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author | Julian Oes <julian@oes.ch> | 2014-04-07 21:45:45 +0200 |
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committer | Julian Oes <julian@oes.ch> | 2014-04-07 21:45:45 +0200 |
commit | fc2bfb828f0f2ba681da1b33addd03698db4b679 (patch) | |
tree | a133e82429f186e8b7b727092944777f4d0b6d42 /src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp | |
parent | 38c3e68976c8dc167b4d1e5d24792401fc7cc7d3 (diff) | |
parent | e4628fbed641496704011b0c488a36ed05b45d5f (diff) | |
download | px4-firmware-fc2bfb828f0f2ba681da1b33addd03698db4b679.tar.gz px4-firmware-fc2bfb828f0f2ba681da1b33addd03698db4b679.tar.bz2 px4-firmware-fc2bfb828f0f2ba681da1b33addd03698db4b679.zip |
Merge remote-tracking branch 'px4/master' into mavlink_broadcast
Diffstat (limited to 'src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp')
-rw-r--r-- | src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp | 388 |
1 files changed, 201 insertions, 187 deletions
diff --git a/src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp b/src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp index c9d75bce4..840cd585e 100644 --- a/src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp +++ b/src/modules/fw_att_pos_estimator/fw_att_pos_estimator_main.cpp @@ -124,6 +124,16 @@ public: */ int start(); + /** + * Print the current status. + */ + void print_status(); + + /** + * Trip the filter by feeding it NaN values. + */ + int trip_nan(); + private: bool _task_should_exit; /**< if true, sensor task should exit */ @@ -199,6 +209,7 @@ private: param_t tas_delay_ms; } _parameter_handles; /**< handles for interesting parameters */ + AttPosEKF *_ekf; /** * Update our local parameter cache. @@ -280,7 +291,8 @@ FixedwingEstimator::FixedwingEstimator() : /* states */ _initialized(false), _gps_initialized(false), - _mavlink_fd(-1) + _mavlink_fd(-1), + _ekf(nullptr) { _mavlink_fd = open(MAVLINK_LOG_DEVICE, 0); @@ -384,6 +396,12 @@ void FixedwingEstimator::task_main() { + _ekf = new AttPosEKF(); + + if (!_ekf) { + errx(1, "failed allocating EKF filter - out of RAM!"); + } + /* * do subscriptions */ @@ -414,23 +432,23 @@ FixedwingEstimator::task_main() parameters_update(); /* set initial filter state */ - fuseVelData = false; - fusePosData = false; - fuseHgtData = false; - fuseMagData = false; - fuseVtasData = false; - statesInitialised = false; + _ekf->fuseVelData = false; + _ekf->fusePosData = false; + _ekf->fuseHgtData = false; + _ekf->fuseMagData = false; + _ekf->fuseVtasData = false; + _ekf->statesInitialised = false; /* initialize measurement data */ - VtasMeas = 0.0f; + _ekf->VtasMeas = 0.0f; Vector3f lastAngRate = {0.0f, 0.0f, 0.0f}; Vector3f lastAccel = {0.0f, 0.0f, -9.81f}; - dVelIMU.x = 0.0f; - dVelIMU.y = 0.0f; - dVelIMU.z = 0.0f; - dAngIMU.x = 0.0f; - dAngIMU.y = 0.0f; - dAngIMU.z = 0.0f; + _ekf->dVelIMU.x = 0.0f; + _ekf->dVelIMU.y = 0.0f; + _ekf->dVelIMU.z = 0.0f; + _ekf->dAngIMU.x = 0.0f; + _ekf->dAngIMU.y = 0.0f; + _ekf->dAngIMU.z = 0.0f; /* wakeup source(s) */ struct pollfd fds[2]; @@ -509,7 +527,7 @@ FixedwingEstimator::task_main() } last_sensor_timestamp = _gyro.timestamp; - IMUmsec = _gyro.timestamp / 1e3f; + _ekf.IMUmsec = _gyro.timestamp / 1e3f; float deltaT = (_gyro.timestamp - last_run) / 1e6f; last_run = _gyro.timestamp; @@ -521,20 +539,20 @@ FixedwingEstimator::task_main() // Always store data, independent of init status /* fill in last data set */ - dtIMU = deltaT; + _ekf->dtIMU = deltaT; - angRate.x = _gyro.x; - angRate.y = _gyro.y; - angRate.z = _gyro.z; + _ekf->angRate.x = _gyro.x; + _ekf->angRate.y = _gyro.y; + _ekf->angRate.z = _gyro.z; - accel.x = _accel.x; - accel.y = _accel.y; - accel.z = _accel.z; + _ekf->accel.x = _accel.x; + _ekf->accel.y = _accel.y; + _ekf->accel.z = _accel.z; - dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU; - lastAngRate = angRate; - dVelIMU = 0.5f * (accel + lastAccel) * dtIMU; - lastAccel = accel; + _ekf->dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU; + _ekf->lastAngRate = angRate; + _ekf->dVelIMU = 0.5f * (accel + lastAccel) * dtIMU; + _ekf->lastAccel = accel; #else @@ -563,20 +581,20 @@ FixedwingEstimator::task_main() // Always store data, independent of init status /* fill in last data set */ - dtIMU = deltaT; + _ekf->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]; + _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]; - accel.x = _sensor_combined.accelerometer_m_s2[0]; - accel.y = _sensor_combined.accelerometer_m_s2[1]; - accel.z = _sensor_combined.accelerometer_m_s2[2]; + _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]; - dAngIMU = 0.5f * (angRate + lastAngRate) * dtIMU; - lastAngRate = angRate; - dVelIMU = 0.5f * (accel + lastAccel) * dtIMU; - lastAccel = accel; + _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; @@ -597,7 +615,7 @@ FixedwingEstimator::task_main() orb_copy(ORB_ID(airspeed), _airspeed_sub, &_airspeed); perf_count(_perf_airspeed); - VtasMeas = _airspeed.true_airspeed_m_s; + _ekf->VtasMeas = _airspeed.true_airspeed_m_s; newAdsData = true; } else { @@ -622,24 +640,24 @@ FixedwingEstimator::task_main() /* check if we had a GPS outage for a long time */ if (hrt_elapsed_time(&last_gps) > 5 * 1000 * 1000) { - ResetPosition(); - ResetVelocity(); - ResetStoredStates(); + _ekf->ResetPosition(); + _ekf->ResetVelocity(); + _ekf->ResetStoredStates(); } /* 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; + _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]); - gpsLat = math::radians(_gps.lat / (double)1e7); - gpsLon = math::radians(_gps.lon / (double)1e7) - M_PI; - gpsHgt = _gps.alt / 1e3f; + _ekf->gpsLat = math::radians(_gps.lat / (double)1e7); + _ekf->gpsLon = math::radians(_gps.lon / (double)1e7) - M_PI; + _ekf->gpsHgt = _gps.alt / 1e3f; newDataGps = true; } @@ -652,10 +670,10 @@ FixedwingEstimator::task_main() if (baro_updated) { orb_copy(ORB_ID(sensor_baro), _baro_sub, &_baro); - baroHgt = _baro.altitude - _baro_ref; + _ekf->baroHgt = _baro.altitude - _baro_ref; // Could use a blend of GPS and baro alt data if desired - hgtMea = 1.0f * baroHgt + 0.0f * gpsHgt; + _ekf->hgtMea = 1.0f * _ekf->baroHgt + 0.0f * _ekf->gpsHgt; } #ifndef SENSOR_COMBINED_SUB @@ -671,27 +689,27 @@ FixedwingEstimator::task_main() // 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 + _ekf->magData.x = _mag.x; + _ekf->magBias.x = 0.000001f; // _mag_offsets.x_offset - magData.y = _mag.y; - magBias.y = 0.000001f; // _mag_offsets.y_offset + _ekf->magData.y = _mag.y; + _ekf->magBias.y = 0.000001f; // _mag_offsets.y_offset - magData.z = _mag.z; - magBias.z = 