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|
/****************************************************************************
*
* Copyright (c) 2013, 2014 PX4 Development Team. All rights reserved.
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/**
* @file fw_att_pos_estimator_main.cpp
* Implementation of the attitude and position estimator.
*
* @author Paul Riseborough <p_riseborough@live.com.au>
* @author Lorenz Meier <lm@inf.ethz.ch>
*/
#include <nuttx/config.h>
#include <stdio.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <fcntl.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <time.h>
#include <drivers/drv_hrt.h>
#define SENSOR_COMBINED_SUB
#include <drivers/drv_gyro.h>
#include <drivers/drv_accel.h>
#include <drivers/drv_mag.h>
#include <drivers/drv_baro.h>
#ifdef SENSOR_COMBINED_SUB
#include <uORB/topics/sensor_combined.h>
#endif
#include <arch/board/board.h>
#include <uORB/uORB.h>
#include <uORB/topics/airspeed.h>
#include <uORB/topics/vehicle_global_position.h>
#include <uORB/topics/vehicle_local_position.h>
#include <uORB/topics/vehicle_gps_position.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/vehicle_status.h>
#include <uORB/topics/parameter_update.h>
#include <systemlib/param/param.h>
#include <systemlib/err.h>
#include <geo/geo.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
#include <mathlib/mathlib.h>
#include "estimator.h"
/**
* estimator app start / stop handling function
*
* @ingroup apps
*/
extern "C" __EXPORT int fw_att_pos_estimator_main(int argc, char *argv[]);
__EXPORT uint32_t millis();
static uint64_t last_run = 0;
static uint64_t IMUmsec = 0;
uint32_t millis()
{
return IMUmsec;
}
static void print_status();
class FixedwingEstimator
{
public:
/**
* Constructor
*/
FixedwingEstimator();
/**
* Destructor, also kills the sensors task.
*/
~FixedwingEstimator();
/**
* Start the sensors task.
*
* @return OK on success.
*/
int start();
private:
bool _task_should_exit; /**< if true, sensor task should exit */
int _estimator_task; /**< task handle for sensor task */
#ifndef SENSOR_COMBINED_SUB
int _gyro_sub; /**< gyro sensor subscription */
int _accel_sub; /**< accel sensor subscription */
int _mag_sub; /**< mag sensor subscription */
#else
int _sensor_combined_sub;
#endif
int _airspeed_sub; /**< airspeed subscription */
int _baro_sub; /**< barometer subscription */
int _gps_sub; /**< GPS subscription */
int _vstatus_sub; /**< vehicle status subscription */
int _params_sub; /**< notification of parameter updates */
int _manual_control_sub; /**< notification of manual control updates */
int _mission_sub;
orb_advert_t _att_pub; /**< vehicle attitude */
orb_advert_t _global_pos_pub; /**< global position */
orb_advert_t _local_pos_pub; /**< position in local frame */
struct vehicle_attitude_s _att; /**< vehicle attitude */
struct gyro_report _gyro;
struct accel_report _accel;
struct mag_report _mag;
struct airspeed_s _airspeed; /**< airspeed */
struct baro_report _baro; /**< baro readings */
struct vehicle_status_s _vstatus; /**< vehicle status */
struct vehicle_global_position_s _global_pos; /**< global vehicle position */
struct vehicle_local_position_s _local_pos; /**< local vehicle position */
struct vehicle_gps_position_s _gps; /**< GPS position */
struct gyro_scale _gyro_offsets;
struct accel_scale _accel_offsets;
struct mag_scale _mag_offsets;
#ifdef SENSOR_COMBINED_SUB
struct sensor_combined_s _sensor_combined;
#endif
perf_counter_t _loop_perf; /**< loop performance counter */
perf_counter_t _perf_gyro; ///<local performance counter for gyro updates
perf_counter_t _perf_accel; ///<local performance counter for accel updates
perf_counter_t _perf_mag; ///<local performance counter for mag updates
perf_counter_t _perf_gps; ///<local performance counter for gps updates
perf_counter_t _perf_baro; ///<local performance counter for baro updates
perf_counter_t _perf_airspeed; ///<local performance counter for airspeed updates
bool _initialized;
struct {
float throttle_cruise;
uint32_t vel_delay_ms;
uint32_t pos_delay_ms;
uint32_t height_delay_ms;
uint32_t mag_delay_ms;
uint32_t tas_delay_ms;
} _parameters; /**< local copies of interesting parameters */
struct {
param_t throttle_cruise;
} _parameter_handles; /**< handles for interesting parameters */
/**
* Update our local parameter cache.
