/**************************************************************************** * * Copyright (c) 2015 Estimation and Control Library (ECL). 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 ECL 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 ekf.h * Class for core functions for ekf attitude and position estimator. * * @author Roman Bast * @author Paul Riseborough * */ #include "estimator_interface.h" class Ekf : public EstimatorInterface { public: Ekf() = default; ~Ekf() = default; // initialise variables to sane values (also interface class) bool init(uint64_t timestamp); // should be called every time new data is pushed into the filter bool update(); // gets the innovations of velocity and position measurements // 0-2 vel, 3-5 pos void get_vel_pos_innov(float vel_pos_innov[6]); // gets the innovations for of the NE auxiliary velocity measurement void get_aux_vel_innov(float aux_vel_innov[2]); // gets the innovations of the earth magnetic field measurements void get_mag_innov(float mag_innov[3]); // gets the innovations of the heading measurement void get_heading_innov(float *heading_innov); // gets the innovation variances of velocity and position measurements // 0-2 vel, 3-5 pos void get_vel_pos_innov_var(float vel_pos_innov_var[6]); // gets the innovation variances of the earth magnetic field measurements void get_mag_innov_var(float mag_innov_var[3]); // gets the innovations of airspeed measurement void get_airspeed_innov(float *airspeed_innov); // gets the innovation variance of the airspeed measurement void get_airspeed_innov_var(float *airspeed_innov_var); // gets the innovations of synthetic sideslip measurement void get_beta_innov(float *beta_innov); // gets the innovation variance of the synthetic sideslip measurement void get_beta_innov_var(float *beta_innov_var); // gets the innovation variance of the heading measurement void get_heading_innov_var(float *heading_innov_var); // gets the innovation variance of the flow measurement void get_flow_innov_var(float flow_innov_var[2]); // gets the innovation of the flow measurement void get_flow_innov(float flow_innov[2]); // gets the innovation variance of the drag specific force measurement void get_drag_innov_var(float drag_innov_var[2]); // gets the innovation of the drag specific force measurement void get_drag_innov(float drag_innov[2]); // gets the innovation variance of the HAGL measurement void get_hagl_innov_var(float *hagl_innov_var); // gets the innovation of the HAGL measurement void get_hagl_innov(float *hagl_innov); // get the state vector at the delayed time horizon void get_state_delayed(float *state); // get the wind velocity in m/s void get_wind_velocity(float *wind); // get the wind velocity var void get_wind_velocity_var(float *wind_var); // get the true airspeed in m/s void get_true_airspeed(float *tas); // get the diagonal elements of the covariance matrix void get_covariances(float *covariances); // ask estimator for sensor data collection decision and do any preprocessing if required, returns true if not defined bool collect_gps(uint64_t time_usec, struct gps_message *gps); bool collect_imu(imuSample &imu); // get the ekf WGS-84 origin position and height and the system time it was last set // return true if the origin is valid bool get_ekf_origin(uint64_t *origin_time, map_projection_reference_s *origin_pos, float *origin_alt); // get the 1-sigma horizontal and vertical position uncertainty of the ekf WGS-84 position void get_ekf_gpos_accuracy(float *ekf_eph, float *ekf_epv); // get the 1-sigma horizontal and vertical position uncertainty of the ekf local position void get_ekf_lpos_accuracy(float *ekf_eph, float *ekf_epv); // get the 1-sigma horizontal and vertical velocity uncertainty void get_ekf_vel_accuracy(float *ekf_evh, float *ekf_evv); // get the vehicle control limits required by the estimator to keep within sensor limitations void get_ekf_ctrl_limits(float *vxy_max, float *vz_max, float *hagl_min, float *hagl_max); /* Reset all IMU bias states and covariances to initial alignment values. Use when the IMU sensor has changed. Returns true if reset performed, false if rejected due to less than 10 seconds lapsed since last reset. */ bool reset_imu_bias(); void get_vel_var(Vector3f &vel_var); void get_pos_var(Vector3f &pos_var); // return an array containing the output predictor angular, velocity and position tracking // error magnitudes (rad), (m/sec), (m) void get_output_tracking_error(float