp = hrt_absolute_time();
new_report.error_count = perf_event_count(_comms_errors);
/*
* @note We could read the status register here, which could tell us that
* we were too early and that the output registers are still being
* written. In the common case that would just slow us down, and
* we're better off just never being early.
*/
/* get measurements from the device */
ret = _interface->read(ADDR_DATA_OUT_X_MSB, (uint8_t *)&hmc_report, sizeof(hmc_report));
if (ret != OK) {
perf_count(_comms_errors);
DEVICE_DEBUG("data/status read error");
goto out;
}
/* swap the data we just received */
report.x = (((int16_t)hmc_report.x[0]) << 8) + hmc_report.x[1];
report.y = (((int16_t)hmc_report.y[0]) << 8) + hmc_report.y[1];
report.z = (((int16_t)hmc_report.z[0]) << 8) + hmc_report.z[1];
/*
* If any of the values are -4096, there was an internal math error in the sensor.
* Generalise this to a simple range check that will also catch some bit errors.
*/
if ((abs(report.x) > 2048) ||
(abs(report.y) > 2048) ||
(abs(report.z) > 2048)) {
perf_count(_comms_errors);
goto out;
}
/* get measurements from the device */
new_report.temperature = 0;
if (_conf_reg & HMC5983_TEMP_SENSOR_ENABLE) {
/*
if temperature compensation is enabled read the
temperature too.
We read the temperature every 10 samples to avoid
excessive I2C traffic
*/
if (_temperature_counter++ == 10) {
uint8_t raw_temperature[2];
_temperature_counter = 0;
ret = _interface->read(ADDR_TEMP_OUT_MSB,
raw_temperature, sizeof(raw_temperature));
if (ret == OK) {
int16_t temp16 = (((int16_t)raw_temperature[0]) << 8) +
raw_temperature[1];
new_report.temperature = 25 + (temp16 / (16 * 8.0f));
_temperature_error_count = 0;
} else {
_temperature_error_count++;
if (_temperature_error_count == 10) {
/*
it probably really is an old HMC5883,
and can't do temperature. Disable it
*/
_temperature_error_count = 0;
DEVICE_DEBUG("disabling temperature compensation");
set_temperature_compensation(0);
}
}
} else {
new_report.temperature = _last_report.temperature;
}
}
/*
* RAW outputs
*
* to align the sensor axes with the board, x and y need to be flipped
* and y needs to be negated
*/
new_report.x_raw = report.y;
new_report.y_raw = -report.x;
/* z remains z */
new_report.z_raw = report.z;
/* scale values for output */
// XXX revisit for SPI part, might require a bus type IOCTL
unsigned dummy;
sensor_is_onboard = !_interface->ioctl(MAGIOCGEXTERNAL, dummy);
if (sensor_is_onboard) {
// convert onboard so it matches offboard for the
// scaling below
report.y = -report.y;
report.x = -report.x;
}
/* the standard external mag by 3DR has x pointing to the
* right, y pointing backwards, and z down, therefore switch x
* and y and invert y */
xraw_f = -report.y;
yraw_f = report.x;
zraw_f = report.z;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
new_report.x = ((xraw_f * _range_scale) - _scale.x_offset) * _scale.x_scale;
/* flip axes and negate value for y */
new_report.y = ((yraw_f * _range_scale) - _scale.y_offset) * _scale.y_scale;
/* z remains z */
new_report.z = ((zraw_f * _range_scale) - _scale.z_offset) * _scale.z_scale;
if (!(_pub_blocked)) {
if (_mag_topic != nullptr) {
/* publish it */
orb_publish(ORB_ID(sensor_mag), _mag_topic, &new_report);
} else {
_mag_topic = orb_advertise_multi(ORB_ID(sensor_mag), &new_report,
&_orb_class_instance, (sensor_is_onboard) ? ORB_PRIO_HIGH : ORB_PRIO_MAX);
if (_mag_topic == nullptr) {
DEVICE_DEBUG("ADVERT FAIL");
}
}
}
_last_report = new_report;
/* post a report to the ring */
if (_reports->force(&new_report)) {
perf_count(_buffer_overflows);
}
/* notify anyone waiting for data */
poll_notify(POLLIN);
/*
periodically check the range register and configuration
registers. With a bad I2C cable it is possible for the
registers to become corrupt, leading to bad readings. It
doesn't happen often, but given the poor cables some
vehicles have it is worth checking for.
*/
check_counter = perf_event_count(_sample_perf) % 256;
if (check_counter == 0) {
check_range();
}
if (check_counter == 128) {
check_conf();
}
ret = OK;
out:
perf_end(_sample_perf);
return ret;
}
/**
* Transition from one hil state to another
*/
transition_result_t hil_state_transition(hil_state_t new_state, orb_advert_t status_pub, struct vehicle_status_s *current_status, const int mavlink_fd)
{
transition_result_t ret = TRANSITION_DENIED;
if (current_status->hil_state == new_state) {
ret = TRANSITION_NOT_CHANGED;
} else {
switch (new_state) {
case vehicle_status_s::HIL_STATE_OFF:
/* we're in HIL and unexpected things can happen if we disable HIL now */
mavlink_log_critical(mavlink_fd, "Not switching off HIL (safety)");
ret = TRANSITION_DENIED;
break;
case vehicle_status_s::HIL_STATE_ON:
if (current_status->arming_state == vehicle_status_s::ARMING_STATE_INIT
|| current_status->arming_state == vehicle_status_s::ARMING_STATE_STANDBY
|| current_status->arming_state == vehicle_status_s::ARMING_STATE_STANDBY_ERROR) {
#ifdef __PX4_NUTTX
/* Disable publication of all attached sensors */
/* list directory */
DIR *d;
d = opendir("/dev");
if (d) {
struct dirent *direntry;
char devname[24];
while ((direntry = readdir(d)) != NULL) {
/* skip serial ports */
if (!strncmp("tty", direntry->d_name, 3)) {
continue;
}
/* skip mtd devices */
if (!strncmp("mtd", direntry->d_name, 3)) {
continue;
}
/* skip ram devices */
if (!strncmp("ram", direntry->d_name, 3)) {
continue;
}
/* skip MMC devices */
if (!strncmp("mmc", direntry->d_name, 3)) {
continue;
}
/* skip mavlink */
if (!strcmp("mavlink", direntry->d_name)) {
continue;
}
/* skip console */
if (!strcmp("console", direntry->d_name)) {
continue;
}
/* skip null */
if (!strcmp("null", direntry->d_name)) {
continue;
}
snprintf(devname, sizeof(devname), "/dev/%s", direntry->d_name);
int sensfd = ::open(devname, 0);
if (sensfd < 0) {
warn("failed opening device %s", devname);
continue;
}
int block_ret = ::ioctl(sensfd, DEVIOCSPUBBLOCK, 1);
close(sensfd);
printf("Disabling %s: %s\n", devname, (block_ret == OK) ? "OK" : "ERROR");
}
closedir(d);
ret = TRANSITION_CHANGED;
mavlink_log_critical(mavlink_fd, "Switched to ON hil state");
} else {
/* failed opening dir */
mavlink_log_info(mavlink_fd, "FAILED LISTING DEVICE ROOT DIRECTORY");
ret = TRANSITION_DENIED;
}
#else
const char *devname;
unsigned int handle = 0;
for(;;) {
devname = px4_get_device_names(&handle);
if (devname == NULL)
break;
/* skip mavlink */
if (!strcmp("/dev/mavlink", devname)) {
continue;
}
int sensfd = px4_open(devname, 0);
if (sensfd < 0) {
warn("failed opening device %s", devname);
continue;
}
int block_ret = px4_ioctl(sensfd, DEVIOCSPUBBLOCK, 1);
px4_close(sensfd);
printf("Disabling %s: %s\n", devname, (block_ret == OK) ? "OK" : "ERROR");
}
ret = TRANSITION_CHANGED;
mavlink_log_critical(mavlink_fd, "Switched to ON hil state");
#endif
} else {
mavlink_log_critical(mavlink_fd, "Not switching to HIL when armed");
ret = TRANSITION_DENIED;
}
break;
default:
warnx("Unknown HIL state");
break;
}
}
if (ret == TRANSITION_CHANGED) {
current_status->hil_state = new_state;
current_status->timestamp = hrt_absolute_time();
// XXX also set lockdown here
orb_publish(ORB_ID(vehicle_status), status_pub, current_status);
}
return ret;
}
int LidarLiteI2C::collect()
{
int ret = -EIO;
/* read from the sensor */
uint8_t val[2] = {0, 0};
perf_begin(_sample_perf);
// read the high and low byte distance registers
uint8_t distance_reg = LL40LS_DISTHIGH_REG;
ret = transfer(&distance_reg, 1, &val[0], sizeof(val));
if (ret < 0) {
if (hrt_absolute_time() - _acquire_time_usec > LL40LS_CONVERSION_TIMEOUT) {
/*
NACKs from the sensor are expected when we
read before it is ready, so only consider it
an error if more than 100ms has elapsed.
*/
debug("error reading from sensor: %d", ret);
perf_count(_comms_errors);
if (perf_event_count(_comms_errors) % 10 == 0) {
perf_count(_sensor_resets);
reset_sensor();
}
}
perf_end(_sample_perf);
// if we are getting lots of I2C transfer errors try
// resetting the sensor
return ret;
}
uint16_t distance_cm = (val[0] << 8) | val[1];
float distance_m = float(distance_cm) * 1e-2f;
struct distance_sensor_s report;
if (distance_cm == 0) {
_zero_counter++;
if (_zero_counter == 20) {
/* we have had 20 zeros in a row - reset the
sensor. This is a known bad state of the
sensor where it returns 16 bits of zero for
the distance with a trailing NACK, and
keeps doing that even when the target comes
into a valid range.
*/
_zero_counter = 0;
perf_end(_sample_perf);
perf_count(_sensor_zero_resets);
return reset_sensor();
}
} else {
_zero_counter = 0;
}
_last_distance = distance_m;
/* this should be fairly close to the end of the measurement, so the best approximation of the time */
report.timestamp = hrt_absolute_time();
report.current_distance = distance_m;
report.min_distance = get_minimum_distance();
report.max_distance = get_maximum_distance();
report.covariance = 0.0f;
/* the sensor is in fact a laser + sonar but there is no enum for this */
report.type = distance_sensor_s::MAV_DISTANCE_SENSOR_LASER;
report.orientation = 8;
/* TODO: set proper ID */
report.id = 0;
/* publish it, if we are the primary */
if (_distance_sensor_topic >= 0) {
orb_publish(ORB_ID(distance_sensor), _distance_sensor_topic, &report);
}
if (_reports->force(&report)) {
perf_count(_buffer_overflows);
}
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
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_multi(ORB_ID(sensor_accel), 0);
_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));
_vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
/* 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();
vehicle_status_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;
_task_running = true;
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);
if (_vehicle_status.is_vtol) {
/* vehicle type is VTOL, need to modify attitude!
* The following modification to the attitude is vehicle specific and in this case applies
* to tail-sitter models !!!
*
* Since the VTOL airframe is initialized as a multicopter we need to
* modify the estimated attitude for the fixed wing operation.
* Since the neutral position of the vehicle in fixed wing mode is -90 degrees rotated around
* the pitch axis compared to the neutral position of the vehicle in multicopter mode
* we need to swap the roll and the yaw axis (1st and 3rd column) in the rotation matrix.
* Additionally, in order to get the correct sign of the pitch, we need to multiply
* the new x axis of the rotation matrix with -1
*
* original: modified:
*
* Rxx Ryx Rzx -Rzx Ryx Rxx
* Rxy Ryy Rzy -Rzy Ryy Rxy
* Rxz Ryz Rzz -Rzz Ryz Rxz
* */
math::Matrix<3, 3> R; //original rotation matrix
math::Matrix<3, 3> R_adapted; //modified rotation matrix
R.set(_att.R);
R_adapted.set(_att.R);
/* move z to x */
R_adapted(0, 0) = R(0, 2);
R_adapted(1, 0) = R(1, 2);
R_adapted(2, 0) = R(2, 2);
/* move x to z */
R_adapted(0, 2) = R(0, 0);
R_adapted(1, 2) = R(1, 0);
R_adapted(2, 2) = R(2, 0);
/* change direction of pitch (convert to right handed system) */
R_adapted(0, 0) = -R_adapted(0, 0);
R_adapted(1, 0) = -R_adapted(1, 0);
R_adapted(2, 0) = -R_adapted(2, 0);
math::Vector<3> euler_angles; //adapted euler angles for fixed wing operation
euler_angles = R_adapted.to_euler();
/* fill in new attitude data */
_att.roll = euler_angles(0);
_att.pitch = euler_angles(1);
_att.yaw = euler_angles(2);
PX4_R(_att.R, 0, 0) = R_adapted(0, 0);
PX4_R(_att.R, 0, 1) = R_adapted(0, 1);
PX4_R(_att.R, 0, 2) = R_adapted(0, 2);
PX4_R(_att.R, 1, 0) = R_adapted(1, 0);
PX4_R(_att.R, 1, 1) = R_adapted(1, 1);
PX4_R(_att.R, 1, 2) = R_adapted(1, 2);
PX4_R(_att.R, 2, 0) = R_adapted(2, 0);
PX4_R(_att.R, 2, 1) = R_adapted(2, 1);
PX4_R(_att.R, 2, 2) = R_adapted(2, 2);
/* lastly, roll- and yawspeed have to be swaped */
float helper = _att.rollspeed;
_att.rollspeed = -_att.yawspeed;
_att.yawspeed = helper;
}
vehicle_airspeed_poll();
vehicle_setpoint_poll();
vehicle_accel_poll();
vehicle_control_mode_poll();
vehicle_manual_poll();
global_pos_poll();
vehicle_status_poll();
/* lock integrator until control is started */
bool lock_integrator;
if (_vcontrol_mode.flag_control_attitude_enabled && !_vehicle_status.is_rotary_wing) {
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[7] = 1.0f;
//warnx("_actuators_airframe.control[1] = 1.0f;");
} else {
_actuators_airframe.control[7] = 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 {
/* prevent numerical drama by requiring 0.5 m/s minimal speed */
airspeed = math::max(0.5f, _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 yaw_manual = 0.0f;
float throttle_sp = 0.0f;
/* Read attitude setpoint from uorb if
* - velocity control or position control is enabled (pos controller is running)
* - manual control is disabled (another app may send the setpoint, but it should
* for sure not be set from the remote control values)
*/
if (_vcontrol_mode.flag_control_auto_enabled ||
!_vcontrol_mode.flag_control_manual_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 if (_vcontrol_mode.flag_control_velocity_enabled) {
/*
* Velocity should be controlled and manual is enabled.
*/
roll_sp = (_manual.y * _parameters.man_roll_max - _parameters.trim_roll)
+ _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;
/* allow manual control of rudder deflection */
yaw_manual = _manual.r;
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 && !_vehicle_status.is_rotary_wing) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_attitude_setpoint), _attitude_sp_pub, &att_sp);
} else if (_attitude_sp_pub < 0 && !_vehicle_status.is_rotary_wing) {
/* advertise and publish */
_attitude_sp_pub = orb_advertise(ORB_ID(vehicle_attitude_setpoint), &att_sp);
}
}
/* If the aircraft is on ground reset the integrators */
if (_vehicle_status.condition_landed || _vehicle_status.is_rotary_wing) {
_roll_ctrl.reset_integrator();
_pitch_ctrl.reset_integrator();
_yaw_ctrl.reset_integrator();
}
/* 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 = PX4_R(_att.R, 0, 0) * _global_pos.vel_n + PX4_R(_att.R, 1, 0) * _global_pos.vel_e + PX4_R(_att.R, 2, 0) * _global_pos.vel_d;
speed_body_v = PX4_R(_att.R, 0, 1) * _global_pos.vel_n + PX4_R(_att.R, 1, 1) * _global_pos.vel_e + PX4_R(_att.R, 2, 1) * _global_pos.vel_d;
speed_body_w = PX4_R(_att.R, 0, 2) * _global_pos.vel_n + PX4_R(_att.R, 1, 2) * _global_pos.vel_e + PX4_R(_att.R, 2, 2) * _global_pos.vel_d;
} else {
if (_debug && loop_counter % 10 == 0) {
warnx("Did not get a valid R\n");
}
}
/* Prepare data for attitude controllers */
struct ECL_ControlData control_input = {};
control_input.roll = _att.roll;
control_input.pitch = _att.pitch;
control_input.yaw = _att.yaw;
control_input.roll_rate = _att.rollspeed;
control_input.pitch_rate = _att.pitchspeed;
control_input.yaw_rate = _att.yawspeed;
control_input.speed_body_u = speed_body_u;
control_input.speed_body_v = speed_body_v;
control_input.speed_body_w = speed_body_w;
control_input.acc_body_x = _accel.x;
control_input.acc_body_y = _accel.y;
control_input.acc_body_z = _accel.z;
control_input.roll_setpoint = roll_sp;
control_input.pitch_setpoint = pitch_sp;
control_input.airspeed_min = _parameters.airspeed_min;
control_input.airspeed_max = _parameters.airspeed_max;
control_input.airspeed = airspeed;
control_input.scaler = airspeed_scaling;
control_input.lock_integrator = lock_integrator;
/* Run attitude controllers */
if (isfinite(roll_sp) && isfinite(pitch_sp)) {
_roll_ctrl.control_attitude(control_input);
_pitch_ctrl.control_attitude(control_input);
_yaw_ctrl.control_attitude(control_input); //runs last, because is depending on output of roll and pitch attitude
/* Update input data for rate controllers */
control_input.roll_rate_setpoint = _roll_ctrl.get_desired_rate();
control_input.pitch_rate_setpoint = _pitch_ctrl.get_desired_rate();
control_input.yaw_rate_setpoint = _yaw_ctrl.get_desired_rate();
/* Run attitude RATE controllers which need the desired attitudes from above, add trim */
float roll_u = _roll_ctrl.control_bodyrate(control_input);
_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 (_debug && loop_counter % 10 == 0) {
warnx("roll_u %.4f", (double)roll_u);
}
}
float pitch_u = _pitch_ctrl.control_bodyrate(control_input);
_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 (_debug && 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(control_input);
_actuators.control[2] = (isfinite(yaw_u)) ? yaw_u + _parameters.trim_yaw : _parameters.trim_yaw;
/* add in manual rudder control */
_actuators.control[2] += yaw_manual;
if (!isfinite(yaw_u)) {
_yaw_ctrl.reset_integrator();
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[3] = (isfinite(throttle_sp) &&
!(_vehicle_status.engine_failure ||
_vehicle_status.engine_failure_cmd)) ?
throttle_sp : 0.0f;
if (!isfinite(throttle_sp)) {
if (_debug && loop_counter % 10 == 0) {
warnx("throttle_sp %.4f", (double)throttle_sp);
}
}
} else {
perf_count(_nonfinite_input_perf);
if (_debug && 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
*/
_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 rates setpoint */
orb_publish(_rates_sp_id, _rate_sp_pub, &_rates_sp);
} else if (_rates_sp_id) {
/* advertise the attitude rates setpoint */
_rate_sp_pub = orb_advertise(_rates_sp_id, &_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.timestamp_sample = _att.timestamp;
_actuators_airframe.timestamp = hrt_absolute_time();
_actuators_airframe.timestamp_sample = _att.timestamp;
/* Only publish if any of the proper modes are enabled */
if(_vcontrol_mode.flag_control_rates_enabled ||
_vcontrol_mode.flag_control_attitude_enabled ||
_vcontrol_mode.flag_control_manual_enabled)
{
/* publish the actuator controls */
if (_actuators_0_pub > 0) {
orb_publish(_actuators_id, _actuators_0_pub, &_actuators);
} else if (_actuators_id) {
_actuators_0_pub= orb_advertise(_actuators_id, &_actuators);
}
if (_actuators_2_pub > 0) {
/* publish the actuator controls*/
orb_publish(ORB_ID(actuator_controls_2), _actuators_2_pub, &_actuators_airframe);
} else {
/* advertise and publish */
_actuators_2_pub = orb_advertise(ORB_ID(actuator_controls_2), &_actuators_airframe);
}
}
}
loop_counter++;
perf_end(_loop_perf);
}
warnx("exiting.\n");
_control_task = -1;
_task_running = false;
_exit(0);
}
void
BMI160::measure()
{
if (hrt_absolute_time() < _reset_wait) {
// we're waiting for a reset to complete
return;
}
struct BMIReport bmi_report;
struct Report {
int16_t accel_x;
int16_t accel_y;
int16_t accel_z;
int16_t temp;
int16_t gyro_x;
int16_t gyro_y;
int16_t gyro_z;
} report;
/* start measuring */
perf_begin(_sample_perf);
/*
* Fetch the full set of measurements from the BMI160 in one pass.
*/
bmi_report.cmd = BMIREG_GYR_X_L | DIR_READ;
set_frequency(BMI160_LOW_BUS_SPEED);
uint8_t status = read_reg(BMIREG_STATUS, BMI160_LOW_BUS_SPEED);
if (OK != transfer((uint8_t *)&bmi_report, ((uint8_t *)&bmi_report), sizeof(bmi_report))) {
return;
}
check_registers();
if ((!(status && (0x80))) && (!(status && (0x04)))) {
perf_end(_sample_perf);
perf_count(_duplicates);
_got_duplicate = true;
return;
}
_last_accel[0] = bmi_report.accel_x;
_last_accel[1] = bmi_report.accel_y;
_last_accel[2] = bmi_report.accel_z;
_got_duplicate = false;
uint8_t temp_l = read_reg(BMIREG_TEMP_0, BMI160_LOW_BUS_SPEED);
uint8_t temp_h = read_reg(BMIREG_TEMP_1, BMI160_LOW_BUS_SPEED);
report.temp = ((temp_h << 8) + temp_l);
report.accel_x = bmi_report.accel_x;
report.accel_y = bmi_report.accel_y;
report.accel_z = bmi_report.accel_z;
report.gyro_x = bmi_report.gyro_x;
report.gyro_y = bmi_report.gyro_y;
report.gyro_z = bmi_report.gyro_z;
if (report.accel_x == 0 &&
report.accel_y == 0 &&
report.accel_z == 0 &&
report.temp == 0 &&
report.gyro_x == 0 &&
report.gyro_y == 0 &&
report.gyro_z == 0) {
// all zero data - probably a SPI bus error
perf_count(_bad_transfers);
perf_end(_sample_perf);
// note that we don't call reset() here as a reset()
// costs 20ms with interrupts disabled. That means if
// the bmi160 does go bad it would cause a FMU failure,
// regardless of whether another sensor is available,
return;
}
perf_count(_good_transfers);
if (_register_wait != 0) {
// we are waiting for some good transfers before using
// the sensor again. We still increment
// _good_transfers, but don't return any data yet
_register_wait--;
return;
}
/*
* Report buffers.
