mirror of https://github.com/ArduPilot/ardupilot
553 lines
20 KiB
C++
553 lines
20 KiB
C++
/// -*- tab-width: 4; Mode: C++; c-basic-offset: 4; indent-tabs-mode: nil -*-
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#include <AP_HAL/AP_HAL.h>
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#if HAL_CPU_CLASS >= HAL_CPU_CLASS_150
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#include "AP_NavEKF2.h"
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#include "AP_NavEKF2_core.h"
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#include <AP_AHRS/AP_AHRS.h>
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#include <AP_Vehicle/AP_Vehicle.h>
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#include <stdio.h>
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extern const AP_HAL::HAL& hal;
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// Check basic filter health metrics and return a consolidated health status
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bool NavEKF2_core::healthy(void) const
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{
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uint16_t faultInt;
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getFilterFaults(faultInt);
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if (faultInt > 0) {
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return false;
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}
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if (velTestRatio > 1 && posTestRatio > 1 && hgtTestRatio > 1) {
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// all three metrics being above 1 means the filter is
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// extremely unhealthy.
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return false;
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}
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// Give the filter a second to settle before use
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if ((imuSampleTime_ms - ekfStartTime_ms) < 1000 ) {
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return false;
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}
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// position and height innovations must be within limits when on-ground and in a static mode of operation
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float horizErrSq = sq(innovVelPos[3]) + sq(innovVelPos[4]);
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if (onGround && (PV_AidingMode == AID_NONE) && ((horizErrSq > 1.0f) || (fabsf(hgtInnovFiltState) > 1.0f))) {
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return false;
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}
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// all OK
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return true;
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}
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// Return a consolidated fault score where higher numbers are less healthy
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// Intended to be used by the front-end to determine which is the primary EKF
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float NavEKF2_core::faultScore(void) const
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{
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float score = 0.0f;
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// If velocity, position or height measurements are failing consistency checks, this adds to the score
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if (velTestRatio > 1.0f) {
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score += velTestRatio-1.0f;
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}
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if (posTestRatio > 1.0f) {
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score += posTestRatio-1.0f;
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}
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if (hgtTestRatio > 1.0f) {
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score += hgtTestRatio-1.0f;
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}
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// If the tilt error is excessive this adds to the score
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const float tiltErrThreshold = 0.05f;
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if (tiltAlignComplete && yawAlignComplete && tiltErrFilt > tiltErrThreshold) {
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score += tiltErrFilt / tiltErrThreshold;
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}
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return score;
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}
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// return data for debugging optical flow fusion
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void NavEKF2_core::getFlowDebug(float &varFlow, float &gndOffset, float &flowInnovX, float &flowInnovY, float &auxInnov, float &HAGL, float &rngInnov, float &range, float &gndOffsetErr) const
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{
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varFlow = MAX(flowTestRatio[0],flowTestRatio[1]);
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gndOffset = terrainState;
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flowInnovX = innovOptFlow[0];
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flowInnovY = innovOptFlow[1];
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auxInnov = auxFlowObsInnov;
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HAGL = terrainState - stateStruct.position.z;
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rngInnov = innovRng;
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range = rangeDataDelayed.rng;
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gndOffsetErr = sqrtf(Popt); // note Popt is constrained to be non-negative in EstimateTerrainOffset()
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}
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// provides the height limit to be observed by the control loops
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// returns false if no height limiting is required
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// this is needed to ensure the vehicle does not fly too high when using optical flow navigation
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bool NavEKF2_core::getHeightControlLimit(float &height) const
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{
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// only ask for limiting if we are doing optical flow navigation
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if (frontend->_fusionModeGPS == 3) {
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// If are doing optical flow nav, ensure the height above ground is within range finder limits after accounting for vehicle tilt and control errors
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height = MAX(float(frontend->_rng.max_distance_cm()) * 0.007f - 1.0f, 1.0f);
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// If we are are not using the range finder as the height reference, then compensate for the difference between terrain and EKF origin
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if (frontend->_altSource != 1) {
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height -= terrainState;
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}
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return true;
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} else {
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return false;
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}
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}
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// return the Euler roll, pitch and yaw angle in radians
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void NavEKF2_core::getEulerAngles(Vector3f &euler) const