error[3]); /* Returns following IMU vibration metrics in the following array locations 0 : Gyro delta angle coning metric = filtered length of (delta_angle x prev_delta_angle) 1 : Gyro high frequency vibe = filtered length of (delta_angle - prev_delta_angle) 2 : Accel high frequency vibe = filtered length of (delta_velocity - prev_delta_velocity) */ void get_imu_vibe_metrics(float vibe[3]); // return true if the global position estimate is valid bool global_position_is_valid(); // check if the EKF is dead reckoning horizontal velocity using inertial data only void update_deadreckoning_status(); // return true if the terrain estimate is valid bool get_terrain_valid(); // update terrain validity status void update_terrain_valid(); // get the estimated terrain vertical position relative to the NED origin void get_terrain_vert_pos(float *ret); // get the accerometer bias in m/s/s void get_accel_bias(float bias[3]); // get the gyroscope bias in rad/s void get_gyro_bias(float bias[3]); // get GPS check status void get_gps_check_status(uint16_t *val); // return the amount the local vertical position changed in the last reset and the number of reset events void get_posD_reset(float *delta, uint8_t *counter) {*delta = _state_reset_status.posD_change; *counter = _state_reset_status.posD_counter;} // return the amount the local vertical velocity changed in the last reset and the number of reset events void get_velD_reset(float *delta, uint8_t *counter) {*delta = _state_reset_status.velD_change; *counter = _state_reset_status.velD_counter;} // return the amount the local horizontal position changed in the last reset and the number of reset events void get_posNE_reset(float delta[2], uint8_t *counter) { memcpy(delta, &_state_reset_status.posNE_change._data[0], sizeof(_state_reset_status.posNE_change._data)); *counter = _state_reset_status.posNE_counter; } // return the amount the local horizontal velocity changed in the last reset and the number of reset events void get_velNE_reset(float delta[2], uint8_t *counter) { memcpy(delta, &_state_reset_status.velNE_change._data[0], sizeof(_state_reset_status.velNE_change._data)); *counter = _state_reset_status.velNE_counter; } // return the amount the quaternion has changed in the last reset and the number of reset events void get_quat_reset(float delta_quat[4], uint8_t *counter) { memcpy(delta_quat, &_state_reset_status.quat_change._data[0], sizeof(_state_reset_status.quat_change._data)); *counter = _state_reset_status.quat_counter; } // get EKF innovation consistency check status information comprising of: // status - a bitmask integer containing the pass/fail status for each EKF measurement innovation consistency check // Innovation Test Ratios - these are the ratio of the innovation to the acceptance threshold. // A value > 1 indicates that the sensor measurement has exceeded the maximum acceptable level and has been rejected by the EKF // Where a measurement type is a vector quantity, eg magnetoemter, GPS position, etc, the maximum value is returned. void get_innovation_test_status(uint16_t *status, float *mag, float *vel, float *pos, float *hgt, float *tas, float *hagl, float *beta); // return a bitmask integer that describes which state estimates can be used for flight control void get_ekf_soln_status(uint16_t *status); // return the quaternion defining the rotation from the EKF to the External Vision reference frame void get_ekf2ev_quaternion(float *quat); private: static constexpr uint8_t _k_num_states{24}; ///< number of EKF states static constexpr float _k_earth_rate{0.000072921f}; ///< earth spin rate (rad/sec) struct { uint8_t velNE_counter; ///< number of horizontal position reset events (allow to wrap if count exceeds 255) uint8_t velD_counter; ///< number of vertical velocity reset events (allow to wrap if count exceeds 255) uint8_t posNE_counter; ///< number of horizontal position reset events (allow to wrap if count exceeds 255) uint8_t posD_counter; ///< number of vertical position reset events (allow to wrap if count exceeds 255) uint8_t quat_counter; ///< number of quaternion reset events (allow to wrap if count exceeds 255) Vector2f velNE_change; ///< North East velocity change due to last reset (m) float velD_change; ///< Down velocity change due to last reset (m/sec) Vector2f posNE_change; ///< North, East position change due to last reset (m) float posD_change; ///< Down position change due to last reset (m) Quatf