*/
accel_report arb;
gyro_report grb;
/*
* Adjust and scale results to m/s^2.
*/
grb.timestamp = arb.timestamp = hrt_absolute_time();
// report the error count as the sum of the number of bad
// transfers and bad register reads. This allows the higher
// level code to decide if it should use this sensor based on
// whether it has had failures
grb.error_count = arb.error_count = perf_event_count(_bad_transfers) + perf_event_count(_bad_registers);
/*
* 1) Scale raw value to SI units using scaling from datasheet.
* 2) Subtract static offset (in SI units)
* 3) Scale the statically calibrated values with a linear
* dynamically obtained factor
*
* Note: the static sensor offset is the number the sensor outputs
* at a nominally 'zero' input. Therefore the offset has to
* be subtracted.
*
* Example: A gyro outputs a value of 74 at zero angular rate
* the offset is 74 from the origin and subtracting
* 74 from all measurements centers them around zero.
*/
/* NOTE: Axes have been swapped to match the board a few lines above. */
arb.x_raw = report.accel_x;
arb.y_raw = report.accel_y;
arb.z_raw = report.accel_z;
float xraw_f = report.accel_x;
float yraw_f = report.accel_y;
float zraw_f = report.accel_z;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
float x_in_new = ((xraw_f * _accel_range_scale) - _accel_scale.x_offset) * _accel_scale.x_scale;
float y_in_new = ((yraw_f * _accel_range_scale) - _accel_scale.y_offset) * _accel_scale.y_scale;
float z_in_new = ((zraw_f * _accel_range_scale) - _accel_scale.z_offset) * _accel_scale.z_scale;
arb.x = _accel_filter_x.apply(x_in_new);
arb.y = _accel_filter_y.apply(y_in_new);
arb.z = _accel_filter_z.apply(z_in_new);
math::Vector<3> aval(x_in_new, y_in_new, z_in_new);
math::Vector<3> aval_integrated;
bool accel_notify = _accel_int.put(arb.timestamp, aval, aval_integrated, arb.integral_dt);
arb.x_integral = aval_integrated(0);
arb.y_integral = aval_integrated(1);
arb.z_integral = aval_integrated(2);
arb.scaling = _accel_range_scale;
arb.range_m_s2 = _accel_range_m_s2;
_last_temperature = 23 + report.temp * 1.0f / 512.0f;
arb.temperature_raw = report.temp;
arb.temperature = _last_temperature;
grb.x_raw = report.gyro_x;
grb.y_raw = report.gyro_y;
grb.z_raw = report.gyro_z;
xraw_f = report.gyro_x;
yraw_f = report.gyro_y;
zraw_f = report.gyro_z;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
float x_gyro_in_new = ((xraw_f * _gyro_range_scale) - _gyro_scale.x_offset) * _gyro_scale.x_scale;
float y_gyro_in_new = ((yraw_f * _gyro_range_scale) - _gyro_scale.y_offset) * _gyro_scale.y_scale;
float z_gyro_in_new = ((zraw_f * _gyro_range_scale) - _gyro_scale.z_offset) * _gyro_scale.z_scale;
grb.x = _gyro_filter_x.apply(x_gyro_in_new);
grb.y = _gyro_filter_y.apply(y_gyro_in_new);
grb.z = _gyro_filter_z.apply(z_gyro_in_new);
math::Vector<3> gval(x_gyro_in_new, y_gyro_in_new, z_gyro_in_new);
math::Vector<3> gval_integrated;
bool gyro_notify = _gyro_int.put(arb.timestamp, gval, gval_integrated, grb.integral_dt);
grb.x_integral = gval_integrated(0);
grb.y_integral = gval_integrated(1);
grb.z_integral = gval_integrated(2);
grb.scaling = _gyro_range_scale;
grb.range_rad_s = _gyro_range_rad_s;
grb.temperature_raw = report.temp;
grb.temperature = _last_temperature;
_accel_reports->force(&arb);
_gyro_reports->force(&grb);
/* notify anyone waiting for data */
if (accel_notify) {
poll_notify(POLLIN);
}
if (gyro_notify) {
_gyro->parent_poll_notify();
}
if (accel_notify && !(_pub_blocked)) {
/* log the time of this report */
perf_begin(_controller_latency_perf);
/* publish it */
orb_publish(ORB_ID(sensor_accel), _accel_topic, &arb);
}
if (gyro_notify && !(_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(sensor_gyro), _gyro->_gyro_topic, &grb);
}
/* stop measuring */
perf_end(_sample_perf);
}
void
PX4FMU::task_main()
{
/* force a reset of the update rate */
_current_update_rate = 0;
_armed_sub = orb_subscribe(ORB_ID(actuator_armed));
/* advertise the mixed control outputs */
actuator_outputs_s outputs;
memset(&outputs, 0, sizeof(outputs));
#ifdef HRT_PPM_CHANNEL
// rc input, published to ORB
struct rc_input_values rc_in;
orb_advert_t to_input_rc = 0;
memset(&rc_in, 0, sizeof(rc_in));
rc_in.input_source = RC_INPUT_SOURCE_PX4FMU_PPM;
#endif
/* initialize PWM limit lib */
pwm_limit_init(&_pwm_limit);
log("starting");
/* loop until killed */
while (!_task_should_exit) {
if (_groups_subscribed != _groups_required) {
subscribe();
_groups_subscribed = _groups_required;
/* force setting update rate */
_current_update_rate = 0;
}
/*
* Adjust actuator topic update rate to keep up with
* the highest servo update rate configured.
*
* We always mix at max rate; some channels may update slower.
*/
unsigned max_rate = (_pwm_default_rate > _pwm_alt_rate) ? _pwm_default_rate : _pwm_alt_rate;
if (_current_update_rate != max_rate) {
_current_update_rate = max_rate;
int update_rate_in_ms = int(1000 / _current_update_rate);
/* reject faster than 500 Hz updates */
if (update_rate_in_ms < 2) {
update_rate_in_ms = 2;
}
/* reject slower than 10 Hz updates */
if (update_rate_in_ms > 100) {
update_rate_in_ms = 100;
}
debug("adjusted actuator update interval to %ums", update_rate_in_ms);
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (_control_subs[i] > 0) {
orb_set_interval(_control_subs[i], update_rate_in_ms);
}
}
// set to current max rate, even if we are actually checking slower/faster
_current_update_rate = max_rate;
}
/* sleep waiting for data, stopping to check for PPM
* input at 50Hz */
int ret = ::poll(_poll_fds, _poll_fds_num, CONTROL_INPUT_DROP_LIMIT_MS);
/* this would be bad... */
if (ret < 0) {
log("poll error %d", errno);
continue;
} else if (ret == 0) {
/* timeout: no control data, switch to failsafe values */
// warnx("no PWM: failsafe");
} else {
/* get controls for required topics */
unsigned poll_id = 0;
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (_control_subs[i] > 0) {
if (_poll_fds[poll_id].revents & POLLIN) {
orb_copy(_control_topics[i], _control_subs[i], &_controls[i]);
}
poll_id++;
}
}
/* can we mix? */
if (_mixers != nullptr) {
unsigned num_outputs;
switch (_mode) {
case MODE_2PWM:
num_outputs = 2;
break;
case MODE_4PWM:
num_outputs = 4;
break;
case MODE_6PWM:
num_outputs = 6;
break;
case MODE_8PWM:
num_outputs = 8;
break;
default:
num_outputs = 0;
break;
}
/* do mixing */
outputs.noutputs = _mixers->mix(&outputs.output[0], num_outputs);
outputs.timestamp = hrt_absolute_time();
/* iterate actuators */
for (unsigned i = 0; i < num_outputs; i++) {
/* last resort: catch NaN and INF */
if ((i >= outputs.noutputs) ||
!isfinite(outputs.output[i])) {
/*
* Value is NaN, INF or out of band - set to the minimum value.
* This will be clearly visible on the servo status and will limit the risk of accidentally
* spinning motors. It would be deadly in flight.
*/
outputs.output[i] = -1.0f;
}
}
uint16_t pwm_limited[num_outputs];
/* the PWM limit call takes care of out of band errors and constrains */
pwm_limit_calc(_servo_armed, num_outputs, _disarmed_pwm, _min_pwm, _max_pwm, outputs.output, pwm_limited, &_pwm_limit);
/* output to the servos */
for (unsigned i = 0; i < num_outputs; i++) {
up_pwm_servo_set(i, pwm_limited[i]);
}
/* publish mixed control outputs */
if (_outputs_pub < 0) {
_outputs_pub = orb_advertise(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), &outputs);
} else {
orb_publish(_primary_pwm_device ? ORB_ID_VEHICLE_CONTROLS : ORB_ID(actuator_outputs_1), _outputs_pub, &outputs);
}
}
}
/* check arming state */
bool updated = false;
orb_check(_armed_sub, &updated);
if (updated) {
orb_copy(ORB_ID(actuator_armed), _armed_sub, &_armed);
/* update the armed status and check that we're not locked down */
bool set_armed = _armed.armed && !_armed.lockdown;
if (_servo_armed != set_armed)
_servo_armed = set_armed;
/* update PWM status if armed or if disarmed PWM values are set */
bool pwm_on = (_armed.armed || _num_disarmed_set > 0);
if (_pwm_on != pwm_on) {
_pwm_on = pwm_on;
up_pwm_servo_arm(pwm_on);
}
}
#ifdef HRT_PPM_CHANNEL
// see if we have new PPM input data
if (ppm_last_valid_decode != rc_in.timestamp_last_signal) {
// we have a new PPM frame. Publish it.
rc_in.channel_count = ppm_decoded_channels;
if (rc_in.channel_count > RC_INPUT_MAX_CHANNELS) {
rc_in.channel_count = RC_INPUT_MAX_CHANNELS;
}
for (uint8_t i = 0; i < rc_in.channel_count; i++) {
rc_in.values[i] = ppm_buffer[i];
}
rc_in.timestamp_publication = ppm_last_valid_decode;
rc_in.timestamp_last_signal = ppm_last_valid_decode;
rc_in.rc_ppm_frame_length = ppm_frame_length;
rc_in.rssi = RC_INPUT_RSSI_MAX;
rc_in.rc_failsafe = false;
rc_in.rc_lost = false;
rc_in.rc_lost_frame_count = 0;
rc_in.rc_total_frame_count = 0;
/* lazily advertise on first publication */
if (to_input_rc == 0) {
to_input_rc = orb_advertise(ORB_ID(input_rc), &rc_in);
} else {
orb_publish(ORB_ID(input_rc), to_input_rc, &rc_in);
}
}
#endif
}
for (unsigned i = 0; i < NUM_ACTUATOR_CONTROL_GROUPS; i++) {
if (_control_subs[i] > 0) {
::close(_control_subs[i]);
_control_subs[i] = -1;
}
}
::close(_armed_sub);
/* make sure servos are off */
up_pwm_servo_deinit();
log("stopping");
/* note - someone else is responsible for restoring the GPIO config */
/* tell the dtor that we are exiting */
_task = -1;
_exit(0);
}
void
FixedwingEstimator::task_main()
{
_mavlink_fd = open(MAVLINK_LOG_DEVICE, 0);
_ekf = new AttPosEKF();
float dt = 0.0f; // time lapsed since last covariance prediction
_filter_start_time = hrt_absolute_time();
if (!_ekf) {
errx(1, "OUT OF MEM!");
}
/*
* do subscriptions
*/
_baro_sub = orb_subscribe(ORB_ID(sensor_baro));
_airspeed_sub = orb_subscribe(ORB_ID(airspeed));
_gps_sub = orb_subscribe(ORB_ID(vehicle_gps_position));
_vstatus_sub = orb_subscribe(ORB_ID(vehicle_status));
_params_sub = orb_subscribe(ORB_ID(parameter_update));
_home_sub = orb_subscribe(ORB_ID(home_position));
/* rate limit vehicle status updates to 5Hz */
orb_set_interval(_vstatus_sub, 200);
#ifndef SENSOR_COMBINED_SUB
_gyro_sub = orb_subscribe(ORB_ID(sensor_gyro));
_accel_sub = orb_subscribe(ORB_ID(sensor_accel));
_mag_sub = orb_subscribe(ORB_ID(sensor_mag));
/* rate limit gyro updates to 50 Hz */
/* XXX remove this!, BUT increase the data buffer size! */
orb_set_interval(_gyro_sub, 4);
#else
_sensor_combined_sub = orb_subscribe(ORB_ID(sensor_combined));
/* XXX remove this!, BUT increase the data buffer size! */
orb_set_interval(_sensor_combined_sub, 9);
#endif
/* sets also parameters in the EKF object */
parameters_update();
Vector3f lastAngRate;
Vector3f lastAccel;
/* wakeup source(s) */
struct pollfd fds[2];
/* Setup of loop */
fds[0].fd = _params_sub;
fds[0].events = POLLIN;
#ifndef SENSOR_COMBINED_SUB
fds[1].fd = _gyro_sub;
fds[1].events = POLLIN;
#else
fds[1].fd = _sensor_combined_sub;
fds[1].events = POLLIN;
#endif
bool newDataGps = false;
bool newHgtData = false;
bool newAdsData = false;
bool newDataMag = false;
float posNED[3] = {0.0f, 0.0f, 0.0f}; // North, East Down position (m)
uint64_t last_gps = 0;
_gps.vel_n_m_s = 0.0f;
_gps.vel_e_m_s = 0.0f;
_gps.vel_d_m_s = 0.0f;
while (!_task_should_exit) {
/* 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 ERR %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 estimator if gyro updated */
if (fds[1].revents & POLLIN) {
/* check vehicle status for changes to publication state */
bool prev_hil = (_vstatus.hil_state == HIL_STATE_ON);
vehicle_status_poll();
bool accel_updated;
bool mag_updated;
perf_count(_perf_gyro);
/* Reset baro reference if switching to HIL, reset sensor states */
if (!prev_hil && (_vstatus.hil_state == HIL_STATE_ON)) {
/* system is in HIL now, wait for measurements to come in one last round */
usleep(60000);
#ifndef SENSOR_COMBINED_SUB
orb_copy(ORB_ID(sensor_gyro), _gyro_sub, &_gyro);
orb_copy(ORB_ID(sensor_accel), _accel_sub, &_accel);
orb_copy(ORB_ID(sensor_mag), _mag_sub, &_mag);
#else
/* now read all sensor publications to ensure all real sensor data is purged */
orb_copy(ORB_ID(sensor_combined), _sensor_combined_sub, &_sensor_combined);
#endif
/* set sensors to de-initialized state */
_gyro_valid = false;
_accel_valid = false;
_mag_valid = false;
_baro_init = false;
_gps_initialized = false;
_last_sensor_timestamp = hrt_absolute_time();
_last_run = _last_sensor_timestamp;
_ekf->ZeroVariables();
_ekf->dtIMU = 0.01f;
_filter_start_time = _last_sensor_timestamp;
/* now skip this loop and get data on the next one, which will also re-init the filter */
continue;
}
/**
* PART ONE: COLLECT ALL DATA
**/
/* load local copies */
#ifndef SENSOR_COMBINED_SUB
orb_copy(ORB_ID(sensor_gyro), _gyro_sub, &_gyro);
orb_check(_accel_sub, &accel_updated);
if (accel_updated) {
orb_copy(ORB_ID(sensor_accel), _accel_sub, &_accel);
}
_last_sensor_timestamp = _gyro.timestamp;
IMUmsec = _gyro.timestamp / 1e3f;
float deltaT = (_gyro.timestamp - _last_run) / 1e6f;
_last_run = _gyro.timestamp;
/* guard against too large deltaT's */
if (!isfinite(deltaT) || deltaT > 1.0f || deltaT < 0.000001f) {
deltaT = 0.01f;
}
// Always store data, independent of init status
/* fill in last data set */
_ekf->dtIMU = deltaT;
if (isfinite(_gyro.x) &&
isfinite(_gyro.y) &&
isfinite(_gyro.z)) {
_ekf->angRate.x = _gyro.x;
_ekf->angRate.y = _gyro.y;
_ekf->angRate.z = _gyro.z;
if (!_gyro_valid) {
lastAngRate = _ekf->angRate;
}
_gyro_valid = true;
}
if (accel_updated) {
_ekf->accel.x = _accel.x;
_ekf->accel.y = _accel.y;
_ekf->accel.z = _accel.z;
if (!_accel_valid) {
lastAccel = _ekf->accel;
}
_accel_valid = true;
}
_ekf->dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU;
_ekf->lastAngRate = angRate;
_ekf->dVelIMU = 0.5f * (accel + lastAccel) * dtIMU;
_ekf->lastAccel = accel;
#else
orb_copy(ORB_ID(sensor_combined), _sensor_combined_sub, &_sensor_combined);
static hrt_abstime last_accel = 0;
static hrt_abstime last_mag = 0;
if (last_accel != _sensor_combined.accelerometer_timestamp) {
accel_updated = true;
} else {
accel_updated = false;
}
last_accel = _sensor_combined.accelerometer_timestamp;
// Copy gyro and accel
_last_sensor_timestamp = _sensor_combined.timestamp;
IMUmsec = _sensor_combined.timestamp / 1e3f;
float deltaT = (_sensor_combined.timestamp - _last_run) / 1e6f;
/* guard against too large deltaT's */
if (!isfinite(deltaT) || deltaT > 1.0f || deltaT < 0.000001f) {
deltaT = 0.01f;
}
_last_run = _sensor_combined.timestamp;
// Always store data, independent of init status
/* fill in last data set */
_ekf->dtIMU = deltaT;
if (isfinite(_sensor_combined.gyro_rad_s[0]) &&
isfinite(_sensor_combined.gyro_rad_s[1]) &&
isfinite(_sensor_combined.gyro_rad_s[2])) {
_ekf->angRate.x = _sensor_combined.gyro_rad_s[0];
_ekf->angRate.y = _sensor_combined.gyro_rad_s[1];
_ekf->angRate.z = _sensor_combined.gyro_rad_s[2];
if (!_gyro_valid) {
lastAngRate = _ekf->angRate;
}
_gyro_valid = true;
perf_count(_perf_gyro);
}
if (accel_updated) {
_ekf->accel.x = _sensor_combined.accelerometer_m_s2[0];
_ekf->accel.y = _sensor_combined.accelerometer_m_s2[1];
_ekf->accel.z = _sensor_combined.accelerometer_m_s2[2];
if (!_accel_valid) {
lastAccel = _ekf->accel;
}
_accel_valid = true;
}
_ekf->dAngIMU = 0.5f * (_ekf->angRate + lastAngRate) * _ekf->dtIMU;
lastAngRate = _ekf->angRate;
_ekf->dVelIMU = 0.5f * (_ekf->accel + lastAccel) * _ekf->dtIMU;
lastAccel = _ekf->accel;
if (last_mag != _sensor_combined.magnetometer_timestamp) {
mag_updated = true;
newDataMag = true;
} else {
newDataMag = false;
}
last_mag = _sensor_combined.magnetometer_timestamp;
#endif
//warnx("dang: %8.4f %8.4f dvel: %8.4f %8.4f", _ekf->dAngIMU.x, _ekf->dAngIMU.z, _ekf->dVelIMU.x, _ekf->dVelIMU.z);
bool airspeed_updated;
orb_check(_airspeed_sub, &airspeed_updated);
if (airspeed_updated) {
orb_copy(ORB_ID(airspeed), _airspeed_sub, &_airspeed);
perf_count(_perf_airspeed);
_ekf->VtasMeas = _airspeed.true_airspeed_m_s;
newAdsData = true;
} else {
newAdsData = false;
}
bool gps_updated;
orb_check(_gps_sub, &gps_updated);
if (gps_updated) {
last_gps = _gps.timestamp_position;
orb_copy(ORB_ID(vehicle_gps_position), _gps_sub, &_gps);
perf_count(_perf_gps);
if (_gps.fix_type < 3) {
newDataGps = false;
} else {
/* store time of valid GPS measurement */
_gps_start_time = hrt_absolute_time();
/* check if we had a GPS outage for a long time */
if (hrt_elapsed_time(&last_gps) > 5 * 1000 * 1000) {
_ekf->ResetPosition();
_ekf->ResetVelocity();
_ekf->ResetStoredStates();
}
/* fuse GPS updates */
//_gps.timestamp / 1e3;
_ekf->GPSstatus = _gps.fix_type;
_ekf->velNED[0] = _gps.vel_n_m_s;
_ekf->velNED[1] = _gps.vel_e_m_s;
_ekf->velNED[2] = _gps.vel_d_m_s;
// warnx("GPS updated: status: %d, vel: %8.4f %8.4f %8.4f", (int)GPSstatus, velNED[0], velNED[1], velNED[2]);
_ekf->gpsLat = math::radians(_gps.lat / (double)1e7);
_ekf->gpsLon = math::radians(_gps.lon / (double)1e7) - M_PI;
_ekf->gpsHgt = _gps.alt / 1e3f;
// if (_gps.s_variance_m_s > 0.25f && _gps.s_variance_m_s < 100.0f * 100.0f) {
// _ekf->vneSigma = sqrtf(_gps.s_variance_m_s);
// } else {
// _ekf->vneSigma = _parameters.velne_noise;
// }
// if (_gps.p_variance_m > 0.25f && _gps.p_variance_m < 100.0f * 100.0f) {
// _ekf->posNeSigma = sqrtf(_gps.p_variance_m);
// } else {
// _ekf->posNeSigma = _parameters.posne_noise;
// }
// warnx("vel: %8.4f pos: %8.4f", _gps.s_variance_m_s, _gps.p_variance_m);
newDataGps = true;
}
}
bool baro_updated;
orb_check(_baro_sub, &baro_updated);
if (baro_updated) {
orb_copy(ORB_ID(sensor_baro), _baro_sub, &_baro);
_ekf->baroHgt = _baro.altitude;
if (!_baro_init) {
_baro_ref = _baro.altitude;
_baro_init = true;
warnx("ALT REF INIT");
}
perf_count(_perf_baro);
newHgtData = true;
} else {
newHgtData = false;
}
#ifndef SENSOR_COMBINED_SUB
orb_check(_mag_sub, &mag_updated);
#endif
if (mag_updated) {
_mag_valid = true;
perf_count(_perf_mag);
#ifndef SENSOR_COMBINED_SUB
orb_copy(ORB_ID(sensor_mag), _mag_sub, &_mag);
// XXX we compensate the offsets upfront - should be close to zero.