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{
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outputDataNew.quat.to_euler(euler.x, euler.y, euler.z);
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euler = euler - _ahrs->get_trim();
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}
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// return body axis gyro bias estimates in rad/sec
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void NavEKF2_core::getGyroBias(Vector3f &gyroBias) const
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{
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if (dtEkfAvg < 1e-6f) {
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gyroBias.zero();
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return;
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}
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gyroBias = stateStruct.gyro_bias / dtEkfAvg;
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}
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// return body axis gyro scale factor error as a percentage
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void NavEKF2_core::getGyroScaleErrorPercentage(Vector3f &gyroScale) const
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{
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if (!statesInitialised) {
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gyroScale.x = gyroScale.y = gyroScale.z = 0;
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return;
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}
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gyroScale.x = 100.0f/stateStruct.gyro_scale.x - 100.0f;
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gyroScale.y = 100.0f/stateStruct.gyro_scale.y - 100.0f;
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gyroScale.z = 100.0f/stateStruct.gyro_scale.z - 100.0f;
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}
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// return tilt error convergence metric
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void NavEKF2_core::getTiltError(float &ang) const
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{
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ang = tiltErrFilt;
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}
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// return the transformation matrix from XYZ (body) to NED axes
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void NavEKF2_core::getRotationBodyToNED(Matrix3f &mat) const
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{
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Vector3f trim = _ahrs->get_trim();
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outputDataNew.quat.rotation_matrix(mat);
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mat.rotateXYinv(trim);
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}
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// return the quaternions defining the rotation from NED to XYZ (body) axes
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void NavEKF2_core::getQuaternion(Quaternion& ret) const
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{
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ret = outputDataNew.quat;
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}
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// return the amount of yaw angle change due to the last yaw angle reset in radians
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// returns the time of the last yaw angle reset or 0 if no reset has ever occurred
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uint32_t NavEKF2_core::getLastYawResetAngle(float &yawAng) const
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{
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yawAng = yawResetAngle;
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return lastYawReset_ms;
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}
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// return the amount of NE position change due to the last position reset in metres
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// returns the time of the last reset or 0 if no reset has ever occurred
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uint32_t NavEKF2_core::getLastPosNorthEastReset(Vector2f &pos) const
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{
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pos = posResetNE;
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return lastPosReset_ms;
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}
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// return the amount of NE velocity change due to the last velocity reset in metres/sec
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// returns the time of the last reset or 0 if no reset has ever occurred
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uint32_t NavEKF2_core::getLastVelNorthEastReset(Vector2f &vel) const
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{
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vel = velResetNE;
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return lastVelReset_ms;
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}
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// return the NED wind speed estimates in m/s (positive is air moving in the direction of the axis)
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void NavEKF2_core::getWind(Vector3f &wind) const
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{
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wind.x = stateStruct.wind_vel.x;
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wind.y = stateStruct.wind_vel.y;
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wind.z = 0.0f; // currently don't estimate this
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}
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// return NED velocity in m/s
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//
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void NavEKF2_core::getVelNED(Vector3f &vel) const
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{
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vel = outputDataNew.velocity;
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}
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// Return the rate of change of vertical position in the down diection (dPosD/dt) in m/s
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float NavEKF2_core::getPosDownDerivative(void) const
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{
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// return the value calculated from a complmentary filer applied to the EKF height and vertical acceleration
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return posDownDerivative;
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}
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// This returns the specific forces in the NED frame
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void NavEKF2_core::getAccelNED(Vector3f &accelNED) const {
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accelNED = velDotNED;
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accelNED.z -= GRAVITY_MSS;
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}
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// return the Z-accel bias estimate in m/s^2
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void NavEKF2_core::getAccelZBias(float &zbias) const {
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if (dtEkfAvg > 0) {
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zbias = stateStruct.accel_zbias / dtEkfAvg;
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} else {
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zbias = 0;
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}
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}
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// Write the last estimated NE position relative to the reference point (m).
