forked from Archive/PX4-Autopilot
Add support for 21 and 23 state estimators. Promoto a number of small delta variables to double
This commit is contained in:
Lorenz Meier
parent
5bf68dad94
commit
b9a3fa60bc
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@ -83,7 +83,7 @@
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#include <mathlib/mathlib.h>
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#include <mavlink/mavlink_log.h>
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#include "estimator.h"
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#include "estimator_21states.h"
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@ -1455,30 +1455,55 @@ FixedwingEstimator::print_status()
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// 16-18: Earth Magnetic Field Vector - gauss (North, East, Down)
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// 19-21: Body Magnetic Field Vector - gauss (X,Y,Z)
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printf("dtIMU: %8.6f IMUmsec: %d\n", (double)_ekf->dtIMU, (int)IMUmsec);
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printf("ref alt: %8.6f\n", (double)_local_pos.ref_alt);
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printf("dvel: %8.6f %8.6f %8.6f accel: %8.6f %8.6f %8.6f\n", (double)_ekf->dVelIMU.x, (double)_ekf->dVelIMU.y, (double)_ekf->dVelIMU.z, (double)_ekf->accel.x, (double)_ekf->accel.y, (double)_ekf->accel.z);
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printf("dang: %8.4f %8.4f %8.4f dang corr: %8.4f %8.4f %8.4f\n" , (double)_ekf->dAngIMU.x, (double)_ekf->dAngIMU.y, (double)_ekf->dAngIMU.z, (double)_ekf->correctedDelAng.x, (double)_ekf->correctedDelAng.y, (double)_ekf->correctedDelAng.z);
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printf("states (quat) [0-3]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[0], (double)_ekf->states[1], (double)_ekf->states[2], (double)_ekf->states[3]);
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printf("states (vel m/s) [4-6]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[4], (double)_ekf->states[5], (double)_ekf->states[6]);
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printf("states (pos m) [7-9]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[7], (double)_ekf->states[8], (double)_ekf->states[9]);
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printf("states (delta ang) [10-12]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[10], (double)_ekf->states[11], (double)_ekf->states[12]);
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printf("states (accel offs) [13]: %8.4f\n", (double)_ekf->states[13]);
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printf("states (wind) [14-15]: %8.4f, %8.4f\n", (double)_ekf->states[14], (double)_ekf->states[15]);
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printf("states (earth mag) [16-18]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[16], (double)_ekf->states[17], (double)_ekf->states[18]);
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printf("states (body mag) [19-21]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[19], (double)_ekf->states[20], (double)_ekf->states[21]);
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printf("states (terrain) [22]: %8.4f\n", (double)_ekf->states[22]);
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printf("states: %s %s %s %s %s %s %s %s %s %s\n",
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(_ekf->statesInitialised) ? "INITIALIZED" : "NON_INIT",
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(_ekf->onGround) ? "ON_GROUND" : "AIRBORNE",
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(_ekf->fuseVelData) ? "FUSE_VEL" : "INH_VEL",
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(_ekf->fusePosData) ? "FUSE_POS" : "INH_POS",
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(_ekf->fuseHgtData) ? "FUSE_HGT" : "INH_HGT",
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(_ekf->fuseMagData) ? "FUSE_MAG" : "INH_MAG",
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(_ekf->fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS",
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(_ekf->useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD",
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(_ekf->useCompass) ? "USE_COMPASS" : "IGN_COMPASS",
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(_ekf->staticMode) ? "STATIC_MODE" : "DYNAMIC_MODE");
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if (n_states == 23) {
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printf("dtIMU: %8.6f IMUmsec: %d\n", (double)_ekf->dtIMU, (int)IMUmsec);
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printf("ref alt: %8.6f\n", (double)_local_pos.ref_alt);
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printf("dvel: %8.6f %8.6f %8.6f accel: %8.6f %8.6f %8.6f\n", (double)_ekf->dVelIMU.x, (double)_ekf->dVelIMU.y, (double)_ekf->dVelIMU.z, (double)_ekf->accel.x, (double)_ekf->accel.y, (double)_ekf->accel.z);
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printf("dang: %8.4f %8.4f %8.4f dang corr: %8.4f %8.4f %8.4f\n" , (double)_ekf->dAngIMU.x, (double)_ekf->dAngIMU.y, (double)_ekf->dAngIMU.z, (double)_ekf->correctedDelAng.x, (double)_ekf->correctedDelAng.y, (double)_ekf->correctedDelAng.z);
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printf("states (quat) [0-3]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[0], (double)_ekf->states[1], (double)_ekf->states[2], (double)_ekf->states[3]);
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printf("states (vel m/s) [4-6]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[4], (double)_ekf->states[5], (double)_ekf->states[6]);
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printf("states (pos m) [7-9]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[7], (double)_ekf->states[8], (double)_ekf->states[9]);
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printf("states (delta ang) [10-12]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[10], (double)_ekf->states[11], (double)_ekf->states[12]);
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printf("states (accel offs) [13]: %8.4f\n", (double)_ekf->states[13]);