// 0.001f
_ekf->magData.x = _mag.x;
_ekf->magBias.x = 0.000001f; // _mag_offsets.x_offset
_ekf->magData.y = _mag.y;
_ekf->magBias.y = 0.000001f; // _mag_offsets.y_offset
_ekf->magData.z = _mag.z;
_ekf->magBias.z = 0.000001f; // _mag_offsets.y_offset
#else
// XXX we compensate the offsets upfront - should be close to zero.
// 0.001f
_ekf->magData.x = _sensor_combined.magnetometer_ga[0];
_ekf->magBias.x = 0.000001f; // _mag_offsets.x_offset
_ekf->magData.y = _sensor_combined.magnetometer_ga[1];
_ekf->magBias.y = 0.000001f; // _mag_offsets.y_offset
_ekf->magData.z = _sensor_combined.magnetometer_ga[2];
_ekf->magBias.z = 0.000001f; // _mag_offsets.y_offset
#endif
newDataMag = true;
} else {
newDataMag = false;
}
/*
* CHECK IF ITS THE RIGHT TIME TO RUN THINGS ALREADY
*/
if (hrt_elapsed_time(&_filter_start_time) < FILTER_INIT_DELAY) {
continue;
}
/**
* PART TWO: EXECUTE THE FILTER
*
* We run the filter only once all data has been fetched
**/
if (_baro_init && _gyro_valid && _accel_valid && _mag_valid) {
float initVelNED[3];
/* Initialize the filter first */
if (!_gps_initialized && _gps.fix_type > 2 && _gps.eph < _parameters.pos_stddev_threshold && _gps.epv < _parameters.pos_stddev_threshold) {
// GPS is in scaled integers, convert
double lat = _gps.lat / 1.0e7;
double lon = _gps.lon / 1.0e7;
float gps_alt = _gps.alt / 1e3f;
initVelNED[0] = _gps.vel_n_m_s;
initVelNED[1] = _gps.vel_e_m_s;
initVelNED[2] = _gps.vel_d_m_s;
// Set up height correctly
orb_copy(ORB_ID(sensor_baro), _baro_sub, &_baro);
_baro_ref_offset = _ekf->states[9]; // this should become zero in the local frame
_baro_gps_offset = _baro.altitude - gps_alt;
_ekf->baroHgt = _baro.altitude;
_ekf->hgtMea = 1.0f * (_ekf->baroHgt - (_baro_ref));
// Set up position variables correctly
_ekf->GPSstatus = _gps.fix_type;
_ekf->gpsLat = math::radians(lat);
_ekf->gpsLon = math::radians(lon) - M_PI;
_ekf->gpsHgt = gps_alt;
// Look up mag declination based on current position
float declination = math::radians(get_mag_declination(lat, lon));
_ekf->InitialiseFilter(initVelNED, math::radians(lat), math::radians(lon) - M_PI, gps_alt, declination);
// Initialize projection
_local_pos.ref_lat = lat;
_local_pos.ref_lon = lon;
_local_pos.ref_alt = gps_alt;
_local_pos.ref_timestamp = _gps.timestamp_position;
map_projection_init(&_pos_ref, lat, lon);
mavlink_log_info(_mavlink_fd, "[ekf] ref: LA %.4f,LO %.4f,ALT %.2f", lat, lon, (double)gps_alt);
#if 0
warnx("HOME/REF: LA %8.4f,LO %8.4f,ALT %8.2f V: %8.4f %8.4f %8.4f", lat, lon, (double)gps_alt,
(double)_ekf->velNED[0], (double)_ekf->velNED[1], (double)_ekf->velNED[2]);
warnx("BARO: %8.4f m / ref: %8.4f m / gps offs: %8.4f m", (double)_ekf->baroHgt, (double)_baro_ref, (double)_baro_ref_offset);
warnx("GPS: eph: %8.4f, epv: %8.4f, declination: %8.4f", (double)_gps.eph, (double)_gps.epv, (double)math::degrees(declination));
#endif
_gps_initialized = true;
} else if (!_ekf->statesInitialised) {
initVelNED[0] = 0.0f;
initVelNED[1] = 0.0f;
initVelNED[2] = 0.0f;
_ekf->posNE[0] = posNED[0];
_ekf->posNE[1] = posNED[1];
_local_pos.ref_alt = _baro_ref;
_baro_ref_offset = 0.0f;
_baro_gps_offset = 0.0f;
_ekf->InitialiseFilter(initVelNED, 0.0, 0.0, 0.0f, 0.0f);
} else if (_ekf->statesInitialised) {
// We're apparently initialized in this case now
int check = check_filter_state();
if (check) {
// Let the system re-initialize itself
continue;
}
// Run the strapdown INS equations every IMU update
_ekf->UpdateStrapdownEquationsNED();
#if 0
// debug code - could be tunred into a filter mnitoring/watchdog function
float tempQuat[4];
for (uint8_t j = 0; j <= 3; j++) tempQuat[j] = states[j];
quat2eul(eulerEst, tempQuat);
for (uint8_t j = 0; j <= 2; j++) eulerDif[j] = eulerEst[j] - ahrsEul[j];
if (eulerDif[2] > pi) eulerDif[2] -= 2 * pi;
if (eulerDif[2] < -pi) eulerDif[2] += 2 * pi;
#endif
// store the predicted states for subsequent use by measurement fusion
_ekf->StoreStates(IMUmsec);
// Check if on ground - status is used by covariance prediction
_ekf->OnGroundCheck();
// sum delta angles and time used by covariance prediction
_ekf->summedDelAng = _ekf->summedDelAng + _ekf->correctedDelAng;
_ekf->summedDelVel = _ekf->summedDelVel + _ekf->dVelIMU;
dt += _ekf->dtIMU;
// perform a covariance prediction if the total delta angle has exceeded the limit
// or the time limit will be exceeded at the next IMU update
if ((dt >= (_ekf->covTimeStepMax - _ekf->dtIMU)) || (_ekf->summedDelAng.length() > _ekf->covDelAngMax)) {
_ekf->CovariancePrediction(dt);
_ekf->summedDelAng.zero();
_ekf->summedDelVel.zero();
dt = 0.0f;
}
// Fuse GPS Measurements
if (newDataGps && _gps_initialized) {
// Convert GPS measurements to Pos NE, hgt and Vel NED
float gps_dt = (_gps.timestamp_position - last_gps) / 1e6f;
// Calculate acceleration predicted by GPS velocity change
if (((fabsf(_ekf->velNED[0] - _gps.vel_n_m_s) > FLT_EPSILON) ||
(fabsf(_ekf->velNED[1] - _gps.vel_e_m_s) > FLT_EPSILON) ||
(fabsf(_ekf->velNED[2] - _gps.vel_d_m_s) > FLT_EPSILON)) && (gps_dt > 0.00001f)) {
_ekf->accelGPSNED[0] = (_ekf->velNED[0] - _gps.vel_n_m_s) / gps_dt;
_ekf->accelGPSNED[1] = (_ekf->velNED[1] - _gps.vel_e_m_s) / gps_dt;
_ekf->accelGPSNED[2] = (_ekf->velNED[2] - _gps.vel_d_m_s) / gps_dt;
}
_ekf->velNED[0] = _gps.vel_n_m_s;
_ekf->velNED[1] = _gps.vel_e_m_s;
_ekf->velNED[2] = _gps.vel_d_m_s;
_ekf->calcposNED(posNED, _ekf->gpsLat, _ekf->gpsLon, _ekf->gpsHgt, _ekf->latRef, _ekf->lonRef, _ekf->hgtRef);
_ekf->posNE[0] = posNED[0];
_ekf->posNE[1] = posNED[1];
// set fusion flags
_ekf->fuseVelData = true;
_ekf->fusePosData = true;
// recall states stored at time of measurement after adjusting for delays
_ekf->RecallStates(_ekf->statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms));
_ekf->RecallStates(_ekf->statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms));
// run the fusion step
_ekf->FuseVelposNED();
} else if (_ekf->statesInitialised) {
// Convert GPS measurements to Pos NE, hgt and Vel NED
_ekf->velNED[0] = 0.0f;
_ekf->velNED[1] = 0.0f;
_ekf->velNED[2] = 0.0f;
_ekf->posNE[0] = 0.0f;
_ekf->posNE[1] = 0.0f;
// set fusion flags
_ekf->fuseVelData = true;
_ekf->fusePosData = true;
// recall states stored at time of measurement after adjusting for delays
_ekf->RecallStates(_ekf->statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms));
_ekf->RecallStates(_ekf->statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms));
// run the fusion step
_ekf->FuseVelposNED();
} else {
_ekf->fuseVelData = false;
_ekf->fusePosData = false;
}
if (newHgtData && _ekf->statesInitialised) {
// Could use a blend of GPS and baro alt data if desired
_ekf->hgtMea = 1.0f * (_ekf->baroHgt - _baro_ref);
_ekf->fuseHgtData = true;
// recall states stored at time of measurement after adjusting for delays
_ekf->RecallStates(_ekf->statesAtHgtTime, (IMUmsec - _parameters.height_delay_ms));
// run the fusion step
_ekf->FuseVelposNED();
} else {
_ekf->fuseHgtData = false;
}
// Fuse Magnetometer Measurements
if (newDataMag && _ekf->statesInitialised) {
_ekf->fuseMagData = true;
_ekf->RecallStates(_ekf->statesAtMagMeasTime, (IMUmsec - _parameters.mag_delay_ms)); // Assume 50 msec avg delay for magnetometer data
_ekf->magstate.obsIndex = 0;
_ekf->FuseMagnetometer();
_ekf->FuseMagnetometer();
_ekf->FuseMagnetometer();
} else {
_ekf->fuseMagData = false;
}
// Fuse Airspeed Measurements
if (newAdsData && _ekf->statesInitialised && _ekf->VtasMeas > 8.0f) {
_ekf->fuseVtasData = true;
_ekf->RecallStates(_ekf->statesAtVtasMeasTime, (IMUmsec - _parameters.tas_delay_ms)); // assume 100 msec avg delay for airspeed data
_ekf->FuseAirspeed();
} else {
_ekf->fuseVtasData = false;
}
// Output results
math::Quaternion q(_ekf->states[0], _ekf->states[1], _ekf->states[2], _ekf->states[3]);
math::Matrix<3, 3> R = q.to_dcm();
math::Vector<3> euler = R.to_euler();
for (int i = 0; i < 3; i++) for (int j = 0; j < 3; j++)
_att.R[i][j] = R(i, j);
_att.timestamp = _last_sensor_timestamp;
_att.q[0] = _ekf->states[0];
_att.q[1] = _ekf->states[1];
_att.q[2] = _ekf->states[2];
_att.q[3] = _ekf->states[3];
_att.q_valid = true;
_att.R_valid = true;
_att.timestamp = _last_sensor_timestamp;
_att.roll = euler(0);
_att.pitch = euler(1);
_att.yaw = euler(2);
_att.rollspeed = _ekf->angRate.x - _ekf->states[10];
_att.pitchspeed = _ekf->angRate.y - _ekf->states[11];
_att.yawspeed = _ekf->angRate.z - _ekf->states[12];
// gyro offsets
_att.rate_offsets[0] = _ekf->states[10];
_att.rate_offsets[1] = _ekf->states[11];
_att.rate_offsets[2] = _ekf->states[12];
/* lazily publish the attitude only once available */
if (_att_pub > 0) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_attitude), _att_pub, &_att);
} else {
/* advertise and publish */
_att_pub = orb_advertise(ORB_ID(vehicle_attitude), &_att);
}
if (_gps_initialized) {
_local_pos.timestamp = _last_sensor_timestamp;
_local_pos.x = _ekf->states[7];
_local_pos.y = _ekf->states[8];
// XXX need to announce change of Z reference somehow elegantly
_local_pos.z = _ekf->states[9] - _baro_ref_offset;
_local_pos.vx = _ekf->states[4];
_local_pos.vy = _ekf->states[5];
_local_pos.vz = _ekf->states[6];
_local_pos.xy_valid = _gps_initialized;
_local_pos.z_valid = true;
_local_pos.v_xy_valid = _gps_initialized;
_local_pos.v_z_valid = true;
_local_pos.xy_global = true;
_velocity_xy_filtered = 0.95f*_velocity_xy_filtered + 0.05f*sqrtf(_local_pos.vx*_local_pos.vx + _local_pos.vy*_local_pos.vy);
_velocity_z_filtered = 0.95f*_velocity_z_filtered + 0.05f*fabsf(_local_pos.vz);
_airspeed_filtered = 0.95f*_airspeed_filtered + + 0.05f*_airspeed.true_airspeed_m_s;
/* crude land detector for fixedwing only,
* TODO: adapt so that it works for both, maybe move to another location
*/
if (_velocity_xy_filtered < 5
&& _velocity_z_filtered < 10
&& _airspeed_filtered < 10) {
_local_pos.landed = true;
} else {
_local_pos.landed = false;
}
_local_pos.z_global = false;
_local_pos.yaw = _att.yaw;
/* lazily publish the local position only once available */
if (_local_pos_pub > 0) {
/* publish the attitude setpoint */
orb_publish(ORB_ID(vehicle_local_position), _local_pos_pub, &_local_pos);
} else {
/* advertise and publish */
_local_pos_pub = orb_advertise(ORB_ID(vehicle_local_position), &_local_pos);
}
_global_pos.timestamp = _local_pos.timestamp;
if (_local_pos.xy_global) {
double est_lat, est_lon;
map_projection_reproject(&_pos_ref, _local_pos.x, _local_pos.y, &est_lat, &est_lon);
_global_pos.lat = est_lat;
_global_pos.lon = est_lon;
_global_pos.time_gps_usec = _gps.time_gps_usec;
_global_pos.eph = _gps.eph;
_global_pos.epv = _gps.epv;
}
if (_local_pos.v_xy_valid) {
_global_pos.vel_n = _local_pos.vx;
_global_pos.vel_e = _local_pos.vy;
} else {
_global_pos.vel_n = 0.0f;
_global_pos.vel_e = 0.0f;
}
/* local pos alt is negative, change sign and add alt offsets */
_global_pos.alt = _baro_ref + (-_local_pos.z) - _baro_gps_offset;
if (_local_pos.v_z_valid) {
_global_pos.vel_d = _local_pos.vz;
}
_global_pos.yaw = _local_pos.yaw;
_global_pos.eph = _gps.eph;
_global_pos.epv = _gps.epv;
_global_pos.timestamp = _local_pos.timestamp;
/* lazily publish the global position only once available */
if (_global_pos_pub > 0) {
/* publish the global position */
orb_publish(ORB_ID(vehicle_global_position), _global_pos_pub, &_global_pos);
} else {
/* advertise and publish */
_global_pos_pub = orb_advertise(ORB_ID(vehicle_global_position), &_global_pos);
}
if (hrt_elapsed_time(&_wind.timestamp) > 99000) {
_wind.timestamp = _global_pos.timestamp;
_wind.windspeed_north = _ekf->states[14];
_wind.windspeed_east = _ekf->states[15];
_wind.covariance_north = 0.0f; // XXX get form filter
_wind.covariance_east = 0.0f;
/* lazily publish the wind estimate only once available */
if (_wind_pub > 0) {
/* publish the wind estimate */
orb_publish(ORB_ID(wind_estimate), _wind_pub, &_wind);
} else {
/* advertise and publish */
_wind_pub = orb_advertise(ORB_ID(wind_estimate), &_wind);
}
}
}
}
if (hrt_elapsed_time(&_wind.timestamp) > 99000) {
_wind.timestamp = _global_pos.timestamp;
_wind.windspeed_north = _ekf->states[14];
_wind.windspeed_east = _ekf->states[15];
_wind.covariance_north = _ekf->P[14][14];
_wind.covariance_east = _ekf->P[15][15];
/* lazily publish the wind estimate only once available */
if (_wind_pub > 0) {
/* publish the wind estimate */
orb_publish(ORB_ID(wind_estimate), _wind_pub, &_wind);
} else {
/* advertise and publish */
_wind_pub = orb_advertise(ORB_ID(wind_estimate), &_wind);
}
}
}
}
perf_end(_loop_perf);
}
warnx("exiting.\n");
_estimator_task = -1;
_exit(0);
}
void
MPU9250::measure()
{
if (hrt_absolute_time() < _reset_wait) {
// we're waiting for a reset to complete
return;
}
struct MPUReport mpu_report;
struct Report {
int16_t accel_x;
int16_t accel_y;
int16_t accel_z;
int16_t temp;
int16_t gyro_x;
int16_t gyro_y;
int16_t gyro_z;
} report;
/* start measuring */
perf_begin(_sample_perf);
/*
* Fetch the full set of measurements from the MPU9250 in one pass
*/
if ((!_magnetometer_only || _mag->is_passthrough()) && _register_wait == 0) {
if (_whoami == MPU_WHOAMI_9250 || _whoami == MPU_WHOAMI_6500) {
if (OK != read_reg_range(MPUREG_INT_STATUS, MPU9250_HIGH_BUS_SPEED, (uint8_t *)&mpu_report, sizeof(mpu_report))) {
perf_end(_sample_perf);
return;
}
}
check_registers();
if (check_duplicate(&mpu_report.accel_x[0])) {
return;
}
}
/*
* In case of a mag passthrough read, hand the magnetometer data over to _mag. Else,
* try to read a magnetometer report.
*/
# ifdef USE_I2C
if (_mag->is_passthrough()) {
# endif
if (_register_wait == 0) {
_mag->_measure(mpu_report.mag);
}
# ifdef USE_I2C
} else {
_mag->measure();
}
# endif
/*
* Continue evaluating gyro and accelerometer results
*/
if (!_magnetometer_only && _register_wait == 0) {
/*
* Convert from big to little endian
*/
report.accel_x = int16_t_from_bytes(mpu_report.accel_x);
report.accel_y = int16_t_from_bytes(mpu_report.accel_y);
report.accel_z = int16_t_from_bytes(mpu_report.accel_z);
report.temp = int16_t_from_bytes(mpu_report.temp);
report.gyro_x = int16_t_from_bytes(mpu_report.gyro_x);
report.gyro_y = int16_t_from_bytes(mpu_report.gyro_y);
report.gyro_z = int16_t_from_bytes(mpu_report.gyro_z);
if (check_null_data((uint16_t *)&report, sizeof(report) / 2)) {
return;
}
}
if (_register_wait != 0) {
/*
* We are waiting for some good transfers before using the sensor again.
* We still increment _good_transfers, but don't return any data yet.
*
*/
_register_wait--;
return;
}
/*
* Get sensor temperature
*/
_last_temperature = (report.temp) / 333.87f + 21.0f;
/*
* Convert and publish accelerometer and gyrometer data.
*/
if (!_magnetometer_only) {
/*
* Swap axes and negate y
*/
int16_t accel_xt = report.accel_y;
int16_t accel_yt = ((report.accel_x == -32768) ? 32767 : -report.accel_x);
int16_t gyro_xt = report.gyro_y;
int16_t gyro_yt = ((report.gyro_x == -32768) ? 32767 : -report.gyro_x);
/*
* Apply the swap
*/
report.accel_x = accel_xt;
report.accel_y = accel_yt;
report.gyro_x = gyro_xt;
report.gyro_y = gyro_yt;
/*
* Report buffers.
*/
sensor_accel_s arb;
sensor_gyro_s grb;
/*
* Adjust and scale results to m/s^2.
*/
grb.timestamp = arb.timestamp = hrt_absolute_time();
// report the error count as the sum of the number of bad
// transfers and bad register reads. This allows the higher
// level code to decide if it should use this sensor based on
// whether it has had failures
grb.error_count = arb.error_count = perf_event_count(_bad_transfers) + perf_event_count(_bad_registers);
/*
* 1) Scale raw value to SI units using scaling from datasheet.
* 2) Subtract static offset (in SI units)
* 3) Scale the statically calibrated values with a linear
* dynamically obtained factor
*
* Note: the static sensor offset is the number the sensor outputs
* at a nominally 'zero' input. Therefore the offset has to
* be subtracted.
*
* Example: A gyro outputs a value of 74 at zero angular rate
* the offset is 74 from the origin and subtracting
* 74 from all measurements centers them around zero.