*/
int parameters_update();
/**
* Update control outputs
*
*/
void control_update();
/**
* Check for changes in vehicle status.
*/
void vehicle_status_poll();
/**
* Shim for calling task_main from task_create.
*/
static void task_main_trampoline(int argc, char *argv[]);
/**
* Main sensor collection task.
*/
void task_main() __attribute__((noreturn));
};
namespace estimator
{
/* oddly, ERROR is not defined for c++ */
#ifdef ERROR
# undef ERROR
#endif
static const int ERROR = -1;
FixedwingEstimator *g_estimator;
}
FixedwingEstimator::FixedwingEstimator() :
_task_should_exit(false),
_estimator_task(-1),
/* subscriptions */
#ifndef SENSOR_COMBINED_SUB
_gyro_sub(-1),
_accel_sub(-1),
_mag_sub(-1),
#else
_sensor_combined_sub(-1),
#endif
_airspeed_sub(-1),
_baro_sub(-1),
_gps_sub(-1),
_vstatus_sub(-1),
_params_sub(-1),
_manual_control_sub(-1),
/* publications */
_att_pub(-1),
_global_pos_pub(-1),
_local_pos_pub(-1),
/* performance counters */
_loop_perf(perf_alloc(PC_COUNT, "fw_att_pos_estimator")),
_perf_gyro(perf_alloc(PC_COUNT, "fw_ekf_gyro_upd")),
_perf_accel(perf_alloc(PC_COUNT, "fw_ekf_accel_upd")),
_perf_mag(perf_alloc(PC_COUNT, "fw_ekf_mag_upd")),
_perf_gps(perf_alloc(PC_COUNT, "fw_ekf_gps_upd")),
_perf_baro(perf_alloc(PC_COUNT, "fw_ekf_baro_upd")),
_perf_airspeed(perf_alloc(PC_COUNT, "fw_ekf_aspd_upd")),
/* states */
_initialized(false)
{
_parameter_handles.throttle_cruise = param_find("NAV_DUMMY");
/* fetch initial parameter values */
parameters_update();
/* get offsets */
int fd, res;
fd = open(GYRO_DEVICE_PATH, O_RDONLY);
if (fd > 0) {
res = ioctl(fd, GYROIOCGSCALE, (long unsigned int)&_gyro_offsets);
close(fd);
}
fd = open(ACCEL_DEVICE_PATH, O_RDONLY);
if (fd > 0) {
res = ioctl(fd, ACCELIOCGSCALE, (long unsigned int)&_accel_offsets);
close(fd);
}
fd = open(MAG_DEVICE_PATH, O_RDONLY);
if (fd > 0) {
res = ioctl(fd, MAGIOCGSCALE, (long unsigned int)&_mag_offsets);
close(fd);
}
}
FixedwingEstimator::~FixedwingEstimator()
{
if (_estimator_task != -1) {
/* task wakes up every 100ms or so at the longest */
_task_should_exit = true;
/* wait for a second for the task to quit at our request */
unsigned i = 0;
do {
/* wait 20ms */
usleep(20000);
/* if we have given up, kill it */
if (++i > 50) {
task_delete(_estimator_task);
break;
}
} while (_estimator_task != -1);
}
estimator::g_estimator = nullptr;
}
int
FixedwingEstimator::parameters_update()
{
// XXX NEED TO GET HANDLES FIRST! NEEDS PARAM INIT
//param_get(_parameter_handles.throttle_cruise, &(_parameters.throttle_cruise));
_parameters.vel_delay_ms = 230;
_parameters.pos_delay_ms = 210;
_parameters.height_delay_ms = 350;
_parameters.mag_delay_ms = 30;
_parameters.tas_delay_ms = 210;
return OK;
}
void
FixedwingEstimator::vehicle_status_poll()
{
bool vstatus_updated;
/* Check HIL state if vehicle status has changed */
orb_check(_vstatus_sub, &vstatus_updated);
if (vstatus_updated) {
orb_copy(ORB_ID(vehicle_status), _vstatus_sub, &_vstatus);
}
}
void
FixedwingEstimator::task_main_trampoline(int argc, char *argv[])
{
estimator::g_estimator->task_main();
}
void
FixedwingEstimator::task_main()
{
/* inform about start */
warnx("Initializing..");
fflush(stdout);
/*
* 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));
/* 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, 4);
#endif
parameters_update();
/* set initial filter state */
fuseVelData = false;
fusePosData = false;
fuseHgtData = false;
fuseMagData = false;
fuseVtasData = false;
statesInitialised = false;
/* initialize measurement data */
