ardupilot/libraries/AP_NavEKF2/AP_NavEKF2.h

/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
/*
  24 state EKF based on https://github.com/priseborough/InertialNav
  Converted from Matlab to C++ by Paul Riseborough

  EKF Tuning parameters refactored by Tom Cauchois

  This program is free software: you can redistribute it and/or modify
  it under the terms of the GNU General Public License as published by
  the Free Software Foundation, either version 3 of the License, or
  (at your option) any later version.

  This program is distributed in the hope that it will be useful,
  but WITHOUT ANY WARRANTY; without even the implied warranty of
  MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
  GNU General Public License for more details.

  You should have received a copy of the GNU General Public License
  along with this program.  If not, see <http://www.gnu.org/licenses/>.
 */

#ifndef AP_NavEKF2_Tuning
#define AP_NavEKF2_Tuning

#include <AP_Math/AP_Math.h>
#include <AP_Param/AP_Param.h>
#include <GCS_MAVLink/GCS_MAVLink.h>
#include <AP_NavEKF/AP_Nav_Common.h>
#include <AP_Baro/AP_Baro.h>
#include <AP_Airspeed/AP_Airspeed.h>
#include <AP_Compass/AP_Compass.h>
#include <AP_NavEKF/AP_Nav_Common.h>
#include <AP_RangeFinder/AP_RangeFinder.h>

class NavEKF2_core;
class AP_AHRS;

class NavEKF2
{
public:
    friend class NavEKF2_core;
    static const struct AP_Param::GroupInfo var_info[];

    NavEKF2(const AP_AHRS *ahrs, AP_Baro &baro, const RangeFinder &rng);

    // allow logging to determine the number of active cores
    uint8_t activeCores(void) const {
        return num_cores;
    }

    // Initialise the filter
    bool InitialiseFilter(void);

    // Update Filter States - this should be called whenever new IMU data is available
    void UpdateFilter(void);

    // Check basic filter health metrics and return a consolidated health status
    bool healthy(void) const;

    // returns the index of the primary core
    // return -1 if no primary core selected
    int8_t getPrimaryCoreIndex(void) const;

    // Return the last calculated NED position relative to the reference point (m) for the specified instance.
    // An out of range instance (eg -1) returns data for the the primary instance
    // If a calculated solution is not available, use the best available data and return false
    // If false returned, do not use for flight control
    bool getPosNED(int8_t instance, Vector3f &pos);

    // return NED velocity in m/s for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getVelNED(int8_t instance, Vector3f &vel);

    // Return the rate of change of vertical position in the down diection (dPosD/dt) in m/s for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    // This can be different to the z component of the EKF velocity state because it will fluctuate with height errors and corrections in the EKF
    // but will always be kinematically consistent with the z component of the EKF position state
    float getPosDownDerivative(int8_t instance);

    // This returns the specific forces in the NED frame
    void getAccelNED(Vector3f &accelNED) const;

    // return body axis gyro bias estimates in rad/sec for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getGyroBias(int8_t instance, Vector3f &gyroBias);

    // return body axis gyro scale factor error as a percentage for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getGyroScaleErrorPercentage(int8_t instance, Vector3f &gyroScale);

    // return tilt error convergence metric for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getTiltError(int8_t instance, float &ang);

    // reset body axis gyro bias estimates
    void resetGyroBias(void);

    // Resets the baro so that it reads zero at the current height
    // Resets the EKF height to zero
    // Adjusts the EKf origin height so that the EKF height + origin height is the same as before
    // Returns true if the height datum reset has been performed
    // If using a range finder for height no reset is performed and it returns false
    bool resetHeightDatum(void);

    // Commands the EKF to not use GPS.
    // This command must be sent prior to arming as it will only be actioned when the filter is in static mode
    // This command is forgotten by the EKF each time it goes back into static mode (eg the vehicle disarms)
    // Returns 0 if command rejected
    // Returns 1 if attitude, vertical velocity and vertical position will be provided
    // Returns 2 if attitude, 3D-velocity, vertical position and relative horizontal position will be provided
    uint8_t setInhibitGPS(void);

    // return the horizontal speed limit in m/s set by optical flow sensor limits
    // return the scale factor to be applied to navigation velocity gains to compensate for increase in velocity noise with height when using optical flow
    void getEkfControlLimits(float &ekfGndSpdLimit, float &ekfNavVelGainScaler) const;