quat_change; ///< quaternion delta due to last reset - multiply pre-reset quaternion by this to get post-reset quaternion } _state_reset_status{}; ///< reset event monitoring structure containing velocity, position, height and yaw reset information float _dt_ekf_avg{0.001f * FILTER_UPDATE_PERIOD_MS}; ///< average update rate of the ekf float _dt_update{0.01f}; ///< delta time since last ekf update. This time can be used for filters which run at the same rate as the Ekf::update() function. (sec) stateSample _state{}; ///< state struct of the ekf running at the delayed time horizon bool _filter_initialised{false}; ///< true when the EKF sttes and covariances been initialised bool _earth_rate_initialised{false}; ///< true when we know the earth rotatin rate (requires GPS) bool _fuse_height{false}; ///< true when baro height data should be fused bool _fuse_pos{false}; ///< true when gps position data should be fused bool _fuse_hor_vel{false}; ///< true when gps horizontal velocity measurement should be fused bool _fuse_vert_vel{false}; ///< true when gps vertical velocity measurement should be fused bool _fuse_hor_vel_aux{false}; ///< true when auxiliary horizontal velocity measurement should be fused float _posObsNoiseNE{0.0f}; ///< 1-STD observtion noise used for the fusion of NE position data (m) float _posInnovGateNE{1.0f}; ///< Number of standard deviations used for the NE position fusion innovation consistency check Vector2f _velObsVarNE; ///< 1-STD observation noise variance used for the fusion of NE velocity data (m/sec)**2 float _hvelInnovGate{1.0f}; ///< Number of standard deviations used for the horizontal velocity fusion innovation consistency check // variables used when position data is being fused using a relative position odometry model bool _fuse_hpos_as_odom{false}; ///< true when the NE position data is being fused using an odometry assumption Vector3f _pos_meas_prev; ///< previous value of NED position measurement fused using odometry assumption (m) Vector2f _hpos_pred_prev; ///< previous value of NE position state used by odometry fusion (m) bool _hpos_prev_available{false}; ///< true when previous values of the estimate and measurement are available for use Vector3f _ev_rot_vec_filt; ///< filtered rotation vector defining the rotation from EKF to EV reference (rad) Dcmf _ev_rot_mat; ///< transformation matrix that rotates observations from the EV to the EKF navigation frame uint64_t _ev_rot_last_time_us{0}; ///< previous time that the calculation of the ekf to ev rotation matrix was updated (uSec) // booleans true when fresh sensor data is available at the fusion time horizon bool _gps_data_ready{false}; ///< true when new GPS data has fallen behind the fusion time horizon and is available to be fused bool _mag_data_ready{false}; ///< true when new magnetometer data has fallen behind the fusion time horizon and is available to be fused bool _baro_data_ready{false}; ///< true when new baro height data has fallen behind the fusion time horizon and is available to be fused bool _range_data_ready{false}; ///< true when new range finder data has fallen behind the fusion time horizon and is available to be fused bool _flow_data_ready{false}; ///< true when new optical flow data has fallen behind the fusion time horizon and is available to be fused bool _ev_data_ready{false}; ///< true when new external vision system data has fallen behind the fusion time horizon and is available to be fused bool _tas_data_ready{false}; ///< true when new true airspeed data has fallen behind the fusion time horizon and is available to be fused uint64_t _time_last_fake_gps{0}; ///< last time we faked GPS position measurements to constrain tilt errors during operation without external aiding (uSec) uint64_t _time_ins_deadreckon_start{0}; ///< amount of time we have been doing inertial only deadreckoning (uSec) bool _using_synthetic_position{false}; ///< true if we are using a synthetic position to constrain drift uint64_t _time_last_pos_fuse{0}; ///< time the last fusion of horizontal position measurements was performed (uSec) uint64_t _time_last_delpos_fuse{0}; ///< time the last fusion of incremental horizontal position measurements was performed (uSec) uint64_t _time_last_vel_fuse{0}; ///< time the last fusion of velocity measurements was performed (uSec) uint64_t _time_last_hgt_fuse{0}; ///< time the last fusion of height measurements was performed (uSec) uint64_t _time_last_of_fuse{0}; ///< time