VtasMeas = 0.0f;
Vector3f lastAngRate = {0.0f, 0.0f, 0.0f};
Vector3f lastAccel = {0.0f, 0.0f, 0.0f};
float dt = 0.0f; // time lapsed since last covariance prediction
/* 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
hrt_abstime start_time = hrt_absolute_time();
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 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 estimator if gyro updated */
if (fds[1].revents & POLLIN) {
/* check vehicle status for changes to publication state */
vehicle_status_poll();
bool accel_updated;
bool mag_updated;
perf_count(_perf_gyro);
/**
* PART ONE: COLLECT ALL DATA
**/
hrt_abstime last_sensor_timestamp;
/* 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) {
perf_count(_perf_accel);
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 (deltaT > 1.0f)
deltaT = 0.01f;
// Always store data, independent of init status
/* fill in last data set */
dtIMU = deltaT;
angRate.x = _gyro.x;
angRate.y = _gyro.y;
angRate.z = _gyro.z;
accel.x = _accel.x;
accel.y = _accel.y;
accel.z = _accel.z;
dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU;
lastAngRate = angRate;
dVelIMU = 0.5f * (accel + lastAccel) * dtIMU;
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;
}
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;
last_run = _sensor_combined.timestamp;
/* guard against too large deltaT's */
if (deltaT > 1.0f || deltaT < 0.000001f)
deltaT = 0.01f;
// Always store data, independent of init status
/* fill in last data set */
dtIMU = deltaT;
angRate.x = _sensor_combined.gyro_rad_s[0];
angRate.y = _sensor_combined.gyro_rad_s[1];
angRate.z = _sensor_combined.gyro_rad_s[2];
accel.x = _sensor_combined.accelerometer_m_s2[0];
accel.y = _sensor_combined.accelerometer_m_s2[1];
accel.z = _sensor_combined.accelerometer_m_s2[2];
dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU;
lastAngRate = angRate;
dVelIMU = 0.5f * (accel + lastAccel) * dtIMU;
lastAccel = accel;
if (last_mag != _sensor_combined.magnetometer_timestamp) {
mag_updated = true;
}
last_mag = _sensor_combined.magnetometer_timestamp;
#endif
bool airspeed_updated;
orb_check(_airspeed_sub, &airspeed_updated);
if (airspeed_updated) {
orb_copy(ORB_ID(airspeed), _airspeed_sub, &_airspeed);
perf_count(_perf_airspeed);
VtasMeas = _airspeed.true_airspeed_m_s;
}
bool gps_updated;
orb_check(_gps_sub, &gps_updated);
if (gps_updated) {
orb_copy(ORB_ID(vehicle_gps_position), _gps_sub, &_gps);
perf_count(_perf_gps);
if (_gps.fix_type < 3) {
gps_updated = false;
} else {
/* fuse GPS updates */
//_gps.timestamp / 1e3;
GPSstatus = _gps.fix_type;
velNED[0] = _gps.vel_n_m_s;
velNED[1] = _gps.vel_e_m_s;
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]);
gpsLat = math::radians(_gps.lat / (double)1e7);
gpsLon = math::radians(_gps.lon / (double)1e7) - M_PI;
gpsHgt = _gps.alt / 1e3f;
}
}
bool baro_updated;
orb_check(_baro_sub, &baro_updated);
if (baro_updated) {
orb_copy(ORB_ID(sensor_baro), _baro_sub, &_baro);
baroHgt = _baro.altitude;
// Could use a blend of GPS and baro alt data if desired
hgtMea = 1.0f*baroHgt + 0.0f*gpsHgt;
}
#ifndef SENSOR_COMBINED_SUB
orb_check(_mag_sub, &mag_updated);
#endif
if (mag_updated) {
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
magData.x = _mag.x;
magBias.x = 0.000001f; // _mag_offsets.x_offset
magData.y = _mag.y;
magBias.y = 0.000001f; // _mag_offsets.y_offset
magData.z = _mag.z;
magBias.z = 0.000001f; // _mag_offsets.y_offset
#else
// XXX we compensate the offsets upfront - should be close to zero.