    // return the Z-accel bias estimate in m/s^2 for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getAccelZBias(int8_t instance, float &zbias);

    // return the NED wind speed estimates in m/s (positive is air moving in the direction of the axis)
    // An out of range instance (eg -1) returns data for the the primary instance
    void getWind(int8_t instance, Vector3f &wind);

    // return earth magnetic field estimates in measurement units / 1000 for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getMagNED(int8_t instance, Vector3f &magNED);

    // return body magnetic field estimates in measurement units / 1000 for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getMagXYZ(int8_t instance, Vector3f &magXYZ);

    // return the magnetometer in use for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    uint8_t getActiveMag(int8_t instance);

    // Return estimated magnetometer offsets
    // Return true if magnetometer offsets are valid
    bool getMagOffsets(Vector3f &magOffsets) const;

    // Return the last calculated latitude, longitude and height in WGS-84
    // If a calculated location isn't available, return a raw GPS measurement
    // The status will return true if a calculation or raw measurement is available
    // The getFilterStatus() function provides a more detailed description of data health and must be checked if data is to be used for flight control
    bool getLLH(struct Location &loc) const;

    // return the latitude and longitude and height used to set the NED origin
    // All NED positions calculated by the filter are relative to this location
    // Returns false if the origin has not been set
    bool getOriginLLH(struct Location &loc) const;

    // set the latitude and longitude and height used to set the NED origin
    // All NED positions calcualted by the filter will be relative to this location
    // The origin cannot be set if the filter is in a flight mode (eg vehicle armed)
    // Returns false if the filter has rejected the attempt to set the origin
    bool setOriginLLH(struct Location &loc);

    // return estimated height above ground level
    // return false if ground height is not being estimated.
    bool getHAGL(float &HAGL) const;

    // return the Euler roll, pitch and yaw angle in radians for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getEulerAngles(int8_t instance, Vector3f &eulers);

    // return the transformation matrix from XYZ (body) to NED axes
    void getRotationBodyToNED(Matrix3f &mat) const;

    // return the quaternions defining the rotation from NED to XYZ (body) axes
    void getQuaternion(Quaternion &quat) const;

    // return the innovations for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void  getInnovations(int8_t index, Vector3f &velInnov, Vector3f &posInnov, Vector3f &magInnov, float &tasInnov, float &yawInnov);

    // return the innovation consistency test ratios for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void  getVariances(int8_t instance, float &velVar, float &posVar, float &hgtVar, Vector3f &magVar, float &tasVar, Vector2f &offset);

    // should we use the compass? This is public so it can be used for
    // reporting via ahrs.use_compass()
    bool use_compass(void) const;

    // write the raw optical flow measurements
    // rawFlowQuality is a measured of quality between 0 and 255, with 255 being the best quality
    // rawFlowRates are the optical flow rates in rad/sec about the X and Y sensor axes.
    // rawGyroRates are the sensor rotation rates in rad/sec measured by the sensors internal gyro
    // The sign convention is that a RH physical rotation of the sensor about an axis produces both a positive flow and gyro rate
    // msecFlowMeas is the scheduler time in msec when the optical flow data was received from the sensor.
    void  writeOptFlowMeas(uint8_t &rawFlowQuality, Vector2f &rawFlowRates, Vector2f &rawGyroRates, uint32_t &msecFlowMeas);

    // return data for debugging optical flow fusion for the specified instance
    // An out of range instance (eg -1) returns data for the the primary instance
    void getFlowDebug(int8_t instance, float &varFlow, float &gndOffset, float &flowInnovX, float &flowInnovY, float &auxInnov, float &HAGL, float &rngInnov, float &range, float &gndOffsetErr);

    // called by vehicle code to specify that a takeoff is happening
    // causes the EKF to compensate for expected barometer errors due to ground effect
    void setTakeoffExpected(bool val);

    // called by vehicle code to specify that a touchdown is expected to happen
    // causes the EKF to compensate for expected barometer errors due to ground effect
    void setTouchdownExpected(bool val);

    /*
    return the filter fault status as a bitmasked integer for the specified instance
    An out of range instance (eg -1) returns data for the the primary instance
     0 = quaternions are NaN
     1 = velocities are NaN
     2 = badly conditioned X magnetometer fusion
     3 = badly conditioned Y magnetometer fusion
     5 = badly conditioned Z magnetometer fusion
     6 = badly conditioned airspeed fusion
     7 = badly conditioned synthetic sideslip fusion
     7 = filter is not initialised
    */
    void  getFilterFaults(int8_t instance, uint8_t &faults);