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printf("states (wind) [14-15]: %8.4f, %8.4f\n", (double)_ekf->states[14], (double)_ekf->states[15]);
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printf("states (earth mag) [16-18]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[16], (double)_ekf->states[17], (double)_ekf->states[18]);
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printf("states (body mag) [19-21]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[19], (double)_ekf->states[20], (double)_ekf->states[21]);
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printf("states (terrain) [22]: %8.4f\n", (double)_ekf->states[22]);
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printf("states: %s %s %s %s %s %s %s %s %s %s\n",
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(_ekf->statesInitialised) ? "INITIALIZED" : "NON_INIT",
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(_ekf->onGround) ? "ON_GROUND" : "AIRBORNE",
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(_ekf->fuseVelData) ? "FUSE_VEL" : "INH_VEL",
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(_ekf->fusePosData) ? "FUSE_POS" : "INH_POS",
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(_ekf->fuseHgtData) ? "FUSE_HGT" : "INH_HGT",
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(_ekf->fuseMagData) ? "FUSE_MAG" : "INH_MAG",
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(_ekf->fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS",
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(_ekf->useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD",
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(_ekf->useCompass) ? "USE_COMPASS" : "IGN_COMPASS",
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(_ekf->staticMode) ? "STATIC_MODE" : "DYNAMIC_MODE");
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} else {
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printf("dtIMU: %8.6f IMUmsec: %d\n", (double)_ekf->dtIMU, (int)IMUmsec);
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printf("ref alt: %8.6f\n", (double)_local_pos.ref_alt);
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printf("dvel: %8.6f %8.6f %8.6f accel: %8.6f %8.6f %8.6f\n", (double)_ekf->dVelIMU.x, (double)_ekf->dVelIMU.y, (double)_ekf->dVelIMU.z, (double)_ekf->accel.x, (double)_ekf->accel.y, (double)_ekf->accel.z);
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printf("dang: %8.4f %8.4f %8.4f dang corr: %8.4f %8.4f %8.4f\n" , (double)_ekf->dAngIMU.x, (double)_ekf->dAngIMU.y, (double)_ekf->dAngIMU.z, (double)_ekf->correctedDelAng.x, (double)_ekf->correctedDelAng.y, (double)_ekf->correctedDelAng.z);
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printf("states (quat) [0-3]: %8.4f, %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[0], (double)_ekf->states[1], (double)_ekf->states[2], (double)_ekf->states[3]);
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printf("states (vel m/s) [4-6]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[4], (double)_ekf->states[5], (double)_ekf->states[6]);
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printf("states (pos m) [7-9]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[7], (double)_ekf->states[8], (double)_ekf->states[9]);
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printf("states (delta ang) [10-12]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[10], (double)_ekf->states[11], (double)_ekf->states[12]);
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printf("states (wind) [13-14]: %8.4f, %8.4f\n", (double)_ekf->states[13], (double)_ekf->states[14]);
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printf("states (earth mag) [15-17]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[15], (double)_ekf->states[16], (double)_ekf->states[17]);
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printf("states (body mag) [18-20]: %8.4f, %8.4f, %8.4f\n", (double)_ekf->states[18], (double)_ekf->states[19], (double)_ekf->states[20]);
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printf("states: %s %s %s %s %s %s %s %s %s %s\n",
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(_ekf->statesInitialised) ? "INITIALIZED" : "NON_INIT",
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(_ekf->onGround) ? "ON_GROUND" : "AIRBORNE",
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(_ekf->fuseVelData) ? "FUSE_VEL" : "INH_VEL",
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(_ekf->fusePosData) ? "FUSE_POS" : "INH_POS",
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(_ekf->fuseHgtData) ? "FUSE_HGT" : "INH_HGT",
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(_ekf->fuseMagData) ? "FUSE_MAG" : "INH_MAG",
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(_ekf->fuseVtasData) ? "FUSE_VTAS" : "INH_VTAS",
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(_ekf->useAirspeed) ? "USE_AIRSPD" : "IGN_AIRSPD",
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(_ekf->useCompass) ? "USE_COMPASS" : "IGN_COMPASS",
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(_ekf->staticMode) ? "STATIC_MODE" : "DYNAMIC_MODE");
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}
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}
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int FixedwingEstimator::trip_nan() {
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File diff suppressed because it is too large
Load Diff
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@ -0,0 +1,247 @@
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#pragma once
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#include "estimator_utilities.h"
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class AttPosEKF {
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public:
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AttPosEKF();
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~AttPosEKF();
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/* ##############################################
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*
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* M A I N F I L T E R P A R A M E T E R S
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*