// 0.001f
magData.x = _sensor_combined.magnetometer_ga[0];
magBias.x = 0.000001f; // _mag_offsets.x_offset
magData.y = _sensor_combined.magnetometer_ga[1];
magBias.y = 0.000001f; // _mag_offsets.y_offset
magData.z = _sensor_combined.magnetometer_ga[2];
magBias.z = 0.000001f; // _mag_offsets.y_offset
#endif
}
/**
* PART TWO: EXECUTE THE FILTER
**/
if (hrt_elapsed_time(&start_time) > 500000 && !_initialized && (GPSstatus == 3)) {
InitialiseFilter(velNED);
_initialized = true;
warnx("init done.");
}
if (_initialized) {
/* predict states and covariances */
/* run the strapdown INS every sensor update */
UpdateStrapdownEquationsNED();
/* store the predictions */
StoreStates(IMUmsec);
/* evaluate if on ground */
// OnGroundCheck();
onGround = false;
/* prepare the delta angles and time used by the covariance prediction */
summedDelAng = summedDelAng + correctedDelAng;
summedDelVel = summedDelVel + correctedDelVel;
dt += dtIMU;
/* predict the covairance if the total delta angle has exceeded the threshold
* or the time limit will be exceeded on the next measurement update
*/
if ((dt >= (covTimeStepMax - dtIMU)) || (summedDelAng.length() > covDelAngMax)) {
CovariancePrediction(dt);
summedDelAng = summedDelAng.zero();
summedDelVel = summedDelVel.zero();
dt = 0.0f;
}
}
if (gps_updated && _initialized) {
/* convert GPS measurements to horizontal NE, altitude and 3D velocity NED */
calcposNED(posNED, gpsLat, gpsLon, gpsHgt, latRef, lonRef, hgtRef);
posNE[0] = posNED[0];
posNE[1] = posNED[1];
// set flags for further processing
fuseVelData = true;
fusePosData = true;
/* recall states after adjusting for delays */
RecallStates(statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms));
RecallStates(statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms));
/* run the actual fusion */
FuseVelposNED();
} else {
fuseVelData = false;
fusePosData = false;
}
if (baro_updated && _initialized) {
fuseHgtData = true;
// recall states stored at time of measurement after adjusting for delays
RecallStates(statesAtHgtTime, (IMUmsec - _parameters.height_delay_ms));
// run the fusion step
FuseVelposNED();
} else {
fuseHgtData = false;
}
if (mag_updated && _initialized) {
fuseMagData = true;
RecallStates(statesAtMagMeasTime, (IMUmsec - _parameters.mag_delay_ms));
} else {
fuseMagData = false;
}
if (_initialized) {
FuseMagnetometer();
}
if (airspeed_updated && _initialized
&& _airspeed.true_airspeed_m_s > 6.0f /* XXX magic number */) {
fuseVtasData = true;
RecallStates(statesAtVtasMeasTime, (IMUmsec - _parameters.tas_delay_ms)); // assume 100 msec avg delay for airspeed data
FuseAirspeed();
} else {
fuseVtasData = false;
}
// Publish results
if (_initialized) {
// State vector:
// 0-3: quaternions (q0, q1, q2, q3)
// 4-6: Velocity - m/sec (North, East, Down)
// 7-9: Position - m (North, East, Down)
// 10-12: Delta Angle bias - rad (X,Y,Z)
// 13-14: Wind Vector - m/sec (North,East)
// 15-17: Earth Magnetic Field Vector - milligauss (North, East, Down)
// 18-20: Body Magnetic Field Vector - milligauss (X,Y,Z)
math::Quaternion q(states[0], states[1], states[2], states[3]);
math::Dcm R(q);
math::EulerAngles euler(R);
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] = states[0];
_att.q[1] = states[1];
_att.q[2] = states[2];
_att.q[3] = states[3];
_att.q_valid = true;
_att.R_valid = true;
_att.timestamp = last_sensor_timestamp;
_att.roll = euler.getPhi();
_att.pitch = euler.getTheta();
_att.yaw = euler.getPsi();
_att.rollspeed = angRate.x - states[10];
_att.pitchspeed = angRate.y - states[11];
_att.yawspeed = angRate.z - states[12];
// gyro offsets
_att.rate_offsets[0] = states[10];
_att.rate_offsets[1] = states[11];
_att.rate_offsets[2] = 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);
}
_local_pos.timestamp = last_sensor_timestamp;
_local_pos.x = states[7];
_local_pos.y = states[8];
_local_pos.z = states[9];
_local_pos.vx = states[4];
_local_pos.vy = states[5];
_local_pos.vz = states[6];
_local_pos.xy_valid = true;
_local_pos.z_valid = true;
_local_pos.v_xy_valid = true;