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 - magData.x = _sensor_combined.magnetometer_ga[0]; - magBias.x = 0.000001f; // _mag_offsets.x_offset + _ekf->magData.x = _sensor_combined.magnetometer_ga[0]; + _ekf->magBias.x = 0.000001f; // _mag_offsets.x_offset - magData.y = _sensor_combined.magnetometer_ga[1]; - magBias.y = 0.000001f; // _mag_offsets.y_offset + _ekf->magData.y = _sensor_combined.magnetometer_ga[1]; + _ekf->magBias.y = 0.000001f; // _mag_offsets.y_offset - magData.z = _sensor_combined.magnetometer_ga[2]; - magBias.z = 0.000001f; // _mag_offsets.y_offset + _ekf->magData.z = _sensor_combined.magnetometer_ga[2]; + _ekf->magBias.z = 0.000001f; // _mag_offsets.y_offset #endif @@ -705,7 +723,7 @@ FixedwingEstimator::task_main() /** * CHECK IF THE INPUT DATA IS SANE */ - int check = CheckAndBound(); + int check = _ekf->CheckAndBound(); switch (check) { case 0: @@ -739,7 +757,7 @@ FixedwingEstimator::task_main() struct ekf_status_report ekf_report; - GetLastErrorState(&ekf_report); + _ekf->GetLastErrorState(&ekf_report); struct estimator_status_report rep; memset(&rep, 0, sizeof(rep)); @@ -779,16 +797,16 @@ FixedwingEstimator::task_main() if (hrt_elapsed_time(&start_time) > 100000) { - if (!_gps_initialized && (GPSstatus == 3)) { - velNED[0] = _gps.vel_n_m_s; - velNED[1] = _gps.vel_e_m_s; - velNED[2] = _gps.vel_d_m_s; + if (!_gps_initialized && (_ekf->GPSstatus == 3)) { + _ekf->velNED[0] = _gps.vel_n_m_s; + _ekf->velNED[1] = _gps.vel_e_m_s; + _ekf->velNED[2] = _gps.vel_d_m_s; double lat = _gps.lat * 1e-7; double lon = _gps.lon * 1e-7; float alt = _gps.alt * 1e-3; - InitialiseFilter(velNED); + _ekf->InitialiseFilter(_ekf->velNED); // Initialize projection _local_pos.ref_lat = _gps.lat; @@ -799,7 +817,7 @@ FixedwingEstimator::task_main() // Store orb_copy(ORB_ID(sensor_baro), _baro_sub, &_baro); _baro_ref = _baro.altitude; - baroHgt = _baro.altitude - _baro_ref; + _ekf->baroHgt = _baro.altitude - _baro_ref; _baro_gps_offset = _baro_ref - _local_pos.ref_alt; // XXX this is not multithreading safe @@ -808,24 +826,24 @@ FixedwingEstimator::task_main() _gps_initialized = true; - } else if (!statesInitialised) { - velNED[0] = 0.0f; - velNED[1] = 0.0f; - velNED[2] = 0.0f; - posNED[0] = 0.0f; - posNED[1] = 0.0f; - posNED[2] = 0.0f; - - posNE[0] = posNED[0]; - posNE[1] = posNED[1]; - InitialiseFilter(velNED); + } else if (!_ekf->statesInitialised) { + _ekf->velNED[0] = 0.0f; + _ekf->velNED[1] = 0.0f; + _ekf->velNED[2] = 0.0f; + _ekf->posNED[0] = 0.0f; + _ekf->posNED[1] = 0.0f; + _ekf->posNED[2] = 0.0f; + + _ekf->posNE[0] = _ekf->posNED[0]; + _ekf->posNE[1] = _ekf->posNED[1]; + _ekf->InitialiseFilter(_ekf->velNED); } } // If valid IMU data and states initialised, predict states and covariances - if (statesInitialised) { + if (_ekf->statesInitialised) { // Run the strapdown INS equations every IMU update - UpdateStrapdownEquationsNED(); + _ekf->UpdateStrapdownEquationsNED(); #if 0 // debug code - could be tunred into a filter mnitoring/watchdog function float tempQuat[4]; @@ -842,20 +860,20 @@ FixedwingEstimator::task_main() #endif // store the predicted states for subsequent use by measurement fusion - StoreStates(IMUmsec); + _ekf->StoreStates(IMUmsec); // Check if on ground - status is used by covariance prediction - OnGroundCheck(); + _ekf->OnGroundCheck(); // sum