/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*- #include #if HAL_CPU_CLASS >= HAL_CPU_CLASS_150 #include "AP_NavEKF2.h" #include "AP_NavEKF2_core.h" #include #include #include extern const AP_HAL::HAL& hal; // Check basic filter health metrics and return a consolidated health status bool NavEKF2_core::healthy(void) const { uint8_t faultInt; getFilterFaults(faultInt); if (faultInt > 0) { return false; } if (velTestRatio > 1 && posTestRatio > 1 && hgtTestRatio > 1) { // all three metrics being above 1 means the filter is // extremely unhealthy. return false; } // Give the filter a second to settle before use if ((imuSampleTime_ms - ekfStartTime_ms) < 1000 ) { return false; } // position and height innovations must be within limits when on-ground and in a static mode of operation float horizErrSq = sq(innovVelPos[3]) + sq(innovVelPos[4]); if (onGround && (PV_AidingMode == AID_NONE) && ((horizErrSq > 1.0f) || (fabsf(hgtInnovFiltState) > 1.0f))) { return false; } // all OK return true; } // Return a consolidated fault score where higher numbers are less healthy // Intended to be used by the front-end to determine which is the primary EKF float NavEKF2_core::faultScore(void) const { float score = 0.0f; // If velocity, position or height measurements are failing consistency checks, this adds to the score if (velTestRatio > 1.0f) { score += velTestRatio-1.0f; } if (posTestRatio > 1.0f) { score += posTestRatio-1.0f; } if (hgtTestRatio > 1.0f) { score += hgtTestRatio-1.0f; } // If the tilt error is excessive this adds to the score const float tiltErrThreshold = 0.05f; if (tiltAlignComplete && yawAlignComplete && tiltErrFilt > tiltErrThreshold) { score += tiltErrFilt / tiltErrThreshold; } return score; } // return data for debugging optical flow fusion void NavEKF2_core::getFlowDebug(float &varFlow, float &gndOffset, float &flowInnovX, float &flowInnovY, float &auxInnov, float &HAGL, float &rngInnov, float &range, float &gndOffsetErr) const { varFlow = MAX(flowTestRatio[0],flowTestRatio[1]); gndOffset = terrainState; flowInnovX = innovOptFlow[0]; flowInnovY = innovOptFlow[1]; auxInnov = auxFlowObsInnov; HAGL = terrainState - stateStruct.position.z; rngInnov = innovRng; range = rangeDataDelayed.rng; gndOffsetErr = sqrtf(Popt); // note Popt is constrained to be non-negative in EstimateTerrainOffset() } // 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 NavEKF2_core::getHeightControlLimit(float &height) const { // only ask for limiting if we are doing optical flow navigation if (frontend->_fusionModeGPS == 3) { // If are doing optical flow nav, ensure the height above ground is within range finder limits after accounting for vehicle tilt and control errors height = MAX(float(frontend->_rng.max_distance_cm()) * 0.007f - 1.0f, 1.0f); // If we are are not using the range finder as the height reference, then compensate for the difference between terrain and EKF origin if (frontend->_altSource != 1) { height -= terrainState; } return true; } else { return false; } } // return the Euler roll, pitch and yaw angle in radians void NavEKF2_core::getEulerAngles(Vector3f &euler) const { outputDataNew.quat.to_euler(euler.x, euler.y, euler.z); euler = euler - _ahrs->get_trim(); } // return body axis gyro bias estimates in rad/sec void NavEKF2_core::getGyroBias(Vector3f &gyroBias) const { if (dtEkfAvg < 1e-6f) { gyroBias.zero(); return; } gyroBias = stateStruct.gyro_bias / dtEkfAvg; } // return body axis gyro scale factor error as a percentage void NavEKF2_core::getGyroScaleErrorPercentage(Vector3f &gyroScale) const { if (!statesInitialised) { gyroScale.x = gyroScale.y = gyroScale.z = 0; return; } gyroScale.x = 100.0f/stateStruct.gyro_scale.x - 100.0f; gyroScale.y = 