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// Return true if the estimate is valid
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bool NavEKF2_core::getPosNE(Vector2f &posNE) const
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{
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// There are three modes of operation, absolute position (GPS fusion), relative position (optical flow fusion) and constant position (no position estimate available)
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if (PV_AidingMode != AID_NONE) {
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// This is the normal mode of operation where we can use the EKF position states
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posNE.x = outputDataNew.position.x;
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posNE.y = outputDataNew.position.y;
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return true;
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} else {
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// In constant position mode the EKF position states are at the origin, so we cannot use them as a position estimate
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if(validOrigin) {
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if ((_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_2D)) {
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// If the origin has been set and we have GPS, then return the GPS position relative to the origin
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const struct Location &gpsloc = _ahrs->get_gps().location();
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Vector2f tempPosNE = location_diff(EKF_origin, gpsloc);
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posNE.x = tempPosNE.x;
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posNE.y = tempPosNE.y;
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return false;
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} else {
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// If no GPS fix is available, all we can do is provide the last known position
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posNE.x = outputDataNew.position.x;
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posNE.y = outputDataNew.position.y;
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return false;
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}
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} else {
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// If the origin has not been set, then we have no means of providing a relative position
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posNE.x = 0.0f;
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posNE.y = 0.0f;
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return false;
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}
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}
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return false;
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}
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// Write the last calculated D position relative to the reference point (m).
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// Return true if the estimte is valid
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bool NavEKF2_core::getPosD(float &posD) const
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{
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// The EKF always has a height estimate regardless of mode of operation
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posD = outputDataNew.position.z;
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// Return the current height solution status
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return filterStatus.flags.vert_pos;
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}
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// return the estimated height above ground level
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bool NavEKF2_core::getHAGL(float &HAGL) const
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{
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HAGL = terrainState - outputDataNew.position.z;
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// If we know the terrain offset and altitude, then we have a valid height above ground estimate
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return !hgtTimeout && gndOffsetValid && healthy();
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}
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// Return the last calculated latitude, longitude and height in WGS-84
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// If a calculated location isn't available, return a raw GPS measurement
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// The status will return true if a calculation or raw measurement is available
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// The getFilterStatus() function provides a more detailed description of data health and must be checked if data is to be used for flight control
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bool NavEKF2_core::getLLH(struct Location &loc) const
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{
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if(validOrigin) {
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// Altitude returned is an absolute altitude relative to the WGS-84 spherioid
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loc.alt = EKF_origin.alt - outputDataNew.position.z*100;
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loc.flags.relative_alt = 0;
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loc.flags.terrain_alt = 0;
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// there are three modes of operation, absolute position (GPS fusion), relative position (optical flow fusion) and constant position (no aiding)
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if (filterStatus.flags.horiz_pos_abs || filterStatus.flags.horiz_pos_rel) {
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loc.lat = EKF_origin.lat;
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loc.lng = EKF_origin.lng;
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location_offset(loc, outputDataNew.position.x, outputDataNew.position.y);
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return true;
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} else {
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// we could be in constant position mode because the vehicle has taken off without GPS, or has lost GPS
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// in this mode we cannot use the EKF states to estimate position so will return the best available data
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if ((_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_2D)) {
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// we have a GPS position fix to return
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const struct Location &gpsloc = _ahrs->get_gps().location();
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loc.lat = gpsloc.lat;
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loc.lng = gpsloc.lng;
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return true;
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} else {
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// if no GPS fix, provide last known position before entering the mode
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location_offset(loc, lastKnownPositionNE.x, lastKnownPositionNE.y);
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return false;
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}
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}
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} else {
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// If no origin has been defined for the EKF, then we cannot use its position states so return a raw
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// GPS reading if available and return false
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if ((_ahrs->get_gps().status() >= AP_GPS::GPS_OK_FIX_3D)) {
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const struct Location &gpsloc = _ahrs->get_gps().location();
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loc = gpsloc;
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loc.flags.relative_alt = 0;
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loc.flags.terrain_alt = 0;
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}
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return false;
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}
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}
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// return the horizontal speed limit in m/s set by optical flow sensor limits