*/
/* NOTE: Axes have been swapped to match the board a few lines above. */
arb.x_raw = report.accel_x;
arb.y_raw = report.accel_y;
arb.z_raw = report.accel_z;
float xraw_f = report.accel_x;
float yraw_f = report.accel_y;
float zraw_f = report.accel_z;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
float x_in_new = ((xraw_f * _accel_range_scale) - _accel_scale.x_offset) * _accel_scale.x_scale;
float y_in_new = ((yraw_f * _accel_range_scale) - _accel_scale.y_offset) * _accel_scale.y_scale;
float z_in_new = ((zraw_f * _accel_range_scale) - _accel_scale.z_offset) * _accel_scale.z_scale;
arb.x = _accel_filter_x.apply(x_in_new);
arb.y = _accel_filter_y.apply(y_in_new);
arb.z = _accel_filter_z.apply(z_in_new);
matrix::Vector3f aval(x_in_new, y_in_new, z_in_new);
matrix::Vector3f aval_integrated;
bool accel_notify = _accel_int.put(arb.timestamp, aval, aval_integrated, arb.integral_dt);
arb.x_integral = aval_integrated(0);
arb.y_integral = aval_integrated(1);
arb.z_integral = aval_integrated(2);
arb.scaling = _accel_range_scale;
arb.temperature = _last_temperature;
/* return device ID */
arb.device_id = _accel->_device_id.devid;
grb.x_raw = report.gyro_x;
grb.y_raw = report.gyro_y;
grb.z_raw = report.gyro_z;
xraw_f = report.gyro_x;
yraw_f = report.gyro_y;
zraw_f = report.gyro_z;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
float x_gyro_in_new = ((xraw_f * _gyro_range_scale) - _gyro_scale.x_offset) * _gyro_scale.x_scale;
float y_gyro_in_new = ((yraw_f * _gyro_range_scale) - _gyro_scale.y_offset) * _gyro_scale.y_scale;
float z_gyro_in_new = ((zraw_f * _gyro_range_scale) - _gyro_scale.z_offset) * _gyro_scale.z_scale;
grb.x = _gyro_filter_x.apply(x_gyro_in_new);
grb.y = _gyro_filter_y.apply(y_gyro_in_new);
grb.z = _gyro_filter_z.apply(z_gyro_in_new);
matrix::Vector3f gval(x_gyro_in_new, y_gyro_in_new, z_gyro_in_new);
matrix::Vector3f gval_integrated;
bool gyro_notify = _gyro_int.put(arb.timestamp, gval, gval_integrated, grb.integral_dt);
grb.x_integral = gval_integrated(0);
grb.y_integral = gval_integrated(1);
grb.z_integral = gval_integrated(2);
grb.scaling = _gyro_range_scale;
grb.temperature = _last_temperature;
/* return device ID */
grb.device_id = _gyro->_device_id.devid;
_accel_reports->force(&arb);
_gyro_reports->force(&grb);
/* notify anyone waiting for data */
if (accel_notify) {
_accel->poll_notify(POLLIN);
}
if (gyro_notify) {
_gyro->parent_poll_notify();
}
if (accel_notify && !(_accel->_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(sensor_accel), _accel_topic, &arb);
}
if (gyro_notify && !(_gyro->_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(sensor_gyro), _gyro->_gyro_topic, &grb);
}
}
/* stop measuring */
perf_end(_sample_perf);
}
/* Main Thread */
int fixedwing_control_thread_main(int argc, char *argv[])
{
/* read arguments */
bool verbose = false;
for (int i = 1; i < argc; i++) {
if (strcmp(argv[i], "-v") == 0 || strcmp(argv[i], "--verbose") == 0) {
verbose = true;
}
}
/* welcome user (warnx prints a line, including an appended\n, with variable arguments */
warnx("[example fixedwing control] started");
/* initialize parameters, first the handles, then the values */
parameters_init(&ph);
parameters_update(&ph, &p);
/*
* PX4 uses a publish/subscribe design pattern to enable
* multi-threaded communication.
*
* The most elegant aspect of this is that controllers and
* other processes can either 'react' to new data, or run
* at their own pace.
*
* PX4 developer guide:
* https://pixhawk.ethz.ch/px4/dev/shared_object_communication
*
* Wikipedia description:
* http://en.wikipedia.org/wiki/Publish–subscribe_pattern
*
*/
/*
* Declare and safely initialize all structs to zero.
*
* These structs contain the system state and things
* like attitude, position, the current waypoint, etc.
*/
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_attitude_setpoint_s att_sp;
memset(&att_sp, 0, sizeof(att_sp));
struct vehicle_rates_setpoint_s rates_sp;
memset(&rates_sp, 0, sizeof(rates_sp));
struct vehicle_global_position_s global_pos;
memset(&global_pos, 0, sizeof(global_pos));
struct manual_control_setpoint_s manual_sp;
memset(&manual_sp, 0, sizeof(manual_sp));
struct vehicle_status_s vstatus;
memset(&vstatus, 0, sizeof(vstatus));
struct position_setpoint_s global_sp;
memset(&global_sp, 0, sizeof(global_sp));
/* output structs - this is what is sent to the mixer */
struct actuator_controls_s actuators;
memset(&actuators, 0, sizeof(actuators));
/* publish actuator controls with zero values */
for (unsigned i = 0; i < actuator_controls_s::NUM_ACTUATOR_CONTROLS; i++) {
actuators.control[i] = 0.0f;
}
/*
* Advertise that this controller will publish actuator
* control values and the rate setpoint
*/
orb_advert_t actuator_pub = orb_advertise(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, &actuators);
orb_advert_t rates_pub = orb_advertise(ORB_ID(vehicle_rates_setpoint), &rates_sp);
/* subscribe to topics. */
int att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
int global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
int manual_sp_sub = orb_subscribe(ORB_ID(manual_control_setpoint));
int vstatus_sub = orb_subscribe(ORB_ID(vehicle_status));
int global_sp_sub = orb_subscribe(ORB_ID(position_setpoint_triplet));
int param_sub = orb_subscribe(ORB_ID(parameter_update));
/* Setup of loop */
struct pollfd fds[2] = {};
fds[0].fd = param_sub;
fds[0].events = POLLIN;
fds[1].fd = att_sub;
fds[1].events = POLLIN;
while (!thread_should_exit) {
/*
* Wait for a sensor or param update, check for exit condition every 500 ms.
* This means that the execution will block here without consuming any resources,
* but will continue to execute the very moment a new attitude measurement or
* a param update is published. So no latency in contrast to the polling
* design pattern (do not confuse the poll() system call with polling).
*
* This design pattern makes the controller also agnostic of the attitude
* update speed - it runs as fast as the attitude updates with minimal latency.
*/
int ret = poll(fds, 2, 500);
if (ret < 0) {
/*
* Poll error, this will not really happen in practice,
* but its good design practice to make output an error message.
*/
warnx("poll error");
} else if (ret == 0) {
/* no return value = nothing changed for 500 ms, ignore */
} else {
/* only update parameters if they changed */
if (fds[0].revents & POLLIN) {
/* read from param to clear updated flag (uORB API requirement) */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), param_sub, &update);
/* if a param update occured, re-read our parameters */
parameters_update(&ph, &p);
}
/* only run controller if attitude changed */
if (fds[1].revents & POLLIN) {
/* Check if there is a new position measurement or position setpoint */
bool pos_updated;
orb_check(global_pos_sub, &pos_updated);
bool global_sp_updated;
orb_check(global_sp_sub, &global_sp_updated);
bool manual_sp_updated;
orb_check(manual_sp_sub, &manual_sp_updated);
/* get a local copy of attitude */
orb_copy(ORB_ID(vehicle_attitude), att_sub, &att);
if (global_sp_updated) {
struct position_setpoint_triplet_s triplet;
orb_copy(ORB_ID(position_setpoint_triplet), global_sp_sub, &triplet);
memcpy(&global_sp, &triplet.current, sizeof(global_sp));
}
if (manual_sp_updated)
/* get the RC (or otherwise user based) input */
{
orb_copy(ORB_ID(manual_control_setpoint), manual_sp_sub, &manual_sp);
}
/* check if the throttle was ever more than 50% - go later only to failsafe if yes */
if (PX4_ISFINITE(manual_sp.z) &&
(manual_sp.z >= 0.6f) &&
(manual_sp.z <= 1.0f)) {
}
/* get the system status and the flight mode we're in */
orb_copy(ORB_ID(vehicle_status), vstatus_sub, &vstatus);
/* publish rates */
orb_publish(ORB_ID(vehicle_rates_setpoint), rates_pub, &rates_sp);
/* sanity check and publish actuator outputs */
if (PX4_ISFINITE(actuators.control[0]) &&
PX4_ISFINITE(actuators.control[1]) &&
PX4_ISFINITE(actuators.control[2]) &&
PX4_ISFINITE(actuators.control[3])) {
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
if (verbose) {
warnx("published");
}
}
}
}
}
printf("[ex_fixedwing_control] exiting, stopping all motors.\n");
thread_running = false;
/* kill all outputs */
for (unsigned i = 0; i < actuator_controls_s::NUM_ACTUATOR_CONTROLS; i++) {
actuators.control[i] = 0.0f;
}
orb_publish(ORB_ID_VEHICLE_ATTITUDE_CONTROLS, actuator_pub, &actuators);
fflush(stdout);
return 0;
}
void
FixedwingAttitudeControl::task_main()
{
/*
* do subscriptions
*/
_att_sp_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
_ctrl_state_sub = orb_subscribe(ORB_ID(control_state));
_accel_sub = orb_subscribe_multi(ORB_ID(sensor_accel), 0);
_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));
_vehicle_status_sub = orb_subscribe(ORB_ID(vehicle_status));
_vehicle_land_detected_sub = orb_subscribe(ORB_ID(vehicle_land_detected));
parameters_update();
/* get an initial update for all sensor and status data */
vehicle_setpoint_poll();
vehicle_accel_poll();
vehicle_control_mode_poll();
vehicle_manual_poll();
vehicle_status_poll();
vehicle_land_detected_poll();
/* wakeup source */
px4_pollfd_struct_t fds[2];
/* Setup of loop */
fds[0].fd = _params_sub;
fds[0].events = POLLIN;
fds[1].fd = _ctrl_state_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) {
deltaT = 0.01f;
}
/* load local copies */
orb_copy(ORB_ID(control_state), _ctrl_state_sub, &_ctrl_state);
/* get current rotation matrix and euler angles from control state quaternions */
math::Quaternion q_att(_ctrl_state.q[0], _ctrl_state.q[1], _ctrl_state.q[2], _ctrl_state.q[3]);
_R = q_att.to_dcm();
math::Vector<3> euler_angles;
euler_angles = _R.to_euler();
_roll = euler_angles(0);
_pitch = euler_angles(1);
_yaw = euler_angles(2);
if (_vehicle_status.is_vtol && _parameters.vtol_type == 0) {
/* vehicle is a tailsitter, we need to modify the estimated attitude for fw mode
*
* Since the VTOL airframe is initialized as a multicopter we need to
* modify the estimated attitude for the fixed wing operation.
* Since the neutral position of the vehicle in fixed wing mode is -90 degrees rotated around
* the pitch axis compared to the neutral position of the vehicle in multicopter mode
* we need to swap the roll and the yaw axis (1st and 3rd column) in the rotation matrix.
* Additionally, in order to get the correct sign of the pitch, we need to multiply
* the new x axis of the rotation matrix with -1
*
* original: modified:
*
* Rxx Ryx Rzx -Rzx Ryx Rxx
* Rxy Ryy Rzy -Rzy Ryy Rxy
* Rxz Ryz Rzz -Rzz Ryz Rxz
* */
math::Matrix<3, 3> R_adapted = _R; //modified rotation matrix
/* move z to x */
R_adapted(0, 0) = _R(0, 2);
R_adapted(1, 0) = _R(1, 2);
R_adapted(2, 0) = _R(2, 2);
/* move x to z */
R_adapted(0, 2) = _R(0, 0);
R_adapted(1, 2) = _R(1, 0);
R_adapted(2, 2) = _R(2, 0);
/* change direction of pitch (convert to right handed system) */
R_adapted(0, 0) = -R_adapted(0, 0);
R_adapted(1, 0) = -R_adapted(1, 0);
R_adapted(2, 0) = -R_adapted(2, 0);
euler_angles = R_adapted.to_euler(); //adapted euler angles for fixed wing operation
/* fill in new attitude data */
_R = R_adapted;
_roll = euler_angles(0);
_pitch = euler_angles(1);
_yaw = euler_angles(2);
/* lastly, roll- and yawspeed have to be swaped */
float helper = _ctrl_state.roll_rate;
_ctrl_state.roll_rate = -_ctrl_state.yaw_rate;
_ctrl_state.yaw_rate = helper;
}
vehicle_setpoint_poll();
vehicle_accel_poll();
vehicle_control_mode_poll();
vehicle_manual_poll();
global_pos_poll();
vehicle_status_poll();
vehicle_land_detected_poll();
// the position controller will not emit attitude setpoints in some modes
// we need to make sure that this flag is reset
_att_sp.fw_control_yaw = _att_sp.fw_control_yaw && _vcontrol_mode.flag_control_auto_enabled;
/* lock integrator until control is started */
bool lock_integrator;
if (_vcontrol_mode.flag_control_attitude_enabled && !_vehicle_status.is_rotary_wing) {
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[7] = 1.0f;
//warnx("_actuators_airframe.control[1] = 1.0f;");
} else {
_actuators_airframe.control[7] = 0.0f;
//warnx("_actuators_airframe.control[1] = -1.0f;");
}
/* if we are in rotary wing mode, do nothing */
if (_vehicle_status.is_rotary_wing && !_vehicle_status.is_vtol) {
continue;
}
/* default flaps to center */
float flaps_control = 0.0f;
static float delta_flaps = 0;
/* map flaps by default to manual if valid */
if (PX4_ISFINITE(_manual.flaps) && _vcontrol_mode.flag_control_manual_enabled) {
flaps_control = 0.5f * (_manual.flaps + 1.0f) * _parameters.flaps_scale;
} else if (_vcontrol_mode.flag_control_auto_enabled) {
flaps_control = _att_sp.apply_flaps ? 1.0f * _parameters.flaps_scale : 0.0f;
}
// move the actual control value continuous with time
static hrt_abstime t_flaps_changed = 0;
if (fabsf(flaps_control - _flaps_cmd_last) > 0.01f) {
t_flaps_changed = hrt_absolute_time();
delta_flaps = flaps_control - _flaps_cmd_last;
_flaps_cmd_last = flaps_control;
}
static float flaps_applied = 0.0f;
if (fabsf(flaps_applied - flaps_control) > 0.01f) {
flaps_applied = (flaps_control - delta_flaps) + (float)hrt_elapsed_time(&t_flaps_changed) * (delta_flaps) / 1000000;
}
/* default flaperon to center */
float flaperon = 0.0f;
static float delta_flaperon = 0.0f;
/* map flaperons by default to manual if valid */
if (PX4_ISFINITE(_manual.aux2) && _vcontrol_mode.flag_control_manual_enabled) {
flaperon = 0.5f * (_manual.aux2 + 1.0f) * _parameters.flaperon_scale;
} else if (_vcontrol_mode.flag_control_auto_enabled) {
flaperon = _att_sp.apply_flaps ? 1.0f * _parameters.flaperon_scale : 0.0f;
}
// move the actual control value continuous with time
static hrt_abstime t_flaperons_changed = 0;
if (fabsf(flaperon - _flaperons_cmd_last) > 0.01f) {
t_flaperons_changed = hrt_absolute_time();
delta_flaperon = flaperon - _flaperons_cmd_last;
_flaperons_cmd_last = flaperon;
}
static float flaperon_applied = 0.0f;
if (fabsf(flaperon_applied - flaperon) > 0.01f) {
flaperon_applied = (flaperon - delta_flaperon) + (float)hrt_elapsed_time(&t_flaperons_changed) *
(delta_flaperon) / 1000000;
}
/* 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 = !PX4_ISFINITE(_ctrl_state.airspeed) || !_ctrl_state.airspeed_valid) {
airspeed = _parameters.airspeed_trim;
if (nonfinite) {
perf_count(_nonfinite_input_perf);
}
} else {
/* prevent numerical drama by requiring 0.5 m/s minimal speed */
airspeed = math::max(0.5f, _ctrl_state.airspeed);
}
/*
* 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);
/* Use min airspeed to calculate ground speed scaling region.
* Don't scale below gspd_scaling_trim
*/
float groundspeed = sqrtf(_global_pos.vel_n * _global_pos.vel_n +
_global_pos.vel_e * _global_pos.vel_e);
float gspd_scaling_trim = (_parameters.airspeed_min * 0.6f);
float groundspeed_scaler = gspd_scaling_trim / ((groundspeed < gspd_scaling_trim) ? gspd_scaling_trim : groundspeed);
float roll_sp = _parameters.rollsp_offset_rad;
float pitch_sp = _parameters.pitchsp_offset_rad;
float yaw_sp = 0.0f;
float yaw_manual = 0.0f;
float throttle_sp = 0.0f;
/* Read attitude setpoint from uorb if
* - velocity control or position control is enabled (pos controller is running)
* - manual control is disabled (another app may send the setpoint, but it should
* for sure not be set from the remote control values)
*/
if (_vcontrol_mode.flag_control_auto_enabled ||
!_vcontrol_mode.flag_control_manual_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;
yaw_sp = _att_sp.yaw_body;
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();
_wheel_ctrl.reset_integrator();
}
} else if (_vcontrol_mode.flag_control_velocity_enabled) {
/* the pilot does not want to change direction,
* take straight attitude setpoint from position controller
*/
if (fabsf(_manual.y) < 0.01f && fabsf(_roll) < 0.2f) {
roll_sp = _att_sp.roll_body + _parameters.rollsp_offset_rad;
} else {
roll_sp = (_manual.y * _parameters.man_roll_max)
+ _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();
_wheel_ctrl.reset_integrator();
}
} else if (_vcontrol_mode.flag_control_altitude_enabled) {
/*
* Velocity should be controlled and manual is enabled.
*/
roll_sp = (_manual.y * _parameters.man_roll_max) + _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();
_wheel_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.rollsp_offset_rad;
pitch_sp = -(_manual.x * _parameters.man_pitch_max) + _parameters.pitchsp_offset_rad;
/* allow manual control of rudder deflection */
yaw_manual = _manual.r;
throttle_sp = _manual.z;
/*
* 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 != nullptr) {
/* publish the attitude setpoint */
orb_publish(_attitude_setpoint_id, _attitude_sp_pub, &att_sp);
} else if (_attitude_setpoint_id) {
/* advertise and publish */
_attitude_sp_pub = orb_advertise(_attitude_setpoint_id, &att_sp);
}
}
/* If the aircraft is on ground reset the integrators */
if (_vehicle_land_detected.landed || _vehicle_status.is_rotary_wing) {
_roll_ctrl.reset_integrator();
_pitch_ctrl.reset_integrator();
_yaw_ctrl.reset_integrator();
_wheel_ctrl.reset_integrator();
}
/* Prepare speed_body_u and speed_body_w */
float speed_body_u = _R(0, 0) * _global_pos.vel_n + _R(1, 0) * _global_pos.vel_e + _R(2, 0) * _global_pos.vel_d;
float speed_body_v = _R(0, 1) * _global_pos.vel_n + _R(1, 1) * _global_pos.vel_e + _R(2, 1) * _global_pos.vel_d;
float speed_body_w = _R(0, 2) * _global_pos.vel_n + _R(1, 2) * _global_pos.vel_e + _R(2, 2) * _global_pos.vel_d;
/* Prepare data for attitude controllers */
struct ECL_ControlData control_input = {};
control_input.roll = _roll;
control_input.pitch = _pitch;
control_input.yaw = _yaw;
control_input.roll_rate = _ctrl_state.roll_rate;
control_input.pitch_rate = _ctrl_state.pitch_rate;
control_input.yaw_rate = _ctrl_state.yaw_rate;
control_input.speed_body_u = speed_body_u;
control_input.speed_body_v = speed_body_v;
control_input.speed_body_w = speed_body_w;
control_input.acc_body_x = _accel.x;
control_input.acc_body_y = _accel.y;
control_input.acc_body_z = _accel.z;
control_input.roll_setpoint = roll_sp;
control_input.pitch_setpoint = pitch_sp;
control_input.yaw_setpoint = yaw_sp;
control_input.airspeed_min = _parameters.airspeed_min;
control_input.airspeed_max = _parameters.airspeed_max;
control_input.airspeed = airspeed;
control_input.scaler = airspeed_scaling;
control_input.lock_integrator = lock_integrator;
control_input.groundspeed = groundspeed;
control_input.groundspeed_scaler = groundspeed_scaler;
_yaw_ctrl.set_coordinated_method(_parameters.y_coordinated_method);
/* Run attitude controllers */
if (PX4_ISFINITE(roll_sp) && PX4_ISFINITE(pitch_sp)) {
_roll_ctrl.control_attitude(control_input);
_pitch_ctrl.control_attitude(control_input);
_yaw_ctrl.control_attitude(control_input); //runs last, because is depending on output of roll and pitch attitude
_wheel_ctrl.control_attitude(control_input);
/* Update input data for rate controllers */
control_input.roll_rate_setpoint = _roll_ctrl.get_desired_rate();
control_input.pitch_rate_setpoint = _pitch_ctrl.get_desired_rate();
control_input.yaw_rate_setpoint = _yaw_ctrl.get_desired_rate();
/* Run attitude RATE controllers which need the desired attitudes from above, add trim */
float roll_u = _roll_ctrl.control_bodyrate(control_input);
_actuators.control[0] = (PX4_ISFINITE(roll_u)) ? roll_u + _parameters.trim_roll : _parameters.trim_roll;
if (!PX4_ISFINITE(roll_u)) {
_roll_ctrl.reset_integrator();
perf_count(_nonfinite_output_perf);
if (_debug && loop_counter % 10 == 0) {
warnx("roll_u %.4f", (double)roll_u);
}
}
float pitch_u = _pitch_ctrl.control_bodyrate(control_input);
_actuators.control[1] = (PX4_ISFINITE(pitch_u)) ? pitch_u + _parameters.trim_pitch : _parameters.trim_pitch;
if (!PX4_ISFINITE(pitch_u)) {
_pitch_ctrl.reset_integrator();
perf_count(_nonfinite_output_perf);
if (_debug && 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 = 0.0f;
if (_att_sp.fw_control_yaw == true) {
yaw_u = _wheel_ctrl.control_bodyrate(control_input);
}
else {
yaw_u = _yaw_ctrl.control_bodyrate(control_input);
}
_actuators.control[2] = (PX4_ISFINITE(yaw_u)) ? yaw_u + _parameters.trim_yaw : _parameters.trim_yaw;
/* add in manual rudder control */
_actuators.control[2] += yaw_manual;
if (!PX4_ISFINITE(yaw_u)) {
_yaw_ctrl.reset_integrator();
_wheel_ctrl.reset_integrator();
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[3] = (PX4_ISFINITE(throttle_sp) &&
!(_vehicle_status.engine_failure ||
_vehicle_status.engine_failure_cmd)) ?