    /*
    return filter timeout status as a bitmasked integer for the specified instance
    An out of range instance (eg -1) returns data for the the primary instance
     0 = position measurement timeout
     1 = velocity measurement timeout
     2 = height measurement timeout
     3 = magnetometer measurement timeout
     5 = unassigned
     6 = unassigned
     7 = unassigned
     7 = unassigned
    */
    void  getFilterTimeouts(int8_t instance, uint8_t &timeouts);

    /*
    return filter gps quality check status for the specified instance
    An out of range instance (eg -1) returns data for the the primary instance
    */
    void  getFilterGpsStatus(int8_t instance, nav_gps_status &faults);

    /*
    return filter status flags for the specified instance
    An out of range instance (eg -1) returns data for the the primary instance
    */
    void  getFilterStatus(int8_t instance, nav_filter_status &status);

    // send an EKF_STATUS_REPORT message to GCS
    void send_status_report(mavlink_channel_t chan);

    // provides the height limit to be observed by the control loops
    // returns false if no height limiting is required
    // this is needed to ensure the vehicle does not fly too high when using optical flow navigation
    bool getHeightControlLimit(float &height) const;

    // return the amount of yaw angle change due to the last yaw angle reset in radians
    // returns the time of the last yaw angle reset or 0 if no reset has ever occurred
    uint32_t getLastYawResetAngle(float &yawAng) const;

    // return the amount of NE position change due to the last position reset in metres
    // returns the time of the last reset or 0 if no reset has ever occurred
    uint32_t getLastPosNorthEastReset(Vector2f &pos) const;

    // return the amount of NE velocity change due to the last velocity reset in metres/sec
    // returns the time of the last reset or 0 if no reset has ever occurred
    uint32_t getLastVelNorthEastReset(Vector2f &vel) const;

    // report any reason for why the backend is refusing to initialise
    const char *prearm_failure_reason(void) const;

    // allow the enable flag to be set by Replay
    void set_enable(bool enable) { _enable.set(enable); }
    
private:
    uint8_t num_cores; // number of allocated cores
    uint8_t primary;   // current primary core
    NavEKF2_core *core = nullptr;
    const AP_AHRS *_ahrs;
    AP_Baro &_baro;
    const RangeFinder &_rng;

    // EKF Mavlink Tuneable Parameters
    AP_Int8  _enable;               // zero to disable EKF2
    AP_Float _gpsHorizVelNoise;     // GPS horizontal velocity measurement noise : m/s
    AP_Float _gpsVertVelNoise;      // GPS vertical velocity measurement noise : m/s
    AP_Float _gpsHorizPosNoise;     // GPS horizontal position measurement noise m
    AP_Float _baroAltNoise;         // Baro height measurement noise : m^2
    AP_Float _magNoise;             // magnetometer measurement noise : gauss
    AP_Float _easNoise;             // equivalent airspeed measurement noise : m/s
    AP_Float _windVelProcessNoise;  // wind velocity state process noise : m/s^2
    AP_Float _wndVarHgtRateScale;   // scale factor applied to wind process noise due to height rate
    AP_Float _magProcessNoise;      // magnetic field process noise : gauss/sec
    AP_Float _gyrNoise;             // gyro process noise : rad/s
    AP_Float _accNoise;             // accelerometer process noise : m/s^2
    AP_Float _gyroBiasProcessNoise; // gyro bias state process noise : rad/s
    AP_Float _accelBiasProcessNoise;// accel bias state process noise : m/s^2
    AP_Int16 _gpsDelay_ms;          // effective average delay of GPS measurements relative to inertial measurement (msec)
    AP_Int16 _hgtDelay_ms;          // effective average delay of Height measurements relative to inertial measurements (msec)
    AP_Int8  _fusionModeGPS;        // 0 = use 3D velocity, 1 = use 2D velocity, 2 = use no velocity
    AP_Int16  _gpsVelInnovGate;     // Percentage number of standard deviations applied to GPS velocity innovation consistency check
    AP_Int16  _gpsPosInnovGate;     // Percentage number of standard deviations applied to GPS position innovation consistency check
    AP_Int16  _hgtInnovGate;        // Percentage number of standard deviations applied to height innovation consistency check
    AP_Int16  _magInnovGate;        // Percentage number of standard deviations applied to magnetometer innovation consistency check
    AP_Int16  _tasInnovGate;        // Percentage number of standard deviations applied to true airspeed innovation consistency check
    AP_Int8  _magCal;               // Sets activation condition for in-flight magnetometer calibration
    AP_Int8 _gpsGlitchRadiusMax;    // Maximum allowed discrepancy between inertial and GPS Horizontal position before GPS glitch is declared : m
    AP_Float _flowNoise;            // optical flow rate measurement noise
    AP_Int16  _flowInnovGate;       // Percentage number of standard deviations applied to optical flow innovation consistency check
    AP_Int8  _flowDelay_ms;         // effective average delay of optical flow measurements rel to IMU (msec)
    AP_Int16  _rngInnovGate;        // Percentage number of standard deviations applied to range finder innovation consistency check
    AP_Float _maxFlowRate;          // Maximum flow rate magnitude that will be accepted by the filter
    AP_Int8 _altSource;             // Primary alt source during optical flow navigation. 0 = use Baro, 1 = use range finder.
    AP_Float _gyroScaleProcessNoise;// gyro scale factor state process noise : 1/s
    AP_Float _rngNoise;             // Range finder noise : m
    AP_Int8 _gpsCheck;              // Bitmask controlling which preflight GPS checks are bypassed
    AP_Int8 _imuMask;               // Bitmask of IMUs to instantiate EKF2 for
    AP_Int16 _gpsCheckScaler;       // Percentage increase to be applied to GPS pre-flight accuracy and drift thresholds