100.0f/stateStruct.gyro_scale.y - 100.0f; gyroScale.z = 100.0f/stateStruct.gyro_scale.z - 100.0f; } // return tilt error convergence metric void NavEKF2_core::getTiltError(float &ang) const { ang = tiltErrFilt; } // return the transformation matrix from XYZ (body) to NED axes void NavEKF2_core::getRotationBodyToNED(Matrix3f &mat) const { Vector3f trim = _ahrs->get_trim(); outputDataNew.quat.rotation_matrix(mat); mat.rotateXYinv(trim); } // return the quaternions defining the rotation from NED to XYZ (body) axes void NavEKF2_core::getQuaternion(Quaternion& ret) const { ret = outputDataNew.quat; } // 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 NavEKF2_core::getLastYawResetAngle(float &yawAng) const { yawAng = yawResetAngle; return lastYawReset_ms; } // 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 NavEKF2_core::getLastPosNorthEastReset(Vector2f &pos) const { pos = posResetNE; return lastPosReset_ms; } // 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 NavEKF2_core::getLastVelNorthEastReset(Vector2f &vel) const { vel = velResetNE; return lastVelReset_ms; } // return the NED wind speed estimates in m/s (positive is air moving in the direction of the axis) void NavEKF2_core::getWind(Vector3f &wind) const { wind.x = stateStruct.wind_vel.x; wind.y = stateStruct.wind_vel.y; wind.z = 0.0f; // currently don't estimate this } // return NED velocity in m/s // void NavEKF2_core::getVelNED(Vector3f &vel) const { vel = outputDataNew.velocity; } // Return the rate of change of vertical position in the down diection (dPosD/dt) in m/s float NavEKF2_core::getPosDownDerivative(void) const { // return the value calculated from a complmentary filer applied to the EKF height and vertical acceleration return posDownDerivative; } // This returns the specific forces in the NED frame void NavEKF2_core::getAccelNED(Vector3f &accelNED) const { accelNED = velDotNED; accelNED.z -= GRAVITY_MSS; } // return the Z-accel bias estimate in m/s^2 void NavEKF2_core::getAccelZBias(float &zbias) const { if (dtEkfAvg > 0) { zbias = stateStruct.accel_zbias / dtEkfAvg; } else { zbias = 0; } } // Return the last calculated NED position relative to the reference point (m). // if a calculated solution is not available, use the best available data and return false bool NavEKF2_core::getPosNED(Vector3f &pos) const { // The EKF always has a height estimate regardless of mode of operation pos.z = outputDataNew.position.z; // There are three modes of operation, absolute position (GPS fusion), relative position (optical flow fusion) and constant position (no position estimate available) nav_filter_status status; getFilterStatus(status); if (PV_AidingMode != AID_NONE) { // This is the normal mode of operation where we can use the EKF position states pos.x = outputDataNew.position.x; pos.y = outputDataNew.position.y; return true; } else { // In constant position mode the EKF position states are at the origin, so we cannot use them as a position estimate if(validOrigin) { if ((_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_2D)) { // If the origin has been set and we have GPS, then return the GPS position relative to the origin const struct Location &gpsloc = _ahrs->get_gps().location(); Vector2f tempPosNE = location_diff(EKF_origin, gpsloc); pos.x = tempPosNE.x; pos.y = tempPosNE.y; return false; } else { // If no GPS fix is available, all we can do is provide the last known position pos.x = outputDataNew.position.x; pos.y = outputDataNew.position.y; return false; } } else { // If the origin has not been set, then we have no means of providing a relative position pos.x = 0.0f; pos.y = 0.0f; return false; } } return false; } // return the estimated height above ground level bool