the last fusion of optical flow measurements were performed (uSec) uint64_t _time_last_arsp_fuse{0}; ///< time the last fusion of airspeed measurements were performed (uSec) uint64_t _time_last_beta_fuse{0}; ///< time the last fusion of synthetic sideslip measurements were performed (uSec) uint64_t _time_last_rng_ready{0}; ///< time the last range finder measurement was ready (uSec) Vector2f _last_known_posNE; ///< last known local NE position vector (m) float _imu_collection_time_adj{0.0f}; ///< the amount of time the IMU collection needs to be advanced to meet the target set by FILTER_UPDATE_PERIOD_MS (sec) uint64_t _time_acc_bias_check{0}; ///< last time the accel bias check passed (uSec) uint64_t _delta_time_baro_us{0}; ///< delta time between two consecutive delayed baro samples from the buffer (uSec) uint64_t _last_imu_bias_cov_reset_us{0}; ///< time the last reset of IMU delta angle and velocity state covariances was performed (uSec) Vector3f _earth_rate_NED; ///< earth rotation vector (NED) in rad/s Dcmf _R_to_earth; ///< transformation matrix from body frame to earth frame from last EKF predition // used by magnetometer fusion mode selection Vector2f _accel_lpf_NE; ///< Low pass filtered horizontal earth frame acceleration (m/sec**2) float _yaw_delta_ef{0.0f}; ///< Recent change in yaw angle measured about the earth frame D axis (rad) float _yaw_rate_lpf_ef{0.0f}; ///< Filtered angular rate about earth frame D axis (rad/sec) bool _mag_bias_observable{false}; ///< true when there is enough rotation to make magnetometer bias errors observable bool _yaw_angle_observable{false}; ///< true when there is enough horizontal acceleration to make yaw observable uint64_t _time_yaw_started{0}; ///< last system time in usec that a yaw rotation moaneouvre was detected uint8_t _num_bad_flight_yaw_events{0}; ///< number of times a bad heading has been detected in flight and required a yaw reset uint64_t _mag_use_not_inhibit_us{0}; ///< last system time in usec before magnetomer use was inhibited bool _mag_use_inhibit{false}; ///< true when magnetomer use is being inhibited bool _mag_use_inhibit_prev{false}; ///< true when magnetomer use was being inhibited the previous frame bool _mag_inhibit_yaw_reset_req{false}; ///< true when magnetomer inhibit has been active for long enough to require a yaw reset when conditons improve. float _last_static_yaw{0.0f}; ///< last yaw angle recorded when on ground motion checks were passing (rad) bool _vehicle_at_rest_prev{false}; ///< true when the vehicle was at rest the previous time the status was checked float P[_k_num_states][_k_num_states] {}; ///< state covariance matrix float _vel_pos_innov[6] {}; ///< NED velocity and position innovations: 0-2 vel (m/sec), 3-5 pos (m) float _vel_pos_innov_var[6] {}; ///< NED velocity and position innovation variances: 0-2 vel ((m/sec)**2), 3-5 pos (m**2) float _aux_vel_innov[2] {}; ///< NE auxiliary velocity innovations: (m/sec) float _mag_innov[3] {}; ///< earth magnetic field innovations (Gauss) float _mag_innov_var[3] {}; ///< earth magnetic field innovation variance (Gauss**2) float _airspeed_innov{0.0f}; ///< airspeed measurement innovation (m/sec) float _airspeed_innov_var{0.0f}; ///< airspeed measurement innovation variance ((m/sec)**2) float _beta_innov{0.0f}; ///< synthetic sideslip measurement innovation (rad) float _beta_innov_var{0.0f}; ///< synthetic sideslip measurement innovation variance (rad**2) float _drag_innov[2] {}; ///< multirotor drag measurement innovation (m/sec**2) float _drag_innov_var[2] {}; ///< multirotor drag measurement innovation variance ((m/sec**2)**2) float _heading_innov{0.0f}; ///< heading measurement innovation (rad) float _heading_innov_var{0.0f}; ///< heading measurement innovation variance (rad**2) // optical flow processing float _flow_innov[2] {}; ///< flow measurement innovation (rad/sec) float _flow_innov_var[2] {}; ///< flow innovation variance ((rad/sec)**2) Vector3f _flow_gyro_bias; ///< bias errors in optical flow sensor rate gyro outputs (rad/sec) Vector3f _imu_del_ang_of; ///< bias corrected delta angle measurements accumulated across the same time frame as the optical flow rates (rad) float _delta_time_of{0.0f}; ///< time in sec that _imu_del_ang_of was accumulated over (sec) uint64_t _time_bad_motion_us{0}; ///< last system time that on-ground motion exceeded limits (uSec) uint64_t _time_good_motion_us{0}; ///< last system time that on-ground motion was