throttle_sp : 0.0f;
if (!PX4_ISFINITE(throttle_sp)) {
if (_debug && loop_counter % 10 == 0) {
warnx("throttle_sp %.4f", (double)throttle_sp);
}
}
} else {
perf_count(_nonfinite_input_perf);
if (_debug && 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
*/
_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 != nullptr) {
/* publish the attitude rates setpoint */
orb_publish(_rates_sp_id, _rate_sp_pub, &_rates_sp);
} else if (_rates_sp_id) {
/* advertise the attitude rates setpoint */
_rate_sp_pub = orb_advertise(_rates_sp_id, &_rates_sp);
}
} else {
/* manual/direct control */
_actuators.control[actuator_controls_s::INDEX_ROLL] = _manual.y + _parameters.trim_roll;
_actuators.control[actuator_controls_s::INDEX_PITCH] = -_manual.x + _parameters.trim_pitch;
_actuators.control[actuator_controls_s::INDEX_YAW] = _manual.r + _parameters.trim_yaw;
_actuators.control[actuator_controls_s::INDEX_THROTTLE] = _manual.z;
}
_actuators.control[actuator_controls_s::INDEX_FLAPS] = flaps_applied;
_actuators.control[5] = _manual.aux1;
_actuators.control[actuator_controls_s::INDEX_AIRBRAKES] = flaperon_applied;
_actuators.control[7] = _manual.aux3;
/* lazily publish the setpoint only once available */
_actuators.timestamp = hrt_absolute_time();
_actuators.timestamp_sample = _ctrl_state.timestamp;
_actuators_airframe.timestamp = hrt_absolute_time();
_actuators_airframe.timestamp_sample = _ctrl_state.timestamp;
/* Only publish if any of the proper modes are enabled */
if (_vcontrol_mode.flag_control_rates_enabled ||
_vcontrol_mode.flag_control_attitude_enabled ||
_vcontrol_mode.flag_control_manual_enabled) {
/* publish the actuator controls */
if (_actuators_0_pub != nullptr) {
orb_publish(_actuators_id, _actuators_0_pub, &_actuators);
} else if (_actuators_id) {
_actuators_0_pub = orb_advertise(_actuators_id, &_actuators);
}
if (_actuators_2_pub != nullptr) {
/* publish the actuator controls*/
orb_publish(ORB_ID(actuator_controls_2), _actuators_2_pub, &_actuators_airframe);
} else {
/* advertise and publish */
_actuators_2_pub = orb_advertise(ORB_ID(actuator_controls_2), &_actuators_airframe);
}
}
}
loop_counter++;
perf_end(_loop_perf);
}
warnx("exiting.\n");
_control_task = -1;
_task_running = false;
}
int
ETSAirspeed::collect()
{
int ret = -EIO;
/* read from the sensor */
uint8_t val[2] = {0, 0};
perf_begin(_sample_perf);
ret = transfer(nullptr, 0, &val[0], 2);
if (ret < 0) {
perf_count(_comms_errors);
return ret;
}
uint16_t diff_pres_pa_raw = val[1] << 8 | val[0];
if (diff_pres_pa_raw == 0) {
// a zero value means the pressure sensor cannot give us a
// value. We need to return, and not report a value or the
// caller could end up using this value as part of an
// average
perf_count(_comms_errors);
DEVICE_LOG("zero value from sensor");
return -1;
}
// The raw value still should be compensated for the known offset
diff_pres_pa_raw -= _diff_pres_offset;
// Track maximum differential pressure measured (so we can work out top speed).
if (diff_pres_pa_raw > _max_differential_pressure_pa) {
_max_differential_pressure_pa = diff_pres_pa_raw;
}
differential_pressure_s report;
report.timestamp = hrt_absolute_time();
report.error_count = perf_event_count(_comms_errors);
// XXX we may want to smooth out the readings to remove noise.
report.differential_pressure_filtered_pa = diff_pres_pa_raw;
report.differential_pressure_raw_pa = diff_pres_pa_raw;
report.temperature = -1000.0f;
report.max_differential_pressure_pa = _max_differential_pressure_pa;
if (_airspeed_pub != nullptr && !(_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(differential_pressure), _airspeed_pub, &report);
}
new_report(report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
int flow_position_estimator_thread_main(int argc, char *argv[])
{
/* welcome user */
thread_running = true;
printf("[flow position estimator] starting\n");
/* rotation matrix for transformation of optical flow speed vectors */
static const int8_t rotM_flow_sensor[3][3] = {{ 0, -1, 0 },
{ 1, 0, 0 },
{ 0, 0, 1 }}; // 90deg rotated
const float time_scale = powf(10.0f,-6.0f);
static float speed[3] = {0.0f, 0.0f, 0.0f};
static float flow_speed[3] = {0.0f, 0.0f, 0.0f};
static float global_speed[3] = {0.0f, 0.0f, 0.0f};
static uint32_t counter = 0;
static uint64_t time_last_flow = 0; // in ms
static float dt = 0.0f; // seconds
static float sonar_last = 0.0f;
static bool sonar_valid = false;
static float sonar_lp = 0.0f;
/* subscribe to vehicle status, attitude, sensors and flow*/
struct actuator_armed_s armed;
memset(&armed, 0, sizeof(armed));
struct vehicle_control_mode_s control_mode;
memset(&control_mode, 0, sizeof(control_mode));
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_attitude_setpoint_s att_sp;
memset(&att_sp, 0, sizeof(att_sp));
struct optical_flow_s flow;
memset(&flow, 0, sizeof(flow));
/* subscribe to parameter changes */
int parameter_update_sub = orb_subscribe(ORB_ID(parameter_update));
/* subscribe to armed topic */
int armed_sub = orb_subscribe(ORB_ID(actuator_armed));
/* subscribe to safety topic */
int control_mode_sub = orb_subscribe(ORB_ID(vehicle_control_mode));
/* subscribe to attitude */
int vehicle_attitude_sub = orb_subscribe(ORB_ID(vehicle_attitude));
/* subscribe to attitude setpoint */
int vehicle_attitude_setpoint_sub = orb_subscribe(ORB_ID(vehicle_attitude_setpoint));
/* subscribe to optical flow*/
int optical_flow_sub = orb_subscribe(ORB_ID(optical_flow));
/* init local position and filtered flow struct */
struct vehicle_local_position_s local_pos = {
.x = 0.0f,
.y = 0.0f,
.z = 0.0f,
.vx = 0.0f,
.vy = 0.0f,
.vz = 0.0f
};
struct filtered_bottom_flow_s filtered_flow = {
.sumx = 0.0f,
.sumy = 0.0f,
.vx = 0.0f,
.vy = 0.0f
};
/* advert pub messages */
orb_advert_t local_pos_pub = orb_advertise(ORB_ID(vehicle_local_position), &local_pos);
orb_advert_t filtered_flow_pub = orb_advertise(ORB_ID(filtered_bottom_flow), &filtered_flow);
/* vehicle flying status parameters */
bool vehicle_liftoff = false;
bool sensors_ready = false;
/* parameters init*/
struct flow_position_estimator_params params;
struct flow_position_estimator_param_handles param_handles;
parameters_init(¶m_handles);
parameters_update(¶m_handles, ¶ms);
perf_counter_t mc_loop_perf = perf_alloc(PC_ELAPSED, "flow_position_estimator_runtime");
perf_counter_t mc_interval_perf = perf_alloc(PC_INTERVAL, "flow_position_estimator_interval");
perf_counter_t mc_err_perf = perf_alloc(PC_COUNT, "flow_position_estimator_err");
while (!thread_should_exit)
{
if (sensors_ready)
{
/*This runs at the rate of the sensors */
struct pollfd fds[2] = {
{ .fd = optical_flow_sub, .events = POLLIN },
{ .fd = parameter_update_sub, .events = POLLIN }
};
/* wait for a sensor update, check for exit condition every 500 ms */
int ret = poll(fds, 2, 500);
if (ret < 0)
{
/* poll error, count it in perf */
perf_count(mc_err_perf);
}
else if (ret == 0)
{
/* no return value, ignore */
// printf("[flow position estimator] no bottom flow.\n");
}
else
{
/* parameter update available? */
if (fds[1].revents & POLLIN)
{
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), parameter_update_sub, &update);
parameters_update(¶m_handles, ¶ms);
printf("[flow position estimator] parameters updated.\n");
}
/* only if flow data changed */
if (fds[0].revents & POLLIN)
{
perf_begin(mc_loop_perf);
orb_copy(ORB_ID(optical_flow), optical_flow_sub, &flow);
/* got flow, updating attitude and status as well */
orb_copy(ORB_ID(vehicle_attitude), vehicle_attitude_sub, &att);
orb_copy(ORB_ID(vehicle_attitude_setpoint), vehicle_attitude_setpoint_sub, &att_sp);
orb_copy(ORB_ID(actuator_armed), armed_sub, &armed);
orb_copy(ORB_ID(vehicle_control_mode), control_mode_sub, &control_mode);
/* vehicle state estimation */
float sonar_new = flow.ground_distance_m;
/* set liftoff boolean
* -> at bottom sonar sometimes does not work correctly, and has to be calibrated (distance higher than 0.3m)
* -> accept sonar measurements after reaching calibration distance (values between 0.3m and 1.0m for some time)
* -> minimum sonar value 0.3m
*/
if (!vehicle_liftoff)
{
if (armed.armed && att_sp.thrust > params.minimum_liftoff_thrust && sonar_new > 0.3f && sonar_new < 1.0f)
vehicle_liftoff = true;
}
else
{
if (!armed.armed || (att_sp.thrust < params.minimum_liftoff_thrust && sonar_new <= 0.3f))
vehicle_liftoff = false;
}
/* calc dt between flow timestamps */
/* ignore first flow msg */
if(time_last_flow == 0)
{
time_last_flow = flow.timestamp;
continue;
}
dt = (float)(flow.timestamp - time_last_flow) * time_scale ;
time_last_flow = flow.timestamp;
/* only make position update if vehicle is lift off or DEBUG is activated*/
if (vehicle_liftoff || params.debug)
{
/* copy flow */
flow_speed[0] = flow.flow_comp_x_m;
flow_speed[1] = flow.flow_comp_y_m;
flow_speed[2] = 0.0f;
/* convert to bodyframe velocity */
for(uint8_t i = 0; i < 3; i++)
{
float sum = 0.0f;
for(uint8_t j = 0; j < 3; j++)
sum = sum + flow_speed[j] * rotM_flow_sensor[j][i];
speed[i] = sum;
}
/* update filtered flow */
filtered_flow.sumx = filtered_flow.sumx + speed[0] * dt;
filtered_flow.sumy = filtered_flow.sumy + speed[1] * dt;
filtered_flow.vx = speed[0];
filtered_flow.vy = speed[1];
// TODO add yaw rotation correction (with distance to vehicle zero)
/* convert to globalframe velocity
* -> local position is currently not used for position control
*/
for(uint8_t i = 0; i < 3; i++)
{
float sum = 0.0f;
for(uint8_t j = 0; j < 3; j++)
sum = sum + speed[j] * att.R[i][j];
global_speed[i] = sum;
}
local_pos.x = local_pos.x + global_speed[0] * dt;
local_pos.y = local_pos.y + global_speed[1] * dt;
local_pos.vx = global_speed[0];
local_pos.vy = global_speed[1];
}
else
{
/* set speed to zero and let position as it is */
filtered_flow.vx = 0;
filtered_flow.vy = 0;
local_pos.vx = 0;
local_pos.vy = 0;
}
/* filtering ground distance */
if (!vehicle_liftoff || !armed.armed)
{
/* not possible to fly */
sonar_valid = false;
local_pos.z = 0.0f;
}
else
{
sonar_valid = true;
}
if (sonar_valid || params.debug)
{
/* simple lowpass sonar filtering */
/* if new value or with sonar update frequency */
if (sonar_new != sonar_last || counter % 10 == 0)
{
sonar_lp = 0.05f * sonar_new + 0.95f * sonar_lp;
sonar_last = sonar_new;
}
float height_diff = sonar_new - sonar_lp;
/* if over 1/2m spike follow lowpass */
if (height_diff < -params.sonar_lower_lp_threshold || height_diff > params.sonar_upper_lp_threshold)
{
local_pos.z = -sonar_lp;
}
else
{
local_pos.z = -sonar_new;
}
}
filtered_flow.timestamp = hrt_absolute_time();
local_pos.timestamp = hrt_absolute_time();
/* publish local position */
if(isfinite(local_pos.x) && isfinite(local_pos.y) && isfinite(local_pos.z)
&& isfinite(local_pos.vx) && isfinite(local_pos.vy))
{
orb_publish(ORB_ID(vehicle_local_position), local_pos_pub, &local_pos);
}
/* publish filtered flow */
if(isfinite(filtered_flow.sumx) && isfinite(filtered_flow.sumy) && isfinite(filtered_flow.vx) && isfinite(filtered_flow.vy))
{
orb_publish(ORB_ID(filtered_bottom_flow), filtered_flow_pub, &filtered_flow);
}
/* measure in what intervals the position estimator runs */
perf_count(mc_interval_perf);
perf_end(mc_loop_perf);
}
}
}
else
{
/* sensors not ready waiting for first attitude msg */
/* polling */
struct pollfd fds[1] = {
{ .fd = vehicle_attitude_sub, .events = POLLIN },
};
/* wait for a attitude message, check for exit condition every 5 s */
int ret = poll(fds, 1, 5000);
if (ret < 0)
{
/* poll error, count it in perf */
perf_count(mc_err_perf);
}
else if (ret == 0)
{
/* no return value, ignore */
printf("[flow position estimator] no attitude received.\n");
}
else
{
if (fds[0].revents & POLLIN){
sensors_ready = true;
printf("[flow position estimator] initialized.\n");
}
}
}
int
MEASAirspeedSim::collect()
{
int ret = -EIO;
/* read from the sensor */
#pragma pack(push, 1)
struct {
float temperature;
float diff_pressure;
} airspeed_report;
#pragma pack(pop)
perf_begin(_sample_perf);
ret = transfer(nullptr, 0, (uint8_t *)&airspeed_report, sizeof(airspeed_report));
if (ret < 0) {
perf_count(_comms_errors);
perf_end(_sample_perf);
return ret;
}
uint8_t status = 0;
switch (status) {
case 0:
break;
case 1:
/* fallthrough */
case 2:
/* fallthrough */
case 3:
perf_count(_comms_errors);
perf_end(_sample_perf);
return -EAGAIN;
}
float temperature = airspeed_report.temperature;
float diff_press_pa_raw = airspeed_report.diff_pressure * 100.0f; // convert from millibar to bar
struct differential_pressure_s report;
/* track maximum differential pressure measured (so we can work out top speed). */
if (diff_press_pa_raw > _max_differential_pressure_pa) {
_max_differential_pressure_pa = diff_press_pa_raw;
}
report.timestamp = hrt_absolute_time();
report.error_count = perf_event_count(_comms_errors);
report.temperature = temperature;
report.differential_pressure_filtered_pa = _filter.apply(diff_press_pa_raw);
report.differential_pressure_raw_pa = diff_press_pa_raw;
report.max_differential_pressure_pa = _max_differential_pressure_pa;
if (_airspeed_pub != nullptr && !(_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(differential_pressure), _airspeed_pub, &report);
}
new_report(report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
void
Navigator::task_main()
{
bool have_geofence_position_data = false;
/* Try to load the geofence:
* if /fs/microsd/etc/geofence.txt load from this file */
struct stat buffer;
if (stat(GEOFENCE_FILENAME, &buffer) == 0) {
PX4_INFO("Loading geofence from %s", GEOFENCE_FILENAME);
_geofence.loadFromFile(GEOFENCE_FILENAME);
}
/* do subscriptions */
_global_pos_sub = orb_subscribe(ORB_ID(vehicle_global_position));
_local_pos_sub = orb_subscribe(ORB_ID(vehicle_local_position));
_gps_pos_sub = orb_subscribe(ORB_ID(vehicle_gps_position));
_sensor_combined_sub = orb_subscribe(ORB_ID(sensor_combined));
_fw_pos_ctrl_status_sub = orb_subscribe(ORB_ID(fw_pos_ctrl_status));
_vstatus_sub = orb_subscribe(ORB_ID(vehicle_status));
_land_detected_sub = orb_subscribe(ORB_ID(vehicle_land_detected));
_home_pos_sub = orb_subscribe(ORB_ID(home_position));
_onboard_mission_sub = orb_subscribe(ORB_ID(onboard_mission));
_offboard_mission_sub = orb_subscribe(ORB_ID(offboard_mission));
_param_update_sub = orb_subscribe(ORB_ID(parameter_update));
_vehicle_command_sub = orb_subscribe(ORB_ID(vehicle_command));
_traffic_sub = orb_subscribe(ORB_ID(transponder_report));
/* copy all topics first time */
vehicle_status_update();
vehicle_land_detected_update();
global_position_update();
local_position_update();
gps_position_update();
sensor_combined_update();
home_position_update(true);
fw_pos_ctrl_status_update(true);
params_update();
/* wakeup source(s) */
px4_pollfd_struct_t fds[1] = {};
/* Setup of loop */
fds[0].fd = _local_pos_sub;
fds[0].events = POLLIN;
/* rate-limit position subscription to 20 Hz / 50 ms */
orb_set_interval(_local_pos_sub, 50);
while (!_task_should_exit) {
/* wait for up to 1000ms for data */
int pret = px4_poll(&fds[0], (sizeof(fds) / sizeof(fds[0])), 1000);
if (pret == 0) {
/* Let the loop run anyway, don't do `continue` here. */
} else if (pret < 0) {
/* this is undesirable but not much we can do - might want to flag unhappy status */
PX4_ERR("poll error %d, %d", pret, errno);
usleep(10000);
continue;
} else {
if (fds[0].revents & POLLIN) {
/* success, local pos is available */
local_position_update();
}
}
perf_begin(_loop_perf);
bool updated;
/* gps updated */
orb_check(_gps_pos_sub, &updated);
if (updated) {
gps_position_update();
if (_geofence.getSource() == Geofence::GF_SOURCE_GPS) {
have_geofence_position_data = true;
}
}
/* global position updated */
orb_check(_global_pos_sub, &updated);
if (updated) {
global_position_update();
if (_geofence.getSource() == Geofence::GF_SOURCE_GLOBALPOS) {
have_geofence_position_data = true;
}
}
/* sensors combined updated */
orb_check(_sensor_combined_sub, &updated);
if (updated) {
sensor_combined_update();
}
/* parameters updated */
orb_check(_param_update_sub, &updated);
if (updated) {
params_update();
}
/* vehicle status updated */
orb_check(_vstatus_sub, &updated);
if (updated) {
vehicle_status_update();
}
/* vehicle land detected updated */
orb_check(_land_detected_sub, &updated);
if (updated) {
vehicle_land_detected_update();
}
/* navigation capabilities updated */
orb_check(_fw_pos_ctrl_status_sub, &updated);
if (updated) {
fw_pos_ctrl_status_update();
}
/* home position updated */
orb_check(_home_pos_sub, &updated);
if (updated) {
home_position_update();
}
/* vehicle_command updated */
orb_check(_vehicle_command_sub, &updated);
if (updated) {
vehicle_command_s cmd;
orb_copy(ORB_ID(vehicle_command), _vehicle_command_sub, &cmd);
if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_GO_AROUND) {
// DO_GO_AROUND is currently handled by the position controller (unacknowledged)
// TODO: move DO_GO_AROUND handling to navigator
publish_vehicle_command_ack(cmd, vehicle_command_s::VEHICLE_CMD_RESULT_ACCEPTED);
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_REPOSITION) {
position_setpoint_triplet_s *rep = get_reposition_triplet();
position_setpoint_triplet_s *curr = get_position_setpoint_triplet();
// store current position as previous position and goal as next
rep->previous.yaw = get_global_position()->yaw;
rep->previous.lat = get_global_position()->lat;
rep->previous.lon = get_global_position()->lon;
rep->previous.alt = get_global_position()->alt;
rep->current.loiter_radius = get_loiter_radius();
rep->current.loiter_direction = 1;
rep->current.type = position_setpoint_s::SETPOINT_TYPE_LOITER;
rep->current.cruising_speed = get_cruising_speed();
rep->current.cruising_throttle = get_cruising_throttle();
// Go on and check which changes had been requested
if (PX4_ISFINITE(cmd.param4)) {
rep->current.yaw = cmd.param4;
} else {
rep->current.yaw = NAN;
}
if (PX4_ISFINITE(cmd.param5) && PX4_ISFINITE(cmd.param6)) {
// Position change with optional altitude change
rep->current.lat = (cmd.param5 < 1000) ? cmd.param5 : cmd.param5 / (double)1e7;
rep->current.lon = (cmd.param6 < 1000) ? cmd.param6 : cmd.param6 / (double)1e7;
if (PX4_ISFINITE(cmd.param7)) {
rep->current.alt = cmd.param7;
} else {
rep->current.alt = get_global_position()->alt;
}
} else if (PX4_ISFINITE(cmd.param7) && curr->current.valid
&& PX4_ISFINITE(curr->current.lat)
&& PX4_ISFINITE(curr->current.lon)) {
// Altitude without position change
rep->current.lat = curr->current.lat;
rep->current.lon = curr->current.lon;
rep->current.alt = cmd.param7;
} else {
// All three set to NaN - hold in current position
rep->current.lat = get_global_position()->lat;
rep->current.lon = get_global_position()->lon;
rep->current.alt = get_global_position()->alt;
}
rep->previous.valid = true;
rep->current.valid = true;
rep->next.valid = false;
// CMD_DO_REPOSITION is acknowledged by commander
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_NAV_TAKEOFF) {
position_setpoint_triplet_s *rep = get_takeoff_triplet();
// store current position as previous position and goal as next
rep->previous.yaw = get_global_position()->yaw;
rep->previous.lat = get_global_position()->lat;
rep->previous.lon = get_global_position()->lon;
rep->previous.alt = get_global_position()->alt;
rep->current.loiter_radius = get_loiter_radius();
rep->current.loiter_direction = 1;
rep->current.type = position_setpoint_s::SETPOINT_TYPE_TAKEOFF;
if (home_position_valid()) {
rep->current.yaw = cmd.param4;
rep->previous.valid = true;
} else {
rep->current.yaw = get_local_position()->yaw;
rep->previous.valid = false;
}
if (PX4_ISFINITE(cmd.param5) && PX4_ISFINITE(cmd.param6)) {
rep->current.lat = (cmd.param5 < 1000) ? cmd.param5 : cmd.param5 / (double)1e7;
rep->current.lon = (cmd.param6 < 1000) ? cmd.param6 : cmd.param6 / (double)1e7;
} else {
// If one of them is non-finite, reset both
rep->current.lat = NAN;
rep->current.lon = NAN;
}
rep->current.alt = cmd.param7;
rep->current.valid = true;
rep->next.valid = false;
// CMD_NAV_TAKEOFF is acknowledged by commander
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_LAND_START) {
/* find NAV_CMD_DO_LAND_START in the mission and
* use MAV_CMD_MISSION_START to start the mission there
*/
int land_start = _mission.find_offboard_land_start();
if (land_start != -1) {
vehicle_command_s vcmd = {};
vcmd.command = vehicle_command_s::VEHICLE_CMD_MISSION_START;
vcmd.param1 = land_start;
publish_vehicle_cmd(&vcmd);
} else {
PX4_WARN("planned landing not available");
}
publish_vehicle_command_ack(cmd, vehicle_command_s::VEHICLE_CMD_RESULT_ACCEPTED);
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_MISSION_START) {
if (get_mission_result()->valid &&
PX4_ISFINITE(cmd.param1) && (cmd.param1 >= 0) && (cmd.param1 < _mission_result.seq_total)) {
_mission.set_current_offboard_mission_index(cmd.param1);
}
// CMD_MISSION_START is acknowledged by commander
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_CHANGE_SPEED) {
if (cmd.param2 > FLT_EPSILON) {
// XXX not differentiating ground and airspeed yet
set_cruising_speed(cmd.param2);
} else {
set_cruising_speed();
/* if no speed target was given try to set throttle */
if (cmd.param3 > FLT_EPSILON) {
set_cruising_throttle(cmd.param3 / 100);
} else {
set_cruising_throttle();
}
}
// TODO: handle responses for supported DO_CHANGE_SPEED options?