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// return the scale factor to be applied to navigation velocity gains to compensate for increase in velocity noise with height when using optical flow
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void NavEKF2_core::getEkfControlLimits(float &ekfGndSpdLimit, float &ekfNavVelGainScaler) const
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{
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if (PV_AidingMode == AID_RELATIVE) {
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// allow 1.0 rad/sec margin for angular motion
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ekfGndSpdLimit = MAX((frontend->_maxFlowRate - 1.0f), 0.0f) * MAX((terrainState - stateStruct.position[2]), rngOnGnd);
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// use standard gains up to 5.0 metres height and reduce above that
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ekfNavVelGainScaler = 4.0f / MAX((terrainState - stateStruct.position[2]),4.0f);
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} else {
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ekfGndSpdLimit = 400.0f; //return 80% of max filter speed
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ekfNavVelGainScaler = 1.0f;
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}
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}
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// return the LLH location of the filters NED origin
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bool NavEKF2_core::getOriginLLH(struct Location &loc) const
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{
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if (validOrigin) {
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loc = EKF_origin;
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}
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return validOrigin;
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}
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// return earth magnetic field estimates in measurement units / 1000
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void NavEKF2_core::getMagNED(Vector3f &magNED) const
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{
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magNED = stateStruct.earth_magfield * 1000.0f;
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}
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// return body magnetic field estimates in measurement units / 1000
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void NavEKF2_core::getMagXYZ(Vector3f &magXYZ) const
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{
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magXYZ = stateStruct.body_magfield*1000.0f;
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}
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// return magnetometer offsets
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// return true if offsets are valid
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bool NavEKF2_core::getMagOffsets(uint8_t mag_idx, Vector3f &magOffsets) const
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{
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// compass offsets are valid if we have finalised magnetic field initialisation, magnetic field learning is not prohibited,
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// primary compass is valid and state variances have converged
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const float maxMagVar = 5E-6f;
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bool variancesConverged = (P[19][19] < maxMagVar) && (P[20][20] < maxMagVar) && (P[21][21] < maxMagVar);
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if ((mag_idx == magSelectIndex) &&
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finalInflightMagInit &&
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!inhibitMagStates &&
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_ahrs->get_compass()->healthy(magSelectIndex) &&
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variancesConverged) {
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magOffsets = _ahrs->get_compass()->get_offsets(magSelectIndex) - stateStruct.body_magfield*1000.0f;
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return true;
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} else {
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magOffsets = _ahrs->get_compass()->get_offsets(magSelectIndex);
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return false;
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}
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}
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// return the index for the active magnetometer
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uint8_t NavEKF2_core::getActiveMag() const
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{
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return (uint8_t)magSelectIndex;
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}
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// return the innovations for the NED Pos, NED Vel, XYZ Mag and Vtas measurements
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void NavEKF2_core::getInnovations(Vector3f &velInnov, Vector3f &posInnov, Vector3f &magInnov, float &tasInnov, float &yawInnov) const
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{
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velInnov.x = innovVelPos[0];
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velInnov.y = innovVelPos[1];
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velInnov.z = innovVelPos[2];
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posInnov.x = innovVelPos[3];
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posInnov.y = innovVelPos[4];
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posInnov.z = innovVelPos[5];
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magInnov.x = 1e3f*innovMag[0]; // Convert back to sensor units
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magInnov.y = 1e3f*innovMag[1]; // Convert back to sensor units
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magInnov.z = 1e3f*innovMag[2]; // Convert back to sensor units
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tasInnov = innovVtas;
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yawInnov = innovYaw;
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}
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// return the innovation consistency test ratios for the velocity, position, magnetometer and true airspeed measurements
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// this indicates the amount of margin available when tuning the various error traps
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// also return the delta in position due to the last position reset
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void NavEKF2_core::getVariances(float &velVar, float &posVar, float &hgtVar, Vector3f &magVar, float &tasVar, Vector2f &offset) const
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{
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velVar = sqrtf(velTestRatio);
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posVar = sqrtf(posTestRatio);
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hgtVar = sqrtf(hgtTestRatio);
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// If we are using simple compass yaw fusion, populate all three components with the yaw test ratio to provide an equivalent output
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magVar.x = sqrtf(MAX(magTestRatio.x,yawTestRatio));
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magVar.y = sqrtf(MAX(magTestRatio.y,yawTestRatio));
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magVar.z = sqrtf(MAX(magTestRatio.z,yawTestRatio));
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tasVar = sqrtf(tasTestRatio);
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offset = posResetNE;
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}
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/*
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return the filter fault status as a bitmasked integer
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0 = quaternions are NaN
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1 = velocities are NaN
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2 = badly conditioned X magnetometer fusion
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3 = badly conditioned Y magnetometer fusion
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5 = badly conditioned Z magnetometer fusion
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6 = badly conditioned airspeed fusion
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7 = badly conditioned synthetic sideslip fusion