within limits (uSec) bool _inhibit_flow_use{false}; ///< true when use of optical flow and range finder is being inhibited Vector2f _flowRadXYcomp; ///< measured delta angle of the image about the X and Y body axes after removal of body rotation (rad), RH rotation is positive float _mag_declination{0.0f}; ///< magnetic declination used by reset and fusion functions (rad) // output predictor states Vector3f _delta_angle_corr; ///< delta angle correction vector (rad) imuSample _imu_down_sampled{}; ///< down sampled imu data (sensor rate -> filter update rate) Quatf _q_down_sampled; ///< down sampled quaternion (tracking delta angles between ekf update steps) Vector3f _vel_err_integ; ///< integral of velocity tracking error (m) Vector3f _pos_err_integ; ///< integral of position tracking error (m.s) float _output_tracking_error[3] {}; ///< contains the magnitude of the angle, velocity and position track errors (rad, m/s, m) // variables used for the GPS quality checks float _gpsDriftVelN{0.0f}; ///< GPS north position derivative (m/sec) float _gpsDriftVelE{0.0f}; ///< GPS east position derivative (m/sec) float _gps_drift_velD{0.0f}; ///< GPS down position derivative (m/sec) float _gps_velD_diff_filt{0.0f}; ///< GPS filtered Down velocity (m/sec) float _gps_velN_filt{0.0f}; ///< GPS filtered North velocity (m/sec) float _gps_velE_filt{0.0f}; ///< GPS filtered East velocity (m/sec) uint64_t _last_gps_fail_us{0}; ///< last system time in usec that the GPS failed it's checks uint64_t _last_gps_pass_us{0}; ///< last system time in usec that the GPS passed it's checks float _gps_error_norm{1.0f}; ///< normalised gps error // Variables used to publish the WGS-84 location of the EKF local NED origin uint64_t _last_gps_origin_time_us{0}; ///< time the origin was last set (uSec) float _gps_alt_ref{0.0f}; ///< WGS-84 height (m) // Variables used to initialise the filter states uint32_t _hgt_counter{0}; ///< number of height samples read during initialisation float _rng_filt_state{0.0f}; ///< filtered height measurement (m) uint32_t _mag_counter{0}; ///< number of magnetometer samples read during initialisation uint32_t _ev_counter{0}; ///< number of external vision samples read during initialisation uint64_t _time_last_mag{0}; ///< measurement time of last magnetomter sample (uSec) Vector3f _mag_filt_state; ///< filtered magnetometer measurement (Gauss) Vector3f _delVel_sum; ///< summed delta velocity (m/sec) float _hgt_sensor_offset{0.0f}; ///< set as necessary if desired to maintain the same height after a height reset (m) float _baro_hgt_offset{0.0f}; ///< baro height reading at the local NED origin (m) // Variables used to control activation of post takeoff functionality float _last_on_ground_posD{0.0f}; ///< last vertical position when the in_air status was false (m) bool _flt_mag_align_complete{false}; ///< true when the in-flight mag field alignment has been completed bool _flt_mag_align_converging{false}; ///< true when the in-flight mag field post alignment convergence is being performd uint64_t _flt_mag_align_start_time{0}; ///< time that inflight magnetic field alignment started (uSec) uint64_t _time_last_movement{0}; ///< last system time that sufficient movement to use 3-axis magnetometer fusion was detected (uSec) float _saved_mag_variance[6] {}; ///< magnetic field state variances that have been saved for use at the next initialisation (Gauss**2) bool _velpos_reset_request{false}; ///< true when a large yaw error has been fixed and a velocity and position state reset is required gps_check_fail_status_u _gps_check_fail_status{}; // variables used to inhibit accel bias learning bool _accel_bias_inhibit{false}; ///< true when the accel bias learning is being inhibited Vector3f _accel_vec_filt{}; ///< acceleration vector after application of a low pass filter (m/sec**2) float _accel_mag_filt{0.0f}; ///< acceleration magnitude after application of a decaying envelope filter (rad/sec) float _ang_rate_mag_filt{0.0f}; ///< angular rate magnitude after application of a decaying envelope filter (rad/sec) Vector3f _prev_dvel_bias_var; ///< saved delta velocity XYZ bias variances (m/sec)**2 // Terrain height state estimation float _terrain_vpos{0.0f}; ///< estimated vertical position of the terrain underneath the vehicle in local NED frame (m) float _terrain_var{1e4f}; ///< variance of terrain position estimate (m**2) float _hagl_innov{0.0f}; ///< innovation of the last height above terrain