publish_vehicle_command_ack(cmd, vehicle_command_s::VEHICLE_CMD_RESULT_ACCEPTED);
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_SET_ROI
|| cmd.command == vehicle_command_s::VEHICLE_CMD_NAV_ROI) {
_vroi = {};
_vroi.mode = cmd.param1;
switch (_vroi.mode) {
case vehicle_command_s::VEHICLE_ROI_NONE:
break;
case vehicle_command_s::VEHICLE_ROI_WPNEXT:
// TODO: implement point toward next MISSION
break;
case vehicle_command_s::VEHICLE_ROI_WPINDEX:
_vroi.mission_seq = cmd.param2;
break;
case vehicle_command_s::VEHICLE_ROI_LOCATION:
_vroi.lat = cmd.param5;
_vroi.lon = cmd.param6;
_vroi.alt = cmd.param7;
break;
case vehicle_command_s::VEHICLE_ROI_TARGET:
_vroi.target_seq = cmd.param2;
break;
default:
_vroi.mode = vehicle_command_s::VEHICLE_ROI_NONE;
break;
}
_vroi.timestamp = hrt_absolute_time();
if (_vehicle_roi_pub != nullptr) {
orb_publish(ORB_ID(vehicle_roi), _vehicle_roi_pub, &_vroi);
} else {
_vehicle_roi_pub = orb_advertise(ORB_ID(vehicle_roi), &_vroi);
}
publish_vehicle_command_ack(cmd, vehicle_command_s::VEHICLE_CMD_RESULT_ACCEPTED);
}
}
/* Check for traffic */
check_traffic();
/* Check geofence violation */
static hrt_abstime last_geofence_check = 0;
if (have_geofence_position_data &&
(_geofence.getGeofenceAction() != geofence_result_s::GF_ACTION_NONE) &&
(hrt_elapsed_time(&last_geofence_check) > GEOFENCE_CHECK_INTERVAL)) {
bool inside = _geofence.check(_global_pos, _gps_pos, _sensor_combined.baro_alt_meter, _home_pos,
home_position_valid());
last_geofence_check = hrt_absolute_time();
have_geofence_position_data = false;
_geofence_result.timestamp = hrt_absolute_time();
_geofence_result.geofence_action = _geofence.getGeofenceAction();
_geofence_result.home_required = _geofence.isHomeRequired();
if (!inside) {
/* inform other apps via the mission result */
_geofence_result.geofence_violated = true;
/* Issue a warning about the geofence violation once */
if (!_geofence_violation_warning_sent) {
mavlink_log_critical(&_mavlink_log_pub, "Geofence violation");
_geofence_violation_warning_sent = true;
}
} else {
/* inform other apps via the mission result */
_geofence_result.geofence_violated = false;
/* Reset the _geofence_violation_warning_sent field */
_geofence_violation_warning_sent = false;
}
publish_geofence_result();
}
/* Do stuff according to navigation state set by commander */
NavigatorMode *navigation_mode_new{nullptr};
switch (_vstatus.nav_state) {
case vehicle_status_s::NAVIGATION_STATE_AUTO_MISSION:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_mission;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_LOITER:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_loiter;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_RCRECOVER:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_rcLoss;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_RTL:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_rtl;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_TAKEOFF:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_takeoff;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_LAND:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_land;
break;
case vehicle_status_s::NAVIGATION_STATE_DESCEND:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_land;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_RTGS:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_dataLinkLoss;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_LANDENGFAIL:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_engineFailure;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_LANDGPSFAIL:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_gpsFailure;
break;
case vehicle_status_s::NAVIGATION_STATE_AUTO_FOLLOW_TARGET:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = &_follow_target;
break;
case vehicle_status_s::NAVIGATION_STATE_MANUAL:
case vehicle_status_s::NAVIGATION_STATE_ACRO:
case vehicle_status_s::NAVIGATION_STATE_ALTCTL:
case vehicle_status_s::NAVIGATION_STATE_POSCTL:
case vehicle_status_s::NAVIGATION_STATE_TERMINATION:
case vehicle_status_s::NAVIGATION_STATE_OFFBOARD:
case vehicle_status_s::NAVIGATION_STATE_STAB:
default:
_pos_sp_triplet_published_invalid_once = false;
navigation_mode_new = nullptr;
_can_loiter_at_sp = false;
break;
}
/* we have a new navigation mode: reset triplet */
if (_navigation_mode != navigation_mode_new) {
reset_triplets();
}
_navigation_mode = navigation_mode_new;
/* iterate through navigation modes and set active/inactive for each */
for (unsigned int i = 0; i < NAVIGATOR_MODE_ARRAY_SIZE; i++) {
_navigation_mode_array[i]->run(_navigation_mode == _navigation_mode_array[i]);
}
/* if we landed and have not received takeoff setpoint then stay in idle */
if (_land_detected.landed &&
!((_vstatus.nav_state == vehicle_status_s::NAVIGATION_STATE_AUTO_TAKEOFF)
|| (_vstatus.nav_state == vehicle_status_s::NAVIGATION_STATE_AUTO_MISSION))) {
_pos_sp_triplet.current.type = position_setpoint_s::SETPOINT_TYPE_IDLE;
_pos_sp_triplet.current.valid = true;
_pos_sp_triplet.previous.valid = false;
_pos_sp_triplet.next.valid = false;
}
/* if nothing is running, set position setpoint triplet invalid once */
if (_navigation_mode == nullptr && !_pos_sp_triplet_published_invalid_once) {
_pos_sp_triplet_published_invalid_once = true;
reset_triplets();
}
if (_pos_sp_triplet_updated) {
_pos_sp_triplet.timestamp = hrt_absolute_time();
publish_position_setpoint_triplet();
_pos_sp_triplet_updated = false;
}
if (_mission_result_updated) {
publish_mission_result();
_mission_result_updated = false;
}
perf_end(_loop_perf);
}
orb_unsubscribe(_global_pos_sub);
orb_unsubscribe(_local_pos_sub);
orb_unsubscribe(_gps_pos_sub);
orb_unsubscribe(_sensor_combined_sub);
orb_unsubscribe(_fw_pos_ctrl_status_sub);
orb_unsubscribe(_vstatus_sub);
orb_unsubscribe(_land_detected_sub);
orb_unsubscribe(_home_pos_sub);
orb_unsubscribe(_onboard_mission_sub);
orb_unsubscribe(_offboard_mission_sub);
orb_unsubscribe(_param_update_sub);
orb_unsubscribe(_vehicle_command_sub);
PX4_INFO("exiting");
_navigator_task = -1;
}
int
ETSAirspeed::collect()
{
int ret = -EIO;
/* read from the sensor */
uint8_t val[2] = {0, 0};
perf_begin(_sample_perf);
ret = transfer(nullptr, 0, &val[0], 2);
if (ret < 0) {
perf_count(_comms_errors);
return ret;
}
uint16_t diff_pres_pa_raw = val[1] << 8 | val[0];
uint16_t diff_pres_pa;
if (diff_pres_pa_raw == 0) {
// a zero value means the pressure sensor cannot give us a
// value. We need to return, and not report a value or the
// caller could end up using this value as part of an
// average
perf_count(_comms_errors);
log("zero value from sensor");
return -1;
}
if (diff_pres_pa_raw < _diff_pres_offset + MIN_ACCURATE_DIFF_PRES_PA) {
diff_pres_pa = 0;
} else {
diff_pres_pa = diff_pres_pa_raw - _diff_pres_offset;
}
// Track maximum differential pressure measured (so we can work out top speed).
if (diff_pres_pa > _max_differential_pressure_pa) {
_max_differential_pressure_pa = diff_pres_pa;
}
// XXX we may want to smooth out the readings to remove noise.
differential_pressure_s report;
report.timestamp = hrt_absolute_time();
report.error_count = perf_event_count(_comms_errors);
report.differential_pressure_pa = (float)diff_pres_pa;
report.differential_pressure_raw_pa = (float)diff_pres_pa_raw;
report.voltage = 0;
report.max_differential_pressure_pa = _max_differential_pressure_pa;
if (_airspeed_pub > 0 && !(_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(differential_pressure), _airspeed_pub, &report);
}
new_report(report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
/*
* 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
*/
void app_att_est_ekf_main(void* parameter)
{
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();
sensor_combined_s raw;
rt_memset(&raw, 0, sizeof(raw));
//struct vehicle_gps_position_s gps;
//rt_memset(&gps, 0, sizeof(gps));
//struct vehicle_global_position_s global_pos;
//rt_memset(&global_pos, 0, sizeof(global_pos));
vehicle_attitude_s att;
rt_memset(&att, 0, sizeof(att));
//struct vehicle_control_mode_s control_mode;
//rt_memset(&control_mode, 0, sizeof(control_mode));
uint64_t last_data = 0;
uint64_t last_measurement = 0;
rt_uint32_t sensors_sub = 0;
uint64_t last_timestamp_acc = 0;
uint64_t last_timestamp_gyro = 0;
uint64_t last_timestamp_mag = 0;
/* rotation matrix */
float R[3][3] = {1,0,0,
0,1,0,
0,0,1};
/* subscribe to raw data */
orb_subscribe(ORB_ID(sensor_combined),&sensors_sub);
orb_advertise(ORB_ID(vehicle_attitude), &att);
att_est_ekf_running = true;
bool initialized = false;
/* magnetic declination, in radians */
float mag_decl = 0.0f;
/* rotation matrix for magnetic declination */
float R_mag[3][3] = {1,0,0,
0,1,0,
0,0,1};
uint8_t update_vect[3] = {0, 0, 0};
rt_memset(&ekf_params, 0, sizeof(ekf_params));
ekf_params.q[0] = 1e-4f;
ekf_params.q[1] = 0.08f;
ekf_params.q[2] = 0.009f;
ekf_params.q[3] = 0.005f;
ekf_params.q[4] = 0.0f;
ekf_params.r[0] = 0.0008f;
ekf_params.r[1] = 10000.0f;
ekf_params.r[2] = 100.0f;
ekf_params.r[3] = 0.0f;
/* Main loop*/
while (!att_est_ekf_should_exit) {
/* only run filter if sensor values changed */
if (orb_check(&sensors_sub,5000) == RT_EOK) {
/* get latest measurements */
orb_copy(ORB_ID(sensor_combined), &raw);
}
else{
rt_kprintf("sensors data lost!\n");
}
if (!initialized) {
initialized = true;
}
else {
/* Calculate data time difference in seconds */
dt = (raw.acc_timestamp - last_measurement) / 1000000.0f;
last_measurement = raw.acc_timestamp;
if(raw.gyro_timestamp != last_timestamp_gyro)
{
update_vect[0] = 1;
last_timestamp_gyro = raw.gyro_timestamp;
}
if(raw.acc_timestamp != last_timestamp_acc)
{
update_vect[1] = 1;
last_timestamp_acc = raw.acc_timestamp;
}
if(raw.mag_timestamp != last_timestamp_mag)
{
update_vect[2] = 1;
last_timestamp_mag = raw.mag_timestamp;
}
z_k[0] = raw.gyro_rad_s[0];
z_k[1] = raw.gyro_rad_s[1];
z_k[2] = raw.gyro_rad_s[2];
z_k[3] = raw.acc_m_s2[0];
z_k[4] = raw.acc_m_s2[1];
z_k[5] = raw.acc_m_s2[2];
z_k[6] = raw.mag_ga[0];
z_k[7] = raw.mag_ga[1];
z_k[8] = raw.mag_ga[2];
uint64_t now = hrt_absolute_time();
unsigned int time_elapsed = now - last_run;
last_run = now;
if (time_elapsed > loop_interval_alarm) {
/* cpu overload */
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;
/* update mag declination rotation matrix */
euler_to_rot_mat(R_mag,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);
for(int i = 0;i < 3;i++)
{
update_vect[i] = 0;
}
/* swap values for next iteration, check for fatal inputs */
if (isfinite(euler[0]) && isfinite(euler[1]) && isfinite(euler[2])) {
rt_memcpy(P_aposteriori_k, P_aposteriori, sizeof(P_aposteriori_k));
rt_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.acc_timestamp - last_data > 30000)
printf("[attitude estimator ekf] sensor data missed! (%llu)\n", raw.acc_timestamp - last_data);
last_data = raw.acc_timestamp;
/* send out */
att.timestamp = raw.acc_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.acc_m_s2[0];
att.g_comp[1] = raw.acc_m_s2[1];
att.g_comp[2] = raw.acc_m_s2[2];
/* copy offsets */
rt_memcpy(&att.rate_offsets, &(x_aposteriori[3]), sizeof(att.rate_offsets));
/* magnetic declination */
float R_body[3][3] = {0};
rt_memcpy(&R_body, &Rot_matrix, sizeof(R_body));
//R = R_mag * R_body;
for(int i = 0;i < 3;i++){
for(int j = 0;j < 3;i++)
{
R[i][j] = 0;
for(int k = 0;k < 3;k++)
R[i][j] += R_mag[i][k] * R_body[k][j];
}
}
/* copy rotation matrix */
rt_memcpy(&att.R, &R, sizeof(att.R));
att.R_valid = true;
if (isfinite(att.roll) && isfinite(att.pitch) && isfinite(att.yaw)) {
// Broadcast
orb_publish(ORB_ID(vehicle_attitude), &att);
} else {
rt_kprintf("NaN in roll/pitch/yaw estimate!");
}
}
}
att_est_ekf_running = false;
}
void
FXAS21002C::measure()
{
/* status register and data as read back from the device */
#pragma pack(push, 1)
struct {
uint8_t cmd;
uint8_t status;
int16_t x;
int16_t y;
int16_t z;
} raw_gyro_report;
#pragma pack(pop)
struct gyro_report gyro_report;
/* start the performance counter */
perf_begin(_sample_perf);
check_registers();
if (_register_wait != 0) {
// we are waiting for some good transfers before using
// the sensor again.
_register_wait--;
perf_end(_sample_perf);
return;
}
/* fetch data from the sensor */
memset(&raw_gyro_report, 0, sizeof(raw_gyro_report));
raw_gyro_report.cmd = DIR_READ(FXAS21002C_STATUS);
transfer((uint8_t *)&raw_gyro_report, (uint8_t *)&raw_gyro_report, sizeof(raw_gyro_report));
if (!(raw_gyro_report.status & DR_STATUS_ZYXDR)) {
perf_end(_sample_perf);
perf_count(_duplicates);
return;
}
/*
* The TEMP register contains an 8-bit 2's complement temperature value with a range
* of –128 °C to +127 °C and a scaling of 1 °C/LSB. The temperature data is only
* compensated (factory trim values applied) when the device is operating in the Active
* mode and actively measuring the angular rate.
*/
if ((_read % _current_rate) == 0) {
_last_temperature = read_reg(FXAS21002C_TEMP) * 1.0f;
gyro_report.temperature = _last_temperature;
}
/*
* 1) Scale raw value to SI units using scaling from datasheet.
* 2) Subtract static offset (in SI units)
* 3) Scale the statically calibrated values with a linear
* dynamically obtained factor
*
* Note: the static sensor offset is the number the sensor outputs
* at a nominally 'zero' input. Therefore the offset has to
* be subtracted.
*
* Example: A gyro outputs a value of 74 at zero angular rate
* the offset is 74 from the origin and subtracting
* 74 from all measurements centers them around zero.
*/
gyro_report.timestamp = hrt_absolute_time();
// report the error count as the number of bad
// register reads. This allows the higher level
// code to decide if it should use this sensor based on
// whether it has had failures
gyro_report.error_count = perf_event_count(_bad_registers);
gyro_report.x_raw = swap16(raw_gyro_report.x);
gyro_report.y_raw = swap16(raw_gyro_report.y);
gyro_report.z_raw = swap16(raw_gyro_report.z);
float xraw_f = gyro_report.x_raw;
float yraw_f = gyro_report.y_raw;
float zraw_f = gyro_report.z_raw;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
float x_in_new = ((xraw_f * _gyro_range_scale) - _gyro_scale.x_offset) * _gyro_scale.x_scale;
float y_in_new = ((yraw_f * _gyro_range_scale) - _gyro_scale.y_offset) * _gyro_scale.y_scale;
float z_in_new = ((zraw_f * _gyro_range_scale) - _gyro_scale.z_offset) * _gyro_scale.z_scale;
gyro_report.x = _gyro_filter_x.apply(x_in_new);
gyro_report.y = _gyro_filter_y.apply(y_in_new);
gyro_report.z = _gyro_filter_z.apply(z_in_new);
math::Vector<3> gval(x_in_new, y_in_new, z_in_new);
math::Vector<3> gval_integrated;
bool gyro_notify = _gyro_int.put(gyro_report.timestamp, gval, gval_integrated, gyro_report.integral_dt);
gyro_report.x_integral = gval_integrated(0);
gyro_report.y_integral = gval_integrated(1);
gyro_report.z_integral = gval_integrated(2);
gyro_report.scaling = _gyro_range_scale;
gyro_report.range_rad_s = _gyro_range_rad_s;
/* return device ID */
gyro_report.device_id = _device_id.devid;
_reports->force(&gyro_report);
/* notify anyone waiting for data */
if (gyro_notify) {
poll_notify(POLLIN);
if (!(_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(sensor_gyro), _gyro_topic, &gyro_report);
}
}
_read++;
/* stop the perf counter */
perf_end(_sample_perf);
}
int
AK8975::collect()
{
#pragma pack(push, 1)
struct { /* status register and data as read back from the device */
uint8_t x[2];
uint8_t y[2];
uint8_t z[2];
} ak8975_report;
#pragma pack(pop)
struct {
int16_t x, y, z;
} report;
int ret = -EIO;
uint8_t cmd;
perf_begin(_sample_perf);
struct mag_report new_report;
/* this should be fairly close to the end of the measurement, so the best approximation of the time */
new_report.timestamp = hrt_absolute_time();
new_report.error_count = perf_event_count(_comms_errors);
/*
* @note We could read the status register here, which could tell us that
* we were too early and that the output registers are still being
* written. In the common case that would just slow us down, and
* we're better off just never being early.