_local_pos.v_z_valid = true;
/* 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 = _gyro.timestamp;
// /* lazily publish the global position only once available */
// if (_global_pos_pub > 0) {
// /* publish the attitude setpoint */
// 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);
// }
}
}
perf_end(_loop_perf);
}
warnx("exiting.\n");
_estimator_task = -1;
_exit(0);
}
int
FixedwingEstimator::start()
{
ASSERT(_estimator_task == -1);
/* start the task */
_estimator_task = task_spawn_cmd("fw_att_pos_estimator",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 40,
6000,
(main_t)&FixedwingEstimator::task_main_trampoline,
nullptr);
if (_estimator_task < 0) {
warn("task start failed");
return -errno;
}
return OK;
}
void print_status()
{
math::Quaternion q(states[0], states[1], states[2], states[3]);
math::EulerAngles euler(q);
printf("attitude: roll: %8.4f, pitch %8.4f, yaw: %8.4f degrees\n",
(double)math::degrees(euler.getPhi()), (double)math::degrees(euler.getTheta()), (double)math::degrees(euler.getPsi()));
// State vector:
// 0-3: quaternions (q0, q1, q2, q3)
// 4-6: Velocity - m/sec (North, East, Down)
// 7-9: Position - m (North, East, Down)
// 10-12: Delta Angle bias - rad (X,Y,Z)
// 13-14: Wind Vector - m/sec (North,East)
// 15-17: Earth Magnetic Field Vector - milligauss (North, East, Down)
// 18-20: Body Magnetic Field Vector - milligauss (X,Y,Z)
printf("dtIMU: %8.6f dt: %8.6f IMUmsec: %d\n", dtIMU, dt, (int)IMUmsec);
printf("dvel: %8.6f %8.6f %8.6f accel: %8.6f %8.6f %8.6f\n", (double)dVelIMU.x, (double)dVelIMU.y, (double)dVelIMU.z, (double)accel.x, (double)accel.y, (double)accel.z);
printf("dang: %8.4f %8.4f %8.4f dang corr: %8.4f %8.4f %8.4f\n" , (double)dAngIMU.x, (double)dAngIMU.y, (double)dAngIMU.z, (double)correctedDelAng.x, (double)correctedDelAng.y, (double)correctedDelAng.z);
printf("states (quat) [1-4]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)states[0], (double)states[1], (double)states[2], (double)states[3]);
printf("states (vel m/s) [5-7]: %8.4f, %8.4f, %8.4f\n", (double)states[4], (double)states[5], (double)states[6]);
printf("states (pos m) [8-10]: %8.4f, %8.4f, %8.4f\n", (double)states[7], (double)states[8], (double)states[9]);
printf("states (delta ang) [11-13]: %8.4f, %8.4f, %8.4f\n", (double)states[10], (double)states[11], (double)states[12]);
printf("states (wind) [14-15]: %8.4f, %8.4f\n", (double)states[13], (double)states[14]);
printf("states (earth mag) [16-18]: %8.4f, %8.4f, %8.4f\n", (double)states[15], (double)states[16], (double)states[17]);
printf("states (body mag) [19-21]: %8.4f, %8.4f, %8.4f\n", (double)states[18], (double)states[19], (double)states[20]);
printf("states: %s %s %s %s %s %s %s %s %s\n",
(statesInitialised) ? "INITIALIZED" : "NON_INIT",
(onGround) ? "ON_GROUND" : "AIRBORNE",
(fuseVelData) ? "FUSE_VEL" : "INH_VEL",
(fusePosData) ? "FUSE_POS" : "INH_POS",
(fuseHgtData) ? "FUSE_HGT" : "INH_HGT",
(fuseMagData) ? "FUSE_MAG" : "INH_MAG",
(fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS",
(useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD",
(useCompass) ? "USE_COMPASS" : "IGN_COMPASS");
}
int fw_att_pos_estimator_main(int argc, char *argv[])
{
if (argc < 1)
errx(1, "usage: fw_att_pos_estimator {start|stop|status}");
if (!strcmp(argv[1], "start")) {
if (estimator::g_estimator != nullptr)
errx(1, "already running");
estimator::g_estimator = new FixedwingEstimator;
if (estimator::g_estimator == nullptr)
errx(1, "alloc failed");
if (OK != estimator::g_estimator->start()) {
delete estimator::g_estimator;
estimator::g_estimator = nullptr;
err(1, "start failed");
}
exit(0);
}
if (!strcmp(argv[1], "stop")) {
if (estimator::g_estimator == nullptr)
errx(1, "not running");
delete estimator::g_estimator;
estimator::g_estimator = nullptr;
exit(0);
}
if (!strcmp(argv[1], "status")) {
if (estimator::g_estimator) {
warnx("running");
print_status();
exit(0);
} else {
errx(1, "not running");
}
}
warnx("unrecognized command");
return 1;
}
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