delta angles and time used by covariance prediction - summedDelAng = summedDelAng + correctedDelAng; - summedDelVel = summedDelVel + dVelIMU; - dt += dtIMU; + _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 >= (covTimeStepMax - dtIMU)) || (summedDelAng.length() > covDelAngMax)) { - CovariancePrediction(dt); - summedDelAng = summedDelAng.zero(); - summedDelVel = summedDelVel.zero(); + if ((dt >= (covTimeStepMax - _ekf->dtIMU)) || (_ekf->summedDelAng.length() > covDelAngMax)) { + _ekf->CovariancePrediction(dt); + _ekf->summedDelAng = _ekf->summedDelAng.zero(); + _ekf->summedDelVel = _ekf->summedDelVel.zero(); dt = 0.0f; } @@ -865,79 +883,79 @@ FixedwingEstimator::task_main() // Fuse GPS Measurements if (newDataGps && _gps_initialized) { // Convert GPS measurements to Pos NE, hgt and Vel NED - velNED[0] = _gps.vel_n_m_s; - velNED[1] = _gps.vel_e_m_s; - velNED[2] = _gps.vel_d_m_s; - calcposNED(posNED, gpsLat, gpsLon, gpsHgt, latRef, lonRef, hgtRef); + _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(_ekf->posNED, _ekf->gpsLat, _ekf->gpsLon, _ekf->gpsHgt, _ekf->latRef, _ekf->lonRef, _ekf->hgtRef); - posNE[0] = posNED[0]; - posNE[1] = posNED[1]; + _ekf->posNE[0] = _ekf->posNED[0]; + _ekf->posNE[1] = _ekf->posNED[1]; // set fusion flags - fuseVelData = true; - fusePosData = true; + _ekf->fuseVelData = true; + _ekf->fusePosData = true; // recall states stored at time of measurement after adjusting for delays - RecallStates(statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms)); - RecallStates(statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms)); + _ekf->RecallStates(_ekf->statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms)); + _ekf->RecallStates(_ekf->statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms)); // run the fusion step - FuseVelposNED(); + _ekf->FuseVelposNED(); - } else if (statesInitialised) { + } else if (_ekf->statesInitialised) { // Convert GPS measurements to Pos NE, hgt and Vel NED - velNED[0] = 0.0f; - velNED[1] = 0.0f; - velNED[2] = 0.0f; - posNED[0] = 0.0f; - posNED[1] = 0.0f; - posNED[2] = 0.0f; - - posNE[0] = posNED[0]; - posNE[1] = posNED[1]; + _ekf->velNED[0] = 0.0f; + _ekf->velNED[1] = 0.0f; + _ekf->velNED[2] = 0.0f; + _ekf->posNED[0] = 0.0f; + _ekf->posNED[1] = 0.0f; + _ekf->posNED[2] = 0.0f; + + _ekf->posNE[0] = _ekf->posNED[0]; + _ekf->posNE[1] = _ekf->posNED[1]; // set fusion flags - fuseVelData = true; - fusePosData = true; + _ekf->fuseVelData = true; + _ekf->fusePosData = true; // recall states stored at time of measurement after adjusting for delays - RecallStates(statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms)); - RecallStates(statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms)); + _ekf->RecallStates(_ekf->statesAtVelTime, (IMUmsec - _parameters.vel_delay_ms)); + _ekf->RecallStates(_ekf->statesAtPosTime, (IMUmsec - _parameters.pos_delay_ms)); // run the fusion step - FuseVelposNED(); + _ekf->FuseVelposNED(); } else { - fuseVelData = false; - fusePosData = false; + _ekf->fuseVelData = false; + _ekf->fusePosData = false; } - if (newAdsData && statesInitialised) { + if (newAdsData && _ekf->statesInitialised) { // Could use a blend of GPS and baro alt data if desired - hgtMea = 1.0f * baroHgt + 0.0f * gpsHgt; - fuseHgtData = true; + _ekf->hgtMea = 1.0f * _ekf->baroHgt + 0.0f * _ekf->gpsHgt; + _ekf->fuseHgtData = true; // recall states stored at time of measurement after adjusting for delays - RecallStates(statesAtHgtTime, (IMUmsec - _parameters.height_delay_ms)); + _ekf->RecallStates(_ekf->statesAtHgtTime, (IMUmsec - _parameters.height_delay_ms)); // run the fusion step - FuseVelposNED(); + _ekf->FuseVelposNED(); } else { - fuseHgtData = false; + _ekf->fuseHgtData = false; } // Fuse Magnetometer Measurements - if (newDataMag && statesInitialised) { - fuseMagData = true; - RecallStates(statesAtMagMeasTime, (IMUmsec - _parameters.mag_delay_ms)); // Assume 50 msec avg delay for magnetometer data + if (newDataMag && _ekf->statesInitialised) { + _ekf->fuseMagData = true; + _ekf->RecallStates(_ekf->statesAtMagMeasTime, (IMUmsec - _parameters.mag_delay_ms)); // Assume 50 msec avg delay for magnetometer data } else { - fuseMagData = false; + _ekf->fuseMagData = false; } - if (statesInitialised) FuseMagnetometer(); + if (_ekf->statesInitialised) _ekf->FuseMagnetometer(); // Fuse Airspeed Measurements - if (newAdsData && statesInitialised && VtasMeas > 8.0f) { - fuseVtasData = true; - RecallStates(statesAtVtasMeasTime, (IMUmsec - _parameters.tas_delay_ms)); // assume 100 msec avg delay for airspeed data - FuseAirspeed(); + 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 { - fuseVtasData = false; + _ekf->fuseVtasData = false; } // Publish results @@ -954,7 +972,7 @@ FixedwingEstimator::task_main() // 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::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(); @@ -962,10 +980,10 @@ FixedwingEstimator::task_main() _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[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; @@ -974,13 +992,13 @@ FixedwingEstimator::task_main() _att.pitch = euler(1); _att.yaw = euler(2); - _att.rollspeed = angRate.x - states[10]; - _att.pitchspeed = angRate.y - states[11]; - _att.yawspeed = angRate.z - states[12]; + _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] = states[10]; - _att.rate_offsets[1] = states[11]; - _att.rate_offsets[2] = states[12]; + _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) { @@ -993,20 +1011,15 @@ FixedwingEstimator::task_main() } } - if (!isfinite(states[0])) { - print_status(); - _exit(0); - } - if (_gps_initialized) { _local_pos.timestamp = last_sensor_timestamp; - _local_pos.x = states[7]; - _local_pos.y = states[8]; - _local_pos.z = states[9]; + _local_pos.x = _ekf->states[7]; + _local_pos.y = _ekf->states[8]; + _local_pos.z = _ekf->states[9]; - _local_pos.vx = states[4]; - _local_pos.vy = states[5]; - _local_pos.vz = states[6]; + _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; @@ -1107,9 +1120,10 @@ FixedwingEstimator::start() return OK; } -void print_status() +void +FixedwingEstimator::print_status() { - math::Quaternion q(states[0], states[1], states[2], states[3]); + 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(); @@ -1125,30 +1139,30 @@ void print_status() // 15-17: Earth Magnetic Field Vector - gauss (North, East, Down) // 18-20: Body Magnetic Field Vector - gauss (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("dtIMU: %8.6f dt: %8.6f IMUmsec: %d\n", _ekf->dtIMU, dt, (int)IMUmsec); + printf("dvel: %8.6f %8.6f %8.6f accel: %8.6f %8.6f %8.6f\n", (double)_ekf->dVelIMU.x, (double)_ekf->dVelIMU.y, (double)_ekf->dVelIMU.z, (double)_ekf->accel.x, (double)_ekf->accel.y, (double)_ekf->accel.z); + printf("dang: %8.4f %8.4f %8.4f dang corr: %8.4f %8.4f %8.4f\n" , (double)_ekf->dAngIMU.x, (double)_ekf->dAngIMU.y, (double)_ekf->dAngIMU.z, (double)_ekf->correctedDelAng.x, (double)_ekf->correctedDelAng.y, (double)_ekf->correctedDelAng.z); + printf("states (quat) [1-4]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[0], (double)_ekf->states[1], (double)_ekf->states[2], (double)_ekf->states[3]); + printf("states (vel m/s) [5-7]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[4], (double)_ekf->states[5], (double)_ekf->states[6]); + printf("states (pos m) [8-10]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[7], (double)_ekf->states[8], (double)_ekf->states[9]); + printf("states (delta ang) [11-13]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[10], (double)_ekf->states[11], (double)_ekf->states[12]); + printf("states (wind) [14-15]: %8.4f, %8.4f\n", (double)_ekf->states[13], (double)_ekf->states[14]); + printf("states (earth mag) [16-18]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[15], (double)_ekf->states[16], (double)_ekf->states[17]); + printf("states (body mag) [19-21]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[18], (double)_ekf->states[19], (double)_ekf->states[20]); printf("states: %s %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", - (staticMode) ? "STATIC_MODE" : "DYNAMIC_MODE"); + (_ekf->statesInitialised) ? "INITIALIZED" : "NON_INIT", + (_ekf->onGround) ? "ON_GROUND" : "AIRBORNE", + (_ekf->fuseVelData) ? "FUSE_VEL" : "INH_VEL", + (_ekf->fusePosData) ? "FUSE_POS" : "INH_POS", + (_ekf->fuseHgtData) ? "FUSE_HGT" : "INH_HGT", + (_ekf->fuseMagData) ? "FUSE_MAG" : "INH_MAG", + (_ekf->fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS", + (_ekf->useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD", + (_ekf->useCompass) ? "USE_COMPASS" : "IGN_COMPASS", + (_ekf->staticMode) ? "STATIC_MODE" : "DYNAMIC_MODE"); } -int trip_nan() { +int FixedwingEstimator::trip_nan() { int ret = 0; @@ -1166,7 +1180,7 @@ int trip_nan() { float nan_val = 0.0f / 0.0f; warnx("system not armed, tripping state vector with NaN values"); - states[5] = nan_val; + _ekf->states[5] = nan_val; usleep(100000); // warnx("tripping covariance #1 with NaN values"); @@ -1178,15 +1192,15 @@ int trip_nan() { // usleep(100000); warnx("tripping covariance #3 with NaN values"); - P[3][3] = nan_val; // covariance matrix + _ekf->P[3][3] = nan_val; // covariance matrix usleep(100000); warnx("tripping Kalman gains with NaN values"); - Kfusion[0] = nan_val; // Kalman gains + _ekf->Kfusion[0] = nan_val; // Kalman gains usleep(100000); warnx("tripping stored states[0] with NaN values"); - storedStates[0][0] = nan_val; + _ekf->storedStates[0][0] = nan_val; usleep(100000); warnx("\nDONE - FILTER STATE:"); @@ -1234,7 +1248,7 @@ int fw_att_pos_estimator_main(int argc, char *argv[]) if (estimator::g_estimator) { warnx("running"); - print_status(); + estimator::g_estimator->print_status(); exit(0); @@ -1245,7 +1259,7 @@ int fw_att_pos_estimator_main(int argc, char *argv[]) if (!strcmp(argv[1], "trip")) { if (estimator::g_estimator) { - int ret = trip_nan(); + int ret = estimator::g_estimator->trip_nan(); exit(ret); |