measurement (m) float _hagl_innov_var{0.0f}; ///< innovation variance for the last height above terrain measurement (m**2) uint64_t _time_last_hagl_fuse{0}; ///< last system time that the hagl measurement failed it's checks (uSec) bool _terrain_initialised{false}; ///< true when the terrain estimator has been intialised float _sin_tilt_rng{0.0f}; ///< sine of the range finder tilt rotation about the Y body axis float _cos_tilt_rng{0.0f}; ///< cosine of the range finder tilt rotation about the Y body axis float _R_rng_to_earth_2_2{0.0f}; ///< 2,2 element of the rotation matrix from sensor frame to earth frame bool _range_data_continuous{false}; ///< true when we are receiving range finder data faster than a 2Hz average float _dt_last_range_update_filt_us{0.0f}; ///< filtered value of the delta time elapsed since the last range measurement came into the filter (uSec) bool _hagl_valid{false}; ///< true when the height above ground estimate is valid // height sensor fault status bool _baro_hgt_faulty{false}; ///< true if valid baro data is unavailable for use bool _gps_hgt_faulty{false}; ///< true if valid gps height data is unavailable for use bool _rng_hgt_faulty{false}; ///< true if valid rnage finder height data is unavailable for use int _primary_hgt_source{VDIST_SENSOR_BARO}; ///< specifies primary source of height data // imu fault status uint64_t _time_bad_vert_accel{0}; ///< last time a bad vertical accel was detected (uSec) uint64_t _time_good_vert_accel{0}; ///< last time a good vertical accel was detected (uSec) bool _bad_vert_accel_detected{false}; ///< true when bad vertical accelerometer data has been detected // variables used to control range aid functionality bool _range_aid_mode_enabled{false}; ///< true when range finder can be used in flight as the height reference instead of the primary height sensor bool _range_aid_mode_selected{false}; ///< true when range finder is being used as the height reference instead of the primary height sensor // variables used to check for "stuck" rng data float _rng_check_min_val{0.0f}; ///< minimum value for new rng measurement when being stuck float _rng_check_max_val{0.0f}; ///< maximum value for new rng measurement when being stuck // update the real time complementary filter states. This includes the prediction // and the correction step void calculateOutputStates(); // initialise filter states of both the delayed ekf and the real time complementary filter bool initialiseFilter(void); // initialise ekf covariance matrix void initialiseCovariance(); // predict ekf state void predictState(); // predict ekf covariance void predictCovariance(); // ekf sequential fusion of magnetometer measurements void fuseMag(); // fuse the first euler angle from either a 321 or 312 rotation sequence as the observation (currently measures yaw using the magnetometer) void fuseHeading(); // fuse magnetometer declination measurement void fuseDeclination(); // fuse airspeed measurement void fuseAirspeed(); // fuse synthetic zero sideslip measurement void fuseSideslip(); // fuse body frame drag specific forces for multi-rotor wind estimation void fuseDrag(); // fuse velocity and position measurements (also barometer height) void fuseVelPosHeight(); // reset velocity states of the ekf bool resetVelocity(); // fuse optical flow line of sight rate measurements void fuseOptFlow(); // calculate optical flow body angular rate compensation // returns false if bias corrected body rate data is unavailable bool calcOptFlowBodyRateComp(); // initialise the terrain vertical position estimator // return true if the initialisation is successful bool initHagl(); // run the terrain estimator void runTerrainEstimator(); // update the terrain vertical position estimate using a height above ground measurement from the range finder void fuseHagl(); // reset the heading and magnetic field states using the declination and magnetometer measurements // return true if successful bool resetMagHeading(Vector3f &mag_init); // Do a forced re-alignment of the yaw angle to align with the horizontal velocity vector from the GPS. // It is used to align the yaw angle after launch or takeoff for fixed wing vehicle. bool realignYawGPS(); // calculate the magnetic declination to be used by the alignment and fusion processing void calcMagDeclination(); // reset position states of the ekf (only horizontal position) bool resetPosition(); // reset height state of the ekf void resetHeight(); // modify