NavEKF2_core::getHAGL(float &HAGL) const { HAGL = terrainState - outputDataNew.position.z; // If we know the terrain offset and altitude, then we have a valid height above ground estimate return !hgtTimeout && gndOffsetValid && healthy(); } // 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 NavEKF2_core::getLLH(struct Location &loc) const { if(validOrigin) { // Altitude returned is an absolute altitude relative to the WGS-84 spherioid loc.alt = EKF_origin.alt - outputDataNew.position.z*100; loc.flags.relative_alt = 0; loc.flags.terrain_alt = 0; // there are three modes of operation, absolute position (GPS fusion), relative position (optical flow fusion) and constant position (no aiding) nav_filter_status status; getFilterStatus(status); if (status.flags.horiz_pos_abs || status.flags.horiz_pos_rel) { loc.lat = EKF_origin.lat; loc.lng = EKF_origin.lng; location_offset(loc, outputDataNew.position.x, outputDataNew.position.y); return true; } else { // we could be in constant position mode becasue the vehicle has taken off without GPS, or has lost GPS // in this mode we cannot use the EKF states to estimate position so will return the best available data if ((_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_2D)) { // we have a GPS position fix to return const struct Location &gpsloc = _ahrs->get_gps().location(); loc.lat = gpsloc.lat; loc.lng = gpsloc.lng; return true; } else { // if no GPS fix, provide last known position before entering the mode location_offset(loc, lastKnownPositionNE.x, lastKnownPositionNE.y); return false; } } } else { // If no origin has been defined for the EKF, then we cannot use its position states so return a raw // GPS reading if available and return false if ((_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_3D)) { const struct Location &gpsloc = _ahrs->get_gps().location(); loc = gpsloc; loc.flags.relative_alt = 0; loc.flags.terrain_alt = 0; } return false; } } // 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 NavEKF2_core::getEkfControlLimits(float &ekfGndSpdLimit, float &ekfNavVelGainScaler) const { if (PV_AidingMode == AID_RELATIVE) { // allow 1.0 rad/sec margin for angular motion ekfGndSpdLimit = MAX((frontend->_maxFlowRate - 1.0f), 0.0f) * MAX((terrainState - stateStruct.position[2]), rngOnGnd); // use standard gains up to 5.0 metres height and reduce above that ekfNavVelGainScaler = 4.0f / MAX((terrainState - stateStruct.position[2]),4.0f); } else { ekfGndSpdLimit = 400.0f; //return 80% of max filter speed ekfNavVelGainScaler = 1.0f; } } // return the LLH location of the filters NED origin bool NavEKF2_core::getOriginLLH(struct Location &loc) const { if (validOrigin) { loc = EKF_origin; } return validOrigin; } // return earth magnetic field estimates in measurement units / 1000 void NavEKF2_core::getMagNED(Vector3f &magNED) const { magNED = stateStruct.earth_magfield * 1000.0f; } // return body magnetic field estimates in measurement units / 1000 void NavEKF2_core::getMagXYZ(Vector3f &magXYZ) const { magXYZ = stateStruct.body_magfield*1000.0f; } // return the index for the active magnetometer uint8_t NavEKF2_core::getActiveMag() const { return (uint8_t)magSelectIndex; } // return the innovations for the NED Pos, NED Vel, XYZ Mag and Vtas measurements void NavEKF2_core::getInnovations(Vector3f &velInnov, Vector3f &posInnov, Vector3f &magInnov, float &tasInnov, float &yawInnov) const { velInnov.x = innovVelPos[0]; velInnov.y = innovVelPos[1]; velInnov.z = innovVelPos[2]; posInnov.x = innovVelPos[3]; posInnov.y = innovVelPos[4]; posInnov.z = innovVelPos[5]; magInnov.x = 1e3f*innovMag[0]; // Convert back to sensor units magInnov.y = 1e3f*innovMag[1]; // Convert back to sensor units magInnov.z = 1e3f*innovMag[2]; // Convert