*/
/* check data ready bit */
if (read_reg(ADDR_DRDY, cmd)) {
perf_count(_comms_errors);
debug("data ready read error");
goto out;
}
if (!(cmd & STATUS_REG_DATA_READY)) {
/* data not ready */
perf_count(_comms_errors);
debug("data not ready [%02X]", cmd);
goto out;
}
/* get measurements from the device */
cmd = ADDR_DATA_OUT_X_LSB;
ret = transfer(&cmd, 1, (uint8_t *)&ak8975_report, sizeof(ak8975_report));
if (ret != OK) {
perf_count(_comms_errors);
debug("data/status read error");
goto out;
}
/* check for overflow and not ready error */
if (read_reg(ADDR_STATUS, cmd)) {
perf_count(_comms_errors);
debug("data status read error");
goto out;
}
if (cmd & (STATUS_REG_DATA_ERROR | STATUS_REG_HOFL)) {
/* data value error */
perf_count(_comms_errors);
debug("data value error");
goto out;
}
/* swap the data we just received */
report.x = (((int16_t)ak8975_report.x[1]) << 8) + ak8975_report.x[0];
report.y = (((int16_t)ak8975_report.y[1]) << 8) + ak8975_report.y[0];
report.z = (((int16_t)ak8975_report.z[1]) << 8) + ak8975_report.z[0];
/*
* If any of the values are -4096, there was an internal math error in the sensor.
* Generalise this to a simple range check that will also catch some bit errors.
*/
if ((abs(report.x) > 4096) ||
(abs(report.y) > 4096) ||
(abs(report.z) > 4096)) {
perf_count(_comms_errors);
goto out;
}
/*
* RAW outputs
*
* to align the sensor axes with the board, x and y need to be flipped
* and y needs to be negated
*/
new_report.x_raw = report.x;
new_report.y_raw = report.y;
/* z remains z */
new_report.z_raw = report.z;
/* scale values for output */
/*
* 1) Scale raw value to SI units using scaling from datasheet.
* 2) Subtract static offset (in SI units)
* 3) Scale the statically calibrated values with a linear
* dynamically obtained factor
*
* Note: the static sensor offset is the number the sensor outputs
* at a nominally 'zero' input. Therefore the offset has to
* be subtracted.
*
* Example: A gyro outputs a value of 74 at zero angular rate
* the offset is 74 from the origin and subtracting
* 74 from all measurements centers them around zero.
*/
/* the standard external mag by 3DR has x pointing to the right, y pointing backwards, and z down,
* therefore switch x and y and invert y */
//new_report.x = ((-report.y * _range_scale) - _scale.x_offset) * _scale.x_scale;
new_report.x = ((report.x * _scale.x_scale) - _scale.x_offset) * _range_scale;
/* flip axes and negate value for y */
//new_report.y = ((report.x * _range_scale) - _scale.y_offset) * _scale.y_scale;
new_report.y = ((report.y * _scale.y_scale) - _scale.y_offset) * _range_scale;
/* z remains z */
//new_report.z = ((report.z * _range_scale) - _scale.z_offset) * _scale.z_scale;
new_report.z = ((report.z * _scale.z_scale) - _scale.z_offset) * _range_scale;
/* publish it */
orb_publish(ORB_ID(sensor_mag), _mag_topic, &new_report);
/* post a report to the ring */
if (_reports->force(&new_report)) {
perf_count(_buffer_overflows);
}
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
out:
perf_end(_sample_perf);
return ret;
}
int
FixedwingEstimator::check_filter_state()
{
/*
* CHECK IF THE INPUT DATA IS SANE
*/
struct ekf_status_report ekf_report;
int check = _ekf->CheckAndBound(&ekf_report);
const char* ekfname = "att pos estimator: ";
switch (check) {
case 0:
/* all ok */
break;
case 1:
{
const char* str = "NaN in states, resetting";
warnx("%s", str);
mavlink_log_critical(_mavlink_fd, "%s%s", ekfname, str);
break;
}
case 2:
{
const char* str = "stale IMU data, resetting";
warnx("%s", str);
mavlink_log_critical(_mavlink_fd, "%s%s", ekfname, str);
break;
}
case 3:
{
const char* str = "switching to dynamic state";
warnx("%s", str);
mavlink_log_info(_mavlink_fd, "%s%s", ekfname, str);
break;
}
case 4:
{
const char* str = "excessive gyro offsets";
warnx("%s", str);
mavlink_log_info(_mavlink_fd, "%s%s", ekfname, str);
break;
}
case 5:
{
const char* str = "GPS velocity divergence";
warnx("%s", str);
mavlink_log_info(_mavlink_fd, "%s%s", ekfname, str);
break;
}
case 6:
{
const char* str = "excessive covariances";
warnx("%s", str);
mavlink_log_info(_mavlink_fd, "%s%s", ekfname, str);
break;
}
default:
{
const char* str = "unknown reset condition";
warnx("%s", str);
mavlink_log_critical(_mavlink_fd, "%s%s", ekfname, str);
}
}
struct estimator_status_report rep;
memset(&rep, 0, sizeof(rep));
// If error flag is set, we got a filter reset
if (check && ekf_report.error) {
// Count the reset condition
perf_count(_perf_reset);
} else if (_ekf_logging) {
_ekf->GetFilterState(&ekf_report);
}
if (_ekf_logging || check) {
rep.timestamp = hrt_absolute_time();
rep.nan_flags |= (((uint8_t)ekf_report.angNaN) << 0);
rep.nan_flags |= (((uint8_t)ekf_report.summedDelVelNaN) << 1);
rep.nan_flags |= (((uint8_t)ekf_report.KHNaN) << 2);
rep.nan_flags |= (((uint8_t)ekf_report.KHPNaN) << 3);
rep.nan_flags |= (((uint8_t)ekf_report.PNaN) << 4);
rep.nan_flags |= (((uint8_t)ekf_report.covarianceNaN) << 5);
rep.nan_flags |= (((uint8_t)ekf_report.kalmanGainsNaN) << 6);
rep.nan_flags |= (((uint8_t)ekf_report.statesNaN) << 7);
rep.health_flags |= (((uint8_t)ekf_report.velHealth) << 0);
rep.health_flags |= (((uint8_t)ekf_report.posHealth) << 1);
rep.health_flags |= (((uint8_t)ekf_report.hgtHealth) << 2);
rep.health_flags |= (((uint8_t)!ekf_report.gyroOffsetsExcessive) << 3);
rep.timeout_flags |= (((uint8_t)ekf_report.velTimeout) << 0);
rep.timeout_flags |= (((uint8_t)ekf_report.posTimeout) << 1);
rep.timeout_flags |= (((uint8_t)ekf_report.hgtTimeout) << 2);
rep.timeout_flags |= (((uint8_t)ekf_report.imuTimeout) << 3);
if (_debug > 10) {
if (rep.health_flags < ((1 << 0) | (1 << 1) | (1 << 2) | (1 << 3))) {
warnx("health: VEL:%s POS:%s HGT:%s OFFS:%s",
((rep.health_flags & (1 << 0)) ? "OK" : "ERR"),
((rep.health_flags & (1 << 1)) ? "OK" : "ERR"),
((rep.health_flags & (1 << 2)) ? "OK" : "ERR"),
((rep.health_flags & (1 << 3)) ? "OK" : "ERR"));
}
if (rep.timeout_flags) {
warnx("timeout: %s%s%s%s",
((rep.timeout_flags & (1 << 0)) ? "VEL " : ""),
((rep.timeout_flags & (1 << 1)) ? "POS " : ""),
((rep.timeout_flags & (1 << 2)) ? "HGT " : ""),
((rep.timeout_flags & (1 << 3)) ? "IMU " : ""));
}
}
// Copy all states or at least all that we can fit
unsigned ekf_n_states = ekf_report.n_states;
unsigned max_states = (sizeof(rep.states) / sizeof(rep.states[0]));
rep.n_states = (ekf_n_states < max_states) ? ekf_n_states : max_states;
for (unsigned i = 0; i < rep.n_states; i++) {
rep.states[i] = ekf_report.states[i];
}
for (unsigned i = 0; i < rep.n_states; i++) {
rep.states[i] = ekf_report.states[i];
}
if (_estimator_status_pub > 0) {
orb_publish(ORB_ID(estimator_status), _estimator_status_pub, &rep);
} else {
_estimator_status_pub = orb_advertise(ORB_ID(estimator_status), &rep);
}
}
return check;
}
int
HMC5883::collect()
{
#pragma pack(push, 1)
struct { /* status register and data as read back from the device */
uint8_t x[2];
uint8_t z[2];
uint8_t y[2];
} hmc_report;
#pragma pack(pop)
struct {
int16_t x, y, z;
} report;
int ret;
uint8_t cmd;
uint8_t check_counter;
perf_begin(_sample_perf);
struct mag_report new_report;
/* this should be fairly close to the end of the measurement, so the best approximation of the time */
new_report.timestamp = hrt_absolute_time();
new_report.error_count = perf_event_count(_comms_errors);
/*
* @note We could read the status register here, which could tell us that
* we were too early and that the output registers are still being
* written. In the common case that would just slow us down, and
* we're better off just never being early.
*/
/* get measurements from the device */
cmd = ADDR_DATA_OUT_X_MSB;
ret = transfer(&cmd, 1, (uint8_t *)&hmc_report, sizeof(hmc_report));
if (ret != OK) {
perf_count(_comms_errors);
debug("data/status read error");
goto out;
}
/* swap the data we just received */
report.x = (((int16_t)hmc_report.x[0]) << 8) + hmc_report.x[1];
report.y = (((int16_t)hmc_report.y[0]) << 8) + hmc_report.y[1];
report.z = (((int16_t)hmc_report.z[0]) << 8) + hmc_report.z[1];
/*
* If any of the values are -4096, there was an internal math error in the sensor.
* Generalise this to a simple range check that will also catch some bit errors.
*/
if ((abs(report.x) > 2048) ||
(abs(report.y) > 2048) ||
(abs(report.z) > 2048)) {
perf_count(_comms_errors);
goto out;
}
/*
* RAW outputs
*
* to align the sensor axes with the board, x and y need to be flipped
* and y needs to be negated
*/
new_report.x_raw = report.y;
new_report.y_raw = -report.x;
/* z remains z */
new_report.z_raw = report.z;
/* scale values for output */
#ifdef PX4_I2C_BUS_ONBOARD
if (_bus == PX4_I2C_BUS_ONBOARD) {
// convert onboard so it matches offboard for the
// scaling below
report.y = -report.y;
report.x = -report.x;
}
#endif
/* the standard external mag by 3DR has x pointing to the
* right, y pointing backwards, and z down, therefore switch x
* and y and invert y */
new_report.x = ((-report.y * _range_scale) - _scale.x_offset) * _scale.x_scale;
/* flip axes and negate value for y */
new_report.y = ((report.x * _range_scale) - _scale.y_offset) * _scale.y_scale;
/* z remains z */
new_report.z = ((report.z * _range_scale) - _scale.z_offset) * _scale.z_scale;
// apply user specified rotation
rotate_3f(_rotation, new_report.x, new_report.y, new_report.z);
if (!(_pub_blocked)) {
if (_mag_topic != -1) {
/* publish it */
orb_publish(_mag_orb_id, _mag_topic, &new_report);
} else {
_mag_topic = orb_advertise(_mag_orb_id, &new_report);
if (_mag_topic < 0)
debug("ADVERT FAIL");
}
}
_last_report = new_report;
/* post a report to the ring */
if (_reports->force(&new_report)) {
perf_count(_buffer_overflows);
}
/* notify anyone waiting for data */
poll_notify(POLLIN);
/*
periodically check the range register and configuration
registers. With a bad I2C cable it is possible for the
registers to become corrupt, leading to bad readings. It
doesn't happen often, but given the poor cables some
vehicles have it is worth checking for.
*/
check_counter = perf_event_count(_sample_perf) % 256;
if (check_counter == 0) {
check_range();
}
if (check_counter == 128) {
check_conf();
}
ret = OK;
out:
perf_end(_sample_perf);
return ret;
}
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 = 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 = _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
Gimbal::cycle()
{
if (!_initialized) {
/* get a subscription handle on the vehicle command topic */
_vehicle_command_sub = orb_subscribe(ORB_ID(vehicle_command));
/* get a publication handle on actuator output topic */
struct actuator_controls_s zero_report;
memset(&zero_report, 0, sizeof(zero_report));
zero_report.timestamp = hrt_absolute_time();
_actuator_controls_2_topic = orb_advertise(ORB_ID(actuator_controls_2), &zero_report);
if (_actuator_controls_2_topic == nullptr) {
warnx("advert err");
}
_initialized = true;
}
bool updated = false;
perf_begin(_sample_perf);
float roll = 0.0f;
float pitch = 0.0f;
float yaw = 0.0f;
if (_att_sub < 0) {
_att_sub = orb_subscribe(ORB_ID(vehicle_attitude));
}
vehicle_attitude_s att;
orb_copy(ORB_ID(vehicle_attitude), _att_sub, &att);
if (_attitude_compensation_roll) {
roll = 1.0f / M_PI_F * -att.roll;
updated = true;
}
if (_attitude_compensation_pitch) {
pitch = 1.0f / M_PI_F * -att.pitch;
updated = true;
}
if (_attitude_compensation_yaw) {
yaw = 1.0f / M_PI_F * att.yaw;
updated = true;
}
struct vehicle_command_s cmd;
bool cmd_updated;
orb_check(_vehicle_command_sub, &cmd_updated);
if (cmd_updated) {
orb_copy(ORB_ID(vehicle_command), _vehicle_command_sub, &cmd);
if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_MOUNT_CONTROL
|| cmd.command == vehicle_command_s::VEHICLE_CMD_DO_MOUNT_CONTROL_QUAT) {
_control_cmd = cmd;
_control_cmd_set = true;
} else if (cmd.command == vehicle_command_s::VEHICLE_CMD_DO_MOUNT_CONFIGURE) {
_config_cmd = cmd;
_config_cmd_set = true;
}
}
if (_config_cmd_set) {
_config_cmd_set = false;
_attitude_compensation_roll = (int)_config_cmd.param2 == 1;
_attitude_compensation_pitch = (int)_config_cmd.param3 == 1;
_attitude_compensation_yaw = (int)_config_cmd.param4 == 1;
}
if (_control_cmd_set) {
unsigned mountMode = _control_cmd.param7;
DEVICE_DEBUG("control_cmd: %d, mountMode %d | param1: %8.4f param2: %8.4f", _control_cmd.command, mountMode, (double)_control_cmd.param1, (double)_control_cmd.param2);
if (_control_cmd.command == vehicle_command_s::VEHICLE_CMD_DO_MOUNT_CONTROL &&
mountMode == vehicle_command_s::VEHICLE_MOUNT_MODE_MAVLINK_TARGETING) {
/* Convert to range -1 ... 1, which corresponds to -180deg ... 180deg */
roll += 1.0f / M_PI_F * M_DEG_TO_RAD_F * _control_cmd.param1;
pitch += 1.0f / M_PI_F * M_DEG_TO_RAD_F * _control_cmd.param2;
yaw += 1.0f / M_PI_F * M_DEG_TO_RAD_F * _control_cmd.param3;
updated = true;
}
if (_control_cmd.command == vehicle_command_s::VEHICLE_CMD_DO_MOUNT_CONTROL_QUAT &&
mountMode == vehicle_command_s::VEHICLE_MOUNT_MODE_MAVLINK_TARGETING) {
float gimbalDirectionQuat[] = {_control_cmd.param1, _control_cmd.param2, _control_cmd.param3, _control_cmd.param4};
math::Vector<3> gimablDirectionEuler = math::Quaternion(gimbalDirectionQuat).to_dcm().to_euler();
roll += gimablDirectionEuler(0);
pitch += gimablDirectionEuler(1);
yaw += gimablDirectionEuler(2);
updated = true;
}
}
if (updated) {
struct actuator_controls_s controls;
// DEVICE_DEBUG("publishing | roll: %8.4f pitch: %8.4f yaw: %8.4f", (double)roll, (double)pitch, (double)yaw);
/* fill in the final control values */
controls.timestamp = hrt_absolute_time();
controls.control[0] = roll;
controls.control[1] = pitch;
controls.control[2] = yaw;
/* publish it */
orb_publish(ORB_ID(actuator_controls_2), _actuator_controls_2_topic, &controls);
}
/* notify anyone waiting for data */
poll_notify(POLLIN);
perf_end(_sample_perf);
/* schedule a fresh cycle call when the measurement is done */
work_queue(LPWORK,
&_work,
(worker_t)&Gimbal::cycle_trampoline,
this,
USEC2TICK(GIMBAL_UPDATE_INTERVAL));
}
int
MEASAirspeed::collect()
{
int ret = -EIO;
/* read from the sensor */
uint8_t val[4] = {0, 0, 0, 0};
perf_begin(_sample_perf);
ret = transfer(nullptr, 0, &val[0], 4);
if (ret < 0) {
perf_count(_comms_errors);
perf_end(_sample_perf);
return ret;
}
uint8_t status = val[0] & 0xC0;
if (status == 2) {
log("err: stale data");
perf_count(_comms_errors);
perf_end(_sample_perf);
return ret;
} else if (status == 3) {
log("err: fault");
perf_count(_comms_errors);
perf_end(_sample_perf);
return ret;
}
//uint16_t diff_pres_pa = (val[1]) | ((val[0] & ~(0xC0)) << 8);
uint16_t temp = (val[3] & 0xE0) << 8 | val[2];
// XXX leaving this in until new calculation method has been cross-checked
//diff_pres_pa = abs(diff_pres_pa - (16384 / 2.0f));
//diff_pres_pa -= _diff_pres_offset;
int16_t dp_raw = 0, dT_raw = 0;
dp_raw = (val[0] << 8) + val[1];
dp_raw = 0x3FFF & dp_raw; //mask the used bits
dT_raw = (val[2] << 8) + val[3];
dT_raw = (0xFFE0 & dT_raw) >> 5;
float temperature = ((200 * dT_raw) / 2047) - 50;
// XXX we may want to smooth out the readings to remove noise.
// Calculate differential pressure. As its centered around 8000
// and can go positive or negative, enforce absolute value
// uint16_t diff_press_pa = abs(dp_raw - (16384 / 2.0f));
const float P_min = -1.0f;
const float P_max = 1.0f;
float diff_press_pa = math::max(0.0f, fabsf( ( ((float)dp_raw - 0.1f*16383.0f) * (P_max-P_min)/(0.8f*16383.0f) + P_min) * 6894.8f) - _diff_pres_offset);
struct differential_pressure_s report;
// Track maximum differential pressure measured (so we can work out top speed).
if (diff_press_pa > _max_differential_pressure_pa) {
_max_differential_pressure_pa = diff_press_pa;
}
report.timestamp = hrt_absolute_time();
report.error_count = perf_event_count(_comms_errors);
report.temperature = temperature;
report.differential_pressure_pa = diff_press_pa;
report.voltage = 0;
report.max_differential_pressure_pa = _max_differential_pressure_pa;
/* announce the airspeed if needed, just publish else */
orb_publish(ORB_ID(differential_pressure), _airspeed_pub, &report);
new_report(report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
void
L3G4200D::measure()
{
#if L3G4200D_USE_DRDY
// if the gyro doesn't have any data ready then re-schedule
// for 100 microseconds later. This ensures we don't double
// read a value and then miss the next value
if (stm32_gpioread(GPIO_EXTI_GYRO_DRDY) == 0) {
perf_count(_reschedules);
hrt_call_delay(&_call, 100);
return;
}
#endif
/* status register and data as read back from the device */
#pragma pack(push, 1)
struct {
uint8_t cmd;
uint8_t temp;
uint8_t status;
int16_t x;
int16_t y;
int16_t z;
} raw_report;
#pragma pack(pop)
gyro_report report;
/* start the performance counter */
perf_begin(_sample_perf);
/* fetch data from the sensor */
memset(&raw_report, 0, sizeof(raw_report));
raw_report.cmd = ADDR_OUT_TEMP | DIR_READ | ADDR_INCREMENT;
transfer((uint8_t *)&raw_report, (uint8_t *)&raw_report, sizeof(raw_report));
#if L3G4200D_USE_DRDY
if ((raw_report.status & 0xF) != 0xF) {
/*
we waited for DRDY, but did not see DRDY on all axes
when we captured. That means a transfer error of some sort
*/
perf_count(_errors);
return;
}
#endif
/*
* 1) Scale raw value to SI units using scaling from datasheet.
* 2) Subtract static offset (in SI units)
* 3) Scale the statically calibrated values with a linear
* dynamically obtained factor
*
* Note: the static sensor offset is the number the sensor outputs
* at a nominally 'zero' input. Therefore the offset has to
* be subtracted.
*
* Example: A gyro outputs a value of 74 at zero angular rate
* the offset is 74 from the origin and subtracting
* 74 from all measurements centers them around zero.
*/
report.timestamp = hrt_absolute_time();
report.error_count = 0; // not recorded
switch (_orientation) {
case SENSOR_BOARD_ROTATION_000_DEG:
/* keep axes in place */
report.x_raw = raw_report.x;
report.y_raw = raw_report.y;
break;
case SENSOR_BOARD_ROTATION_090_DEG:
/* swap x and y */
report.x_raw = raw_report.y;
report.y_raw = raw_report.x;
break;
case SENSOR_BOARD_ROTATION_180_DEG:
/* swap x and y and negate both */
/* since sensor is mounted on top, need to rotate and then negate y, z */
report.x_raw = ((raw_report.x == -32768) ? 32767 : -raw_report.x);
// report.y_raw = ((raw_report.y == -32768) ? 32767 : -raw_report.y); /* leave as is, 180 rotate + negate */
report.y_raw = raw_report.y;
report.z_raw = ((raw_report.z == -32768) ? 32767 : -raw_report.z);
break;
case SENSOR_BOARD_ROTATION_270_DEG:
/* swap x and y and negate y */
report.x_raw = raw_report.y;
report.y_raw = ((raw_report.x == -32768) ? 32767 : -raw_report.x);
break;
}
// report.z_raw = raw_report.z;
report.x = ((report.x_raw * _gyro_range_scale) - _gyro_scale.x_offset) * _gyro_scale.x_scale;
report.y = ((report.y_raw * _gyro_range_scale) - _gyro_scale.y_offset) * _gyro_scale.y_scale;
report.z = ((report.z_raw * _gyro_range_scale) - _gyro_scale.z_offset) * _gyro_scale.z_scale;
report.x = _gyro_filter_x.apply(report.x);
report.y = _gyro_filter_y.apply(report.y);
report.z = _gyro_filter_z.apply(report.z);
report.scaling = _gyro_range_scale;
report.range_rad_s = _gyro_range_rad_s;
_reports->force(&report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
/* publish for subscribers */
if (_gyro_topic > 0)
orb_publish(ORB_ID(sensor_gyro), _gyro_topic, &report);
_read++;
/* stop the perf counter */
perf_end(_sample_perf);
}
int
LIS3MDL::collect()
{
#pragma pack(push, 1)
struct { /* status register and data as read back from the device */
uint8_t x[2];
uint8_t y[2];
uint8_t z[2];
uint8_t t[2];
} lis_report;
struct {
int16_t x;
int16_t y;
int16_t z;
int16_t t;
} report;
#pragma pack(pop)
int ret;
// uint8_t check_counter;
perf_begin(_sample_perf);
struct mag_report new_report;
bool sensor_is_onboard = false;
float xraw_f;
float yraw_f;
float zraw_f;
/* this should be fairly close to the end of the measurement, so the best approximation of the time */
new_report.timestamp = hrt_absolute_time();
new_report.error_count = perf_event_count(_comms_errors);
/*
* @note We could read the status register here, which could tell us that
* we were too early and that the output registers are still being
* written. In the common case that would just slow us down, and
* we're better off just never being early.