output filter to match the the EKF state at the fusion time horizon void alignOutputFilter(); // update the estimated angular misalignment vector between the EV naigration frame and the EKF navigation frame // and update the rotation matrix which transforms EV navigation frame measurements into NED void calcExtVisRotMat(); // reset the estimated angular misalignment vector between the EV naigration frame and the EKF navigation frame // and reset the rotation matrix which transforms EV navigation frame measurements into NED void resetExtVisRotMat(); // limit the diagonal of the covariance matrix void fixCovarianceErrors(); // make ekf covariance matrix symmetric between a nominated state indexe range void makeSymmetrical(float (&cov_mat)[_k_num_states][_k_num_states], uint8_t first, uint8_t last); // constrain the ekf states void constrainStates(); // generic function which will perform a fusion step given a kalman gain K // and a scalar innovation value void fuse(float *K, float innovation); // calculate the earth rotation vector from a given latitude void calcEarthRateNED(Vector3f &omega, double lat_rad) const; // return true id the GPS quality is good enough to set an origin and start aiding bool gps_is_good(struct gps_message *gps); // Control the filter fusion modes void controlFusionModes(); // control fusion of external vision observations void controlExternalVisionFusion(); // control fusion of optical flow observtions void controlOpticalFlowFusion(); // control fusion of GPS observations void controlGpsFusion(); // control fusion of magnetometer observations void controlMagFusion(); // control fusion of range finder observations void controlRangeFinderFusion(); // control fusion of air data observations void controlAirDataFusion(); // control fusion of synthetic sideslip observations void controlBetaFusion(); // control fusion of multi-rotor drag specific force observations void controlDragFusion(); // control fusion of pressure altitude observations void controlBaroFusion(); // control fusion of velocity and position observations void controlVelPosFusion(); // control fusion of auxiliary velocity observations void controlAuxVelFusion(); // control for height sensor timeouts, sensor changes and state resets void controlHeightSensorTimeouts(); // control for combined height fusion mode (implemented for switching between baro and range height) void controlHeightFusion(); // determine if flight condition is suitable so use range finder instead of the primary height senor void rangeAidConditionsMet(); // check for "stuck" range finder measurements when rng was not valid for certain period void checkForStuckRange(); // return the square of two floating point numbers - used in auto coded sections inline float sq(float var) { return var * var; } // set control flags to use baro height void setControlBaroHeight(); // set control flags to use range height void setControlRangeHeight(); // set control flags to use GPS height void setControlGPSHeight(); // set control flags to use external vision height void setControlEVHeight(); // zero the specified range of rows in the state covariance matrix void zeroRows(float (&cov_mat)[_k_num_states][_k_num_states], uint8_t first, uint8_t last); // zero the specified range of columns in the state covariance matrix void zeroCols(float (&cov_mat)[_k_num_states][_k_num_states], uint8_t first, uint8_t last); // zero the specified range of off diagonals in the state covariance matrix void zeroOffDiag(float (&cov_mat)[_k_num_states][_k_num_states], uint8_t first, uint8_t last); // zero the specified range of off diagonals in the state covariance matrix // set the diagonals to the supplied value void setDiag(float (&cov_mat)[_k_num_states][_k_num_states], uint8_t first, uint8_t last, float variance); // calculate the measurement variance for the optical flow sensor float calcOptFlowMeasVar(); // rotate quaternion covariances into variances for an equivalent rotation vector Vector3f calcRotVecVariances(); // initialise the quaternion covariances using rotation vector variances void initialiseQuatCovariances(Vector3f &rot_vec_var); // perform a limited reset of the magnetic field state covariances void resetMagCovariance(); // perform a limited reset of the wind state covariances void resetWindCovariance(); // perform a reset of the wind states void resetWindStates(); // check that the range finder data is continuous void checkRangeDataContinuity(); };