    // Tuning parameters
    const float gpsNEVelVarAccScale;    // Scale factor applied to NE velocity measurement variance due to manoeuvre acceleration
    const float gpsDVelVarAccScale;     // Scale factor applied to vertical velocity measurement variance due to manoeuvre acceleration
    const float gpsPosVarAccScale;      // Scale factor applied to horizontal position measurement variance due to manoeuvre acceleration
    const uint16_t magDelay_ms;         // Magnetometer measurement delay (msec)
    const uint16_t tasDelay_ms;         // Airspeed measurement delay (msec)
    const uint16_t gpsRetryTimeUseTAS_ms;  // GPS retry time with airspeed measurements (msec)
    const uint16_t gpsRetryTimeNoTAS_ms;   // GPS retry time without airspeed measurements (msec)
    const uint16_t gpsFailTimeWithFlow_ms; // If we have no GPs for longer than this and we have optical flow, then we will switch across to using optical flow (msec)
    const uint16_t hgtRetryTimeMode0_ms;   // Height retry time with vertical velocity measurement (msec)
    const uint16_t hgtRetryTimeMode12_ms;  // Height retry time without vertical velocity measurement (msec)
    const uint16_t tasRetryTime_ms;     // True airspeed timeout and retry interval (msec)
    const uint32_t magFailTimeLimit_ms; // number of msec before a magnetometer failing innovation consistency checks is declared failed (msec)
    const float magVarRateScale;        // scale factor applied to magnetometer variance due to angular rate
    const float gyroBiasNoiseScaler;    // scale factor applied to gyro bias state process noise when on ground
    const uint16_t hgtAvg_ms;           // average number of msec between height measurements
    const uint16_t betaAvg_ms;          // average number of msec between synthetic sideslip measurements
    const float covTimeStepMax;         // maximum time (sec) between covariance prediction updates
    const float covDelAngMax;           // maximum delta angle between covariance prediction updates
    const float DCM33FlowMin;           // If Tbn(3,3) is less than this number, optical flow measurements will not be fused as tilt is too high.
    const float fScaleFactorPnoise;     // Process noise added to focal length scale factor state variance at each time step
    const uint8_t flowTimeDeltaAvg_ms;  // average interval between optical flow measurements (msec)
    const uint32_t flowIntervalMax_ms;  // maximum allowable time between flow fusion events
    const uint16_t gndEffectTimeout_ms; // time in msec that ground effect mode is active after being activated
    const float gndEffectBaroScaler;    // scaler applied to the barometer observation variance when ground effect mode is active
    const uint8_t gndGradientSigma;     // RMS terrain gradient percentage assumed by the terrain height estimation
    const uint8_t fusionTimeStep_ms;    // The minimum time interval between covariance predictions and measurement fusions in msec
};

#endif //AP_NavEKF2