*/
/* get measurements from the device */
ret = _interface->read(ADDR_OUT_X_L, (uint8_t *)&lis_report, sizeof(lis_report));
if (ret != OK) {
perf_count(_comms_errors);
DEVICE_DEBUG("data/status read error");
goto out;
}
/* convert the data we just received */
report.x = (((int16_t)lis_report.x[1]) << 8) + lis_report.x[0];
report.y = (((int16_t)lis_report.y[1]) << 8) + lis_report.y[0];
report.z = (((int16_t)lis_report.z[1]) << 8) + lis_report.z[0];
report.t = (((int16_t)lis_report.t[1]) << 8) + lis_report.t[0];
/* get measurements from the device */
new_report.temperature = report.t;
new_report.temperature = 25 + (report.t / (16 * 8.0f));
// XXX revisit for SPI part, might require a bus type IOCTL
unsigned dummy;
sensor_is_onboard = !_interface->ioctl(MAGIOCGEXTERNAL, dummy);
/*
* RAW outputs
*
*/
new_report.x_raw = report.x;
new_report.y_raw = report.y;
new_report.z_raw = report.z;
/* the LIS3MDL mag on Pixhawk Pro by Drotek has x pointing towards,
* y pointing to the right, and z down, therefore no switch needed,
* it is better to have no artificial rotation inside the
* driver and then use the startup script with -R command with the
* real rotation between the sensor and body frame */
xraw_f = report.x;
yraw_f = report.y;
zraw_f = report.z;
// apply user specified rotation
rotate_3f(_rotation, xraw_f, yraw_f, zraw_f);
new_report.x = ((xraw_f * _range_scale) - _scale.x_offset) * _scale.x_scale;
/* flip axes and negate value for y */
new_report.y = ((yraw_f * _range_scale) - _scale.y_offset) * _scale.y_scale;
/* z remains z */
new_report.z = ((zraw_f * _range_scale) - _scale.z_offset) * _scale.z_scale;
if (!(_pub_blocked)) {
if (_mag_topic != nullptr) {
/* publish it */
orb_publish(ORB_ID(sensor_mag), _mag_topic, &new_report);
} else {
_mag_topic = orb_advertise_multi(ORB_ID(sensor_mag), &new_report,
&_orb_class_instance, (sensor_is_onboard) ? ORB_PRIO_HIGH : ORB_PRIO_MAX);
if (_mag_topic == nullptr) {
DEVICE_DEBUG("ADVERT FAIL");
}
}
}
_last_report = new_report;
/* post a report to the ring */
if (_reports->force(&new_report)) {
perf_count(_buffer_overflows);
}
/* notify anyone waiting for data */
poll_notify(POLLIN);
check_conf();
ret = OK;
out:
perf_end(_sample_perf);
return ret;
}
void UavcanServers::cb_getset(const uavcan::ServiceCallResult<uavcan::protocol::param::GetSet> &result)
{
if (_count_in_progress) {
/*
* Currently in parameter count mode:
* Iterate over all parameters for the node to which the request was
* originally sent, in order to find the maximum parameter ID. If a
* request fails, set the node's parameter count to zero.
*/
uint8_t node_id = result.getCallID().server_node_id.get();
if (result.isSuccessful()) {
uavcan::protocol::param::GetSet::Response resp = result.getResponse();
if (resp.name.size()) {
_count_index++;
_param_counts[node_id] = _count_index;
uavcan::protocol::param::GetSet::Request req;
req.index = _count_index;
int call_res = _param_getset_client.call(result.getCallID().server_node_id, req);
if (call_res < 0) {
_count_in_progress = false;
_count_index = 0;
warnx("UAVCAN command bridge: couldn't send GetSet during param count: %d", call_res);
}
} else {
_count_in_progress = false;
_count_index = 0;
warnx("UAVCAN command bridge: completed param count for node %hhu: %hhu", node_id, _param_counts[node_id]);
}
} else {
_param_counts[node_id] = 0;
_count_in_progress = false;
_count_index = 0;
warnx("UAVCAN command bridge: GetSet error during param count");
}
} else {
/*
* Currently in parameter get/set mode:
* Publish a uORB uavcan_parameter_value message containing the current value
* of the parameter.
*/
if (result.isSuccessful()) {
uavcan::protocol::param::GetSet::Response param = result.getResponse();
struct uavcan_parameter_value_s response;
response.node_id = result.getCallID().server_node_id.get();
strncpy(response.param_id, param.name.c_str(), sizeof(response.param_id) - 1);
response.param_id[16] = '\0';
response.param_index = _param_index;
response.param_count = _param_counts[response.node_id];
if (param.value.is(uavcan::protocol::param::Value::Tag::integer_value)) {
response.param_type = MAV_PARAM_TYPE_INT64;
response.int_value = param.value.to<uavcan::protocol::param::Value::Tag::integer_value>();
} else if (param.value.is(uavcan::protocol::param::Value::Tag::real_value)) {
response.param_type = MAV_PARAM_TYPE_REAL32;
response.real_value = param.value.to<uavcan::protocol::param::Value::Tag::real_value>();
} else if (param.value.is(uavcan::protocol::param::Value::Tag::boolean_value)) {
response.param_type = MAV_PARAM_TYPE_UINT8;
response.int_value = param.value.to<uavcan::protocol::param::Value::Tag::boolean_value>();
}
if (_param_response_pub == nullptr) {
_param_response_pub = orb_advertise(ORB_ID(uavcan_parameter_value), &response);
} else {
orb_publish(ORB_ID(uavcan_parameter_value), _param_response_pub, &response);
}
} else {
warnx("UAVCAN command bridge: GetSet error");
}
_param_in_progress = false;
_param_index++;
}
}
void *nmea_loop(void *args)
{
/* Set thread name */
prctl(PR_SET_NAME, "gps nmea read", getpid());
/* Retrieve file descriptor and thread flag */
struct arg_struct *arguments = (struct arg_struct *)args;
int *fd = arguments->fd_ptr;
bool *thread_should_exit = arguments->thread_should_exit_ptr;
/* Initialize gps stuff */
nmeaINFO info_d;
nmeaINFO *info = &info_d;
char gps_rx_buffer[NMEA_BUFFER_SIZE];
/* gps parser (nmea) */
nmeaPARSER parser;
nmea_parser_init(&parser);
nmea_zero_INFO(info);
/* advertise GPS topic */
struct vehicle_gps_position_s nmea_gps_d = {.counter=0};
nmea_gps = &nmea_gps_d;
orb_advert_t gps_handle = orb_advertise(ORB_ID(vehicle_gps_position), nmea_gps);
while (!(*thread_should_exit)) {
/* Parse a message from the gps receiver */
uint8_t read_res = read_gps_nmea(fd, gps_rx_buffer, NMEA_BUFFER_SIZE, info, &parser);
if (0 == read_res) {
/* convert data, ready it for publishing */
/* convert nmea utc time to usec */
struct tm timeinfo;
timeinfo.tm_year = info->utc.year;
timeinfo.tm_mon = info->utc.mon;
timeinfo.tm_mday = info->utc.day;
timeinfo.tm_hour = info->utc.hour;
timeinfo.tm_min = info->utc.min;
timeinfo.tm_sec = info->utc.sec;
time_t epoch = mktime(&timeinfo);
// printf("%d.%d.%d %d:%d:%d:%d\n", timeinfo.tm_year, timeinfo.tm_mon, timeinfo.tm_mday, timeinfo.tm_hour, timeinfo.tm_min, timeinfo.tm_sec, info->utc.hsec);
nmea_gps->timestamp = hrt_absolute_time();
nmea_gps->time_gps_usec = (uint64_t)((epoch)*1000000 + (info->utc.hsec)*10000);
nmea_gps->fix_type = (uint8_t)info->fix;
nmea_gps->lat = (int32_t)(ndeg2degree(info->lat) * 1e7f);
nmea_gps->lon = (int32_t)(ndeg2degree(info->lon) * 1e7f);
nmea_gps->alt = (int32_t)(info->elv * 1000.0f);
nmea_gps->eph = (uint16_t)(info->HDOP * 100); //TODO:test scaling
nmea_gps->epv = (uint16_t)(info->VDOP * 100); //TODO:test scaling
nmea_gps->vel = (uint16_t)(info->speed * 1000 / 36); //*1000/3600*100
nmea_gps->cog = (uint16_t)info->direction*100; //nmea: degrees float, ubx/mavlink: degrees*1e2
nmea_gps->satellites_visible = (uint8_t)info->satinfo.inview;
int i = 0;
/* Write info about individual satellites */
for (i = 0; i < 12; i++) {
nmea_gps->satellite_prn[i] = (uint8_t)info->satinfo.sat[i].id;
nmea_gps->satellite_used[i] = (uint8_t)info->satinfo.sat[i].in_use;
nmea_gps->satellite_elevation[i] = (uint8_t)info->satinfo.sat[i].elv;
nmea_gps->satellite_azimuth[i] = (uint8_t)info->satinfo.sat[i].azimuth;
nmea_gps->satellite_snr[i] = (uint8_t)info->satinfo.sat[i].sig;
}
if (nmea_gps->satellites_visible > 0) {
nmea_gps->satellite_info_available = 1;
} else {
nmea_gps->satellite_info_available = 0;
}
nmea_gps->counter_pos_valid++;
nmea_gps->timestamp = hrt_absolute_time();
nmea_gps->counter++;
pthread_mutex_lock(nmea_mutex);
nmea_state->last_message_timestamp = hrt_absolute_time();
pthread_mutex_unlock(nmea_mutex);
/* publish new GPS position */
orb_publish(ORB_ID(vehicle_gps_position), gps_handle, nmea_gps);
} else if (read_res == 2) { //termination
/* de-advertise */
close(gps_handle);
break;
}
}
//destroy gps parser
nmea_parser_destroy(&parser);
if(gps_verbose) printf("[gps] nmea loop is going to terminate\n");
return NULL;
}
void *nmea_watchdog_loop(void *args)
{
/* Set thread name */
prctl(PR_SET_NAME, "gps nmea watchdog", getpid());
bool nmea_healthy = false;
uint8_t nmea_fail_count = 0;
uint8_t nmea_success_count = 0;
bool once_ok = false;
/* Retrieve file descriptor and thread flag */
struct arg_struct *arguments = (struct arg_struct *)args;
//int *fd = arguments->fd_ptr;
bool *thread_should_exit = arguments->thread_should_exit_ptr;
int mavlink_fd = open(MAVLINK_LOG_DEVICE, 0);
while (!(*thread_should_exit)) {
// printf("nmea_watchdog_loop : while ");
/* if we have no update for a long time print warning (in nmea mode there is no reconfigure) */
pthread_mutex_lock(nmea_mutex);
uint64_t timestamp_now = hrt_absolute_time();
bool all_okay = true;
if (timestamp_now - nmea_state->last_message_timestamp > NMEA_WATCHDOG_CRITICAL_TIME_MICROSECONDS) {
all_okay = false;
}
pthread_mutex_unlock(nmea_mutex);
if (!all_okay) {
/* gps error */
nmea_fail_count++;
// printf("nmea error, nmea_fail_count=%u\n", nmea_fail_count);
// fflush(stdout);
/* If we have too many failures and another mode or baud should be tried, exit... */
if ((gps_mode_try_all == true || gps_baud_try_all == true) && (nmea_fail_count >= NMEA_HEALTH_FAIL_COUNTER_LIMIT) && (nmea_healthy == false) && once_ok == false) {
if (gps_verbose) printf("\t[gps] no NMEA module found\n");
gps_mode_success = false;
break;
}
if (nmea_healthy && nmea_fail_count >= NMEA_HEALTH_FAIL_COUNTER_LIMIT) {
printf("\t[gps] ERROR: NMEA GPS module stopped responding\n");
// global_data_send_subsystem_info(&nmea_present_enabled);
mavlink_log_critical(mavlink_fd, "[gps] NMEA module stopped responding\n");
nmea_healthy = false;
nmea_success_count = 0;
}
fflush(stdout);
sleep(1);
} else {
/* gps healthy */
// printf("\t[gps] nmea success\n");
nmea_success_count++;
if (!nmea_healthy && nmea_success_count >= NMEA_HEALTH_SUCCESS_COUNTER_LIMIT) {
printf("[gps] NMEA module found, status ok (baud=%d)\r\n", current_gps_speed);
// global_data_send_subsystem_info(&nmea_present_enabled_healthy);
mavlink_log_info(mavlink_fd, "[gps] NMEA module found, status ok\n");
nmea_healthy = true;
nmea_fail_count = 0;
once_ok = true;
}
}
usleep(NMEA_WATCHDOG_WAIT_TIME_MICROSECONDS);
}
if(gps_verbose) printf("[gps] nmea watchdog loop is going to terminate\n");
close(mavlink_fd);
return NULL;
}
int
TFMINI::collect()
{
perf_begin(_sample_perf);
/* clear buffer if last read was too long ago */
int64_t read_elapsed = hrt_elapsed_time(&_last_read);
/* the buffer for read chars is buflen minus null termination */
char readbuf[sizeof(_linebuf)];
unsigned readlen = sizeof(readbuf) - 1;
int ret = 0;
float distance_m = -1.0f;
/* Check the number of bytes available in the buffer*/
int bytes_available = 0;
::ioctl(_fd, FIONREAD, (unsigned long)&bytes_available);
if (!bytes_available) {
return -EAGAIN;
}
/* parse entire buffer */
do {
/* read from the sensor (uart buffer) */
ret = ::read(_fd, &readbuf[0], readlen);
if (ret < 0) {
PX4_ERR("read err: %d", ret);
perf_count(_comms_errors);
perf_end(_sample_perf);
/* only throw an error if we time out */
if (read_elapsed > (_conversion_interval * 2)) {
/* flush anything in RX buffer */
tcflush(_fd, TCIFLUSH);
return ret;
} else {
return -EAGAIN;
}
}
_last_read = hrt_absolute_time();
/* parse buffer */
for (int i = 0; i < ret; i++) {
tfmini_parse(readbuf[i], _linebuf, &_linebuf_index, &_parse_state, &distance_m);
}
/* bytes left to parse */
bytes_available -= ret;
} while (bytes_available > 0);
/* no valid measurement after parsing buffer */
if (distance_m < 0.0f) {
return -EAGAIN;
}
/* publish most recent valid measurement from buffer */
distance_sensor_s report{};
report.timestamp = hrt_absolute_time();
report.type = distance_sensor_s::MAV_DISTANCE_SENSOR_LASER;
report.orientation = _rotation;
report.current_distance = distance_m;
report.min_distance = get_minimum_distance();
report.max_distance = get_maximum_distance();
report.covariance = 0.0f;
report.signal_quality = -1;
/* TODO: set proper ID */
report.id = 0;
/* publish it */
orb_publish(ORB_ID(distance_sensor), _distance_sensor_topic, &report);
_reports->force(&report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
int
MEASAirspeed::collect()
{
int ret = -EIO;
/* read from the sensor */
uint8_t val[4] = {0, 0, 0, 0};
perf_begin(_sample_perf);
ret = transfer(nullptr, 0, &val[0], 4);
if (ret < 0) {
perf_count(_comms_errors);
perf_end(_sample_perf);
return ret;
}
uint8_t status = (val[0] & 0xC0) >> 6;
switch (status) {
case 0:
break;
case 1:
/* fallthrough */
case 2:
/* fallthrough */
case 3:
perf_count(_comms_errors);
perf_end(_sample_perf);
return -EAGAIN;
}
int16_t dp_raw = 0, dT_raw = 0;
dp_raw = (val[0] << 8) + val[1];
/* mask the used bits */
dp_raw = 0x3FFF & dp_raw;
dT_raw = (val[2] << 8) + val[3];
dT_raw = (0xFFE0 & dT_raw) >> 5;
float temperature = ((200.0f * dT_raw) / 2047) - 50;
// Calculate differential pressure. As its centered around 8000
// and can go positive or negative
const float P_min = -1.0f;
const float P_max = 1.0f;
const float PSI_to_Pa = 6894.757f;
/*
this equation is an inversion of the equation in the
pressure transfer function figure on page 4 of the datasheet
We negate the result so that positive differential pressures
are generated when the bottom port is used as the static
port on the pitot and top port is used as the dynamic port
*/
float diff_press_PSI = -((dp_raw - 0.1f*16383) * (P_max-P_min)/(0.8f*16383) + P_min);
float diff_press_pa_raw = diff_press_PSI * PSI_to_Pa;
// correct for 5V rail voltage if possible
voltage_correction(diff_press_pa_raw, temperature);
// the raw value still should be compensated for the known offset
diff_press_pa_raw -= _diff_pres_offset;
/*
With the above calculation the MS4525 sensor will produce a
positive number when the top port is used as a dynamic port
and bottom port is used as the static port
*/
struct differential_pressure_s report;
/* track maximum differential pressure measured (so we can work out top speed). */
if (diff_press_pa_raw > _max_differential_pressure_pa) {
_max_differential_pressure_pa = diff_press_pa_raw;
}
report.timestamp = hrt_absolute_time();
report.error_count = perf_event_count(_comms_errors);
report.temperature = temperature;
report.differential_pressure_filtered_pa = _filter.apply(diff_press_pa_raw);
report.differential_pressure_raw_pa = diff_press_pa_raw;
report.max_differential_pressure_pa = _max_differential_pressure_pa;
if (_airspeed_pub > 0 && !(_pub_blocked)) {
/* publish it */
orb_publish(ORB_ID(differential_pressure), _airspeed_pub, &report);
}
new_report(report);
/* notify anyone waiting for data */
poll_notify(POLLIN);
ret = OK;
perf_end(_sample_perf);
return ret;
}
void
ADC::update_system_power(hrt_abstime now)
{
#if defined (BOARD_ADC_USB_CONNECTED)
system_power_s system_power = {};
system_power.timestamp = now;
system_power.voltage5v_v = 0;
system_power.voltage3v3_v = 0;
system_power.v3v3_valid = 0;
/* Assume HW provides only ADC_SCALED_V5_SENSE */
int cnt = 1;
/* HW provides both ADC_SCALED_V5_SENSE and ADC_SCALED_V3V3_SENSORS_SENSE */
# if defined(ADC_SCALED_V5_SENSE) && defined(ADC_SCALED_V3V3_SENSORS_SENSE)
cnt++;
# endif
for (unsigned i = 0; i < _channel_count; i++) {
# if defined(ADC_SCALED_V5_SENSE)
if (_samples[i].am_channel == ADC_SCALED_V5_SENSE) {
// it is 2:1 scaled
system_power.voltage5v_v = _samples[i].am_data * (ADC_V5_V_FULL_SCALE / 4096.0f);
cnt--;
} else
# endif
# if defined(ADC_SCALED_V3V3_SENSORS_SENSE)
{
if (_samples[i].am_channel == ADC_SCALED_V3V3_SENSORS_SENSE) {
// it is 2:1 scaled
system_power.voltage3v3_v = _samples[i].am_data * (ADC_3V3_SCALE * (3.3f / 4096.0f));
system_power.v3v3_valid = 1;
cnt--;
}
}
# endif
if (cnt == 0) {
break;
}
}
/* Note once the board_config.h provides BOARD_ADC_USB_CONNECTED,
* It must provide the true logic GPIO BOARD_ADC_xxxx macros.
*/
// these are not ADC related, but it is convenient to
// publish these to the same topic
system_power.usb_connected = BOARD_ADC_USB_CONNECTED;
/* If provided used the Valid signal from HW*/
#if defined(BOARD_ADC_USB_VALID)
system_power.usb_valid = BOARD_ADC_USB_VALID;
#else
/* If not provided then use connected */
system_power.usb_valid = system_power.usb_connected;
#endif
/* The valid signals (HW dependent) are associated with each brick */
bool valid_chan[BOARD_NUMBER_BRICKS] = BOARD_BRICK_VALID_LIST;
system_power.brick_valid = 0;
for (int b = 0; b < BOARD_NUMBER_BRICKS; b++) {
system_power.brick_valid |= valid_chan[b] ? 1 << b : 0;
}
system_power.servo_valid = BOARD_ADC_SERVO_VALID;
// OC pins are active low
system_power.periph_5v_oc = BOARD_ADC_PERIPH_5V_OC;
system_power.hipower_5v_oc = BOARD_ADC_HIPOWER_5V_OC;
/* lazily publish */
if (_to_system_power != nullptr) {
orb_publish(ORB_ID(system_power), _to_system_power, &system_power);
} else {
_to_system_power = orb_advertise(ORB_ID(system_power), &system_power);
}
#endif // BOARD_ADC_USB_CONNECTED
}