back to sensor units tasInnov = innovVtas; yawInnov = innovYaw; } // return the innovation consistency test ratios for the velocity, position, magnetometer and true airspeed measurements // this indicates the amount of margin available when tuning the various error traps // also return the delta in position due to the last position reset void NavEKF2_core::getVariances(float &velVar, float &posVar, float &hgtVar, Vector3f &magVar, float &tasVar, Vector2f &offset) const { velVar = sqrtf(velTestRatio); posVar = sqrtf(posTestRatio); hgtVar = sqrtf(hgtTestRatio); // If we are using simple compass yaw fusion, populate all three components with the yaw test ratio to provide an equivalent output magVar.x = sqrtf(MAX(magTestRatio.x,yawTestRatio)); magVar.y = sqrtf(MAX(magTestRatio.y,yawTestRatio)); magVar.z = sqrtf(MAX(magTestRatio.z,yawTestRatio)); tasVar = sqrtf(tasTestRatio); offset = posResetNE; } /* return the filter fault status as a bitmasked integer 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 NavEKF2_core::getFilterFaults(uint8_t &faults) const { faults = (stateStruct.quat.is_nan()<<0 | stateStruct.velocity.is_nan()<<1 | faultStatus.bad_xmag<<2 | faultStatus.bad_ymag<<3 | faultStatus.bad_zmag<<4 | faultStatus.bad_airspeed<<5 | faultStatus.bad_sideslip<<6 | !statesInitialised<<7); } /* return filter timeout status as a bitmasked integer 0 = position measurement timeout 1 = velocity measurement timeout 2 = height measurement timeout 3 = magnetometer measurement timeout 4 = true airspeed measurement timeout 5 = unassigned 6 = unassigned 7 = unassigned */ void NavEKF2_core::getFilterTimeouts(uint8_t &timeouts) const { timeouts = (posTimeout<<0 | velTimeout<<1 | hgtTimeout<<2 | magTimeout<<3 | tasTimeout<<4); } /* Return a filter function status that indicates: Which outputs are valid If the filter has detected takeoff If the filter has activated the mode that mitigates against ground effect static pressure errors If GPS data is being used */ void NavEKF2_core::getFilterStatus(nav_filter_status &status) const { // init return value status.value = 0; bool doingFlowNav = (PV_AidingMode == AID_RELATIVE) && flowDataValid; bool doingWindRelNav = !tasTimeout && assume_zero_sideslip(); bool doingNormalGpsNav = !posTimeout && (PV_AidingMode == AID_ABSOLUTE); bool someVertRefData = (!velTimeout && useGpsVertVel) || !hgtTimeout; bool someHorizRefData = !(velTimeout && posTimeout && tasTimeout) || doingFlowNav; bool optFlowNavPossible = flowDataValid && (frontend->_fusionModeGPS == 3); bool gpsNavPossible = !gpsNotAvailable && (PV_AidingMode == AID_ABSOLUTE) && gpsGoodToAlign; bool filterHealthy = healthy() && tiltAlignComplete && yawAlignComplete; // If GPS height useage is specified, height is considered to be inaccurate until the GPS passes all checks bool hgtNotAccurate = (frontend->_altSource == 2) && !validOrigin; // set individual flags status.flags.attitude = !stateStruct.quat.is_nan() && filterHealthy; // attitude valid (we need a better check) status.flags.horiz_vel = someHorizRefData && filterHealthy; // horizontal velocity estimate valid status.flags.vert_vel = someVertRefData && filterHealthy; // vertical velocity estimate valid status.flags.horiz_pos_rel = ((doingFlowNav && gndOffsetValid) || doingWindRelNav || doingNormalGpsNav) && filterHealthy; // relative horizontal position estimate valid status.flags.horiz_pos_abs = doingNormalGpsNav && filterHealthy; // absolute horizontal position estimate valid status.flags.vert_pos = !hgtTimeout && filterHealthy && !hgtNotAccurate; // vertical position estimate valid status.flags.terrain_alt = gndOffsetValid && filterHealthy; // terrain height estimate valid status.flags.const_pos_mode = (PV_AidingMode == AID_NONE) && filterHealthy; // constant position mode status.flags.pred_horiz_pos_rel = (optFlowNavPossible || gpsNavPossible) && filterHealthy; // we should be able to estimate a relative position when we enter flight mode status.flags.pred_horiz_pos_abs = gpsNavPossible && filterHealthy; // we should be able to estimate an absolute position when we enter flight mode status.flags.takeoff_detected = takeOffDetected; // takeoff for optical flow navigation has been detected status.flags.takeoff = expectGndEffectTakeoff; // The EKF has been told to expect takeoff and is in a ground effect mitigation mode status.flags.touchdown = expectGndEffectTouchdown; // The EKF has been told to detect touchdown and is in a ground effect mitigation mode status.flags.using_gps = (imuSampleTime_ms - lastPosPassTime_ms) < 4000; status.flags.gps_glitching = !gpsAccuracyGood; // The GPS is glitching } /* return filter gps quality check status */ void NavEKF2_core::getFilterGpsStatus(nav_gps_status &faults) const { // init return value faults.value = 0; // set individual flags faults.flags.bad_sAcc = gpsCheckStatus.bad_sAcc; // reported speed accuracy is insufficient faults.flags.bad_hAcc = gpsCheckStatus.bad_hAcc; // reported horizontal position accuracy is insufficient faults.flags.bad_yaw = gpsCheckStatus.bad_yaw; // EKF heading accuracy is too large for GPS use faults.flags.bad_sats = gpsCheckStatus.bad_sats; // reported number of satellites is insufficient faults.flags.bad_horiz_drift = gpsCheckStatus.bad_horiz_drift; // GPS horizontal drift is too large to start using GPS (check assumes vehicle is static) faults.flags.bad_hdop = gpsCheckStatus.bad_hdop; // reported HDoP is too large to start using GPS faults.flags.bad_vert_vel = gpsCheckStatus.bad_vert_vel; // GPS vertical speed is too large to start using GPS (check assumes vehicle is static) faults.flags.bad_fix = gpsCheckStatus.bad_fix; // The GPS cannot provide the 3D fix required faults.flags.bad_horiz_vel = gpsCheckStatus.bad_horiz_vel; // The GPS horizontal speed is excessive (check assumes the vehicle is static) } // send an EKF_STATUS message to GCS void NavEKF2_core::send_status_report(mavlink_channel_t chan) { // get filter status nav_filter_status filt_state; getFilterStatus(filt_state); // prepare flags uint16_t flags = 0; if (filt_state.flags.attitude) { flags |= EKF_ATTITUDE; } if (filt_state.flags.horiz_vel) { flags |= EKF_VELOCITY_HORIZ; } if (filt_state.flags.vert_vel) { flags |= EKF_VELOCITY_VERT; } if (filt_state.flags.horiz_pos_rel) { flags |= EKF_POS_HORIZ_REL; } if (filt_state.flags.horiz_pos_abs) { flags |= EKF_POS_HORIZ_ABS; } if (filt_state.flags.vert_pos) { flags |= EKF_POS_VERT_ABS; } if (filt_state.flags.terrain_alt) { flags |= EKF_POS_VERT_AGL; } if (filt_state.flags.const_pos_mode) { flags |= EKF_CONST_POS_MODE; } if (filt_state.flags.pred_horiz_pos_rel) { flags |= EKF_PRED_POS_HORIZ_REL; } if (filt_state.flags.pred_horiz_pos_abs) { flags |= EKF_PRED_POS_HORIZ_ABS; } // get variances float velVar, posVar, hgtVar, tasVar; Vector3f magVar; Vector2f offset; getVariances(velVar, posVar, hgtVar, magVar, tasVar, offset); // send message mavlink_msg_ekf_status_report_send(chan, flags, velVar, posVar, hgtVar, magVar.length(), tasVar); } // report the reason for why the backend is refusing to initialise const char *NavEKF2_core::prearm_failure_reason(void) const { if (imuSampleTime_ms - lastGpsVelFail_ms > 10000) { // we are not failing return nullptr; } return prearm_fail_string; } // report the number of frames lapsed since the last state prediction // this is used by other instances to level load uint8_t NavEKF2_core::getFramesSincePredict(void) const { return framesSincePredict; } #endif // HAL_CPU_CLASS