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7 = filter is not initialised
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*/
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void NavEKF2_core::getFilterFaults(uint16_t &faults) const
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{
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faults = (stateStruct.quat.is_nan()<<0 |
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stateStruct.velocity.is_nan()<<1 |
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faultStatus.bad_xmag<<2 |
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faultStatus.bad_ymag<<3 |
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faultStatus.bad_zmag<<4 |
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faultStatus.bad_airspeed<<5 |
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faultStatus.bad_sideslip<<6 |
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!statesInitialised<<7);
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}
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/*
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return filter timeout status as a bitmasked integer
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0 = position measurement timeout
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1 = velocity measurement timeout
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2 = height measurement timeout
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3 = magnetometer measurement timeout
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4 = true airspeed measurement timeout
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5 = unassigned
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6 = unassigned
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7 = unassigned
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*/
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void NavEKF2_core::getFilterTimeouts(uint8_t &timeouts) const
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{
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timeouts = (posTimeout<<0 |
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velTimeout<<1 |
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hgtTimeout<<2 |
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magTimeout<<3 |
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tasTimeout<<4);
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}
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// Return the navigation filter status message
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void NavEKF2_core::getFilterStatus(nav_filter_status &status) const
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{
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status = filterStatus;
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}
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/*
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return filter gps quality check status
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*/
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void NavEKF2_core::getFilterGpsStatus(nav_gps_status &faults) const
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{
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// init return value
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faults.value = 0;
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// set individual flags
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faults.flags.bad_sAcc = gpsCheckStatus.bad_sAcc; // reported speed accuracy is insufficient
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faults.flags.bad_hAcc = gpsCheckStatus.bad_hAcc; // reported horizontal position accuracy is insufficient
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faults.flags.bad_yaw = gpsCheckStatus.bad_yaw; // EKF heading accuracy is too large for GPS use
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faults.flags.bad_sats = gpsCheckStatus.bad_sats; // reported number of satellites is insufficient
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faults.flags.bad_horiz_drift = gpsCheckStatus.bad_horiz_drift; // GPS horizontal drift is too large to start using GPS (check assumes vehicle is static)
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faults.flags.bad_hdop = gpsCheckStatus.bad_hdop; // reported HDoP is too large to start using GPS
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faults.flags.bad_vert_vel = gpsCheckStatus.bad_vert_vel; // GPS vertical speed is too large to start using GPS (check assumes vehicle is static)
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faults.flags.bad_fix = gpsCheckStatus.bad_fix; // The GPS cannot provide the 3D fix required
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faults.flags.bad_horiz_vel = gpsCheckStatus.bad_horiz_vel; // The GPS horizontal speed is excessive (check assumes the vehicle is static)
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}
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// send an EKF_STATUS message to GCS
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void NavEKF2_core::send_status_report(mavlink_channel_t chan)
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{
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// prepare flags
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uint16_t flags = 0;
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if (filterStatus.flags.attitude) {
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flags |= EKF_ATTITUDE;
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}
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if (filterStatus.flags.horiz_vel) {
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flags |= EKF_VELOCITY_HORIZ;
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}
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if (filterStatus.flags.vert_vel) {
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flags |= EKF_VELOCITY_VERT;
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}
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if (filterStatus.flags.horiz_pos_rel) {
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flags |= EKF_POS_HORIZ_REL;
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}
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if (filterStatus.flags.horiz_pos_abs) {
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flags |= EKF_POS_HORIZ_ABS;
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}
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if (filterStatus.flags.vert_pos) {
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flags |= EKF_POS_VERT_ABS;
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}
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if (filterStatus.flags.terrain_alt) {
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flags |= EKF_POS_VERT_AGL;
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}
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if (filterStatus.flags.const_pos_mode) {
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|
flags |= EKF_CONST_POS_MODE;
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}
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if (filterStatus.flags.pred_horiz_pos_rel) {
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flags |= EKF_PRED_POS_HORIZ_REL;
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}
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if (filterStatus.flags.pred_horiz_pos_abs) {
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|
flags |= EKF_PRED_POS_HORIZ_ABS;
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}
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|
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// get variances
|
|
float velVar, posVar, hgtVar, tasVar;
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|
Vector3f magVar;
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|
Vector2f offset;
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|
getVariances(velVar, posVar, hgtVar, magVar, tasVar, offset);
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|
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// send message
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mavlink_msg_ekf_status_report_send(chan, flags, velVar, posVar, hgtVar, magVar.length(), sqrtf(auxRngTestRatio));
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|
|
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}
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|
|
|
// 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;
|
|
}
|
|
|
|
// publish output observer angular, velocity and position tracking error
|
|
void NavEKF2_core::getOutputTrackingError(Vector3f &error) const
|
|
{
|
|
error = outputTrackError;
|
|
}
|
|
|
|
#endif // HAL_CPU_CLASS
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