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* ########################################### */
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/*
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* parameters are defined here and initialised in
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* the InitialiseParameters() (which is just 20 lines down)
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*/
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float covTimeStepMax; // maximum time allowed between covariance predictions
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float covDelAngMax; // maximum delta angle between covariance predictions
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float rngFinderPitch; // pitch angle of laser range finder in radians. Zero is aligned with the Z body axis. Positive is RH rotation about Y body axis.
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float yawVarScale;
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float windVelSigma;
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float dAngBiasSigma;
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float dVelBiasSigma;
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float magEarthSigma;
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float magBodySigma;
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float gndHgtSigma;
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float vneSigma;
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float vdSigma;
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float posNeSigma;
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float posDSigma;
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float magMeasurementSigma;
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float airspeedMeasurementSigma;
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float gyroProcessNoise;
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float accelProcessNoise;
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float EAS2TAS; // ratio f true to equivalent airspeed
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void InitialiseParameters()
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{
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covTimeStepMax = 0.07f; // maximum time allowed between covariance predictions
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covDelAngMax = 0.02f; // maximum delta angle between covariance predictions
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rngFinderPitch = 0.0f; // pitch angle of laser range finder in radians. Zero is aligned with the Z body axis. Positive is RH rotation about Y body axis.
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EAS2TAS = 1.0f;
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yawVarScale = 1.0f;
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windVelSigma = 0.1f;
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dAngBiasSigma = 5.0e-7f;
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dVelBiasSigma = 1e-4f;
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magEarthSigma = 3.0e-4f;
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magBodySigma = 3.0e-4f;
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gndHgtSigma = 0.02f; // assume 2% terrain gradient 1-sigma
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vneSigma = 0.2f;
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vdSigma = 0.3f;
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posNeSigma = 2.0f;
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posDSigma = 2.0f;
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magMeasurementSigma = 0.05;
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airspeedMeasurementSigma = 1.4f;
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gyroProcessNoise = 1.4544411e-2f;
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accelProcessNoise = 0.5f;
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}
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// Global variables
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float KH[n_states][n_states]; // intermediate result used for covariance updates
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float KHP[n_states][n_states]; // intermediate result used for covariance updates
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float P[n_states][n_states]; // covariance matrix
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float Kfusion[n_states]; // Kalman gains
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float states[n_states]; // state matrix
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float storedStates[n_states][data_buffer_size]; // state vectors stored for the last 50 time steps
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uint32_t statetimeStamp[data_buffer_size]; // time stamp for each state vector stored
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float statesAtVelTime[n_states]; // States at the effective measurement time for posNE and velNED measurements
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float statesAtPosTime[n_states]; // States at the effective measurement time for posNE and velNED measurements
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float statesAtHgtTime[n_states]; // States at the effective measurement time for the hgtMea measurement
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float statesAtMagMeasTime[n_states]; // filter satates at the effective measurement time
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float statesAtVtasMeasTime[n_states]; // filter states at the effective measurement time
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Vector3f correctedDelAng; // delta angles about the xyz body axes corrected for errors (rad)
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Vector3f correctedDelVel; // delta velocities along the XYZ body axes corrected for errors (m/s)
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Vector3f summedDelAng; // summed delta angles about the xyz body axes corrected for errors (rad)
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Vector3f summedDelVel; // summed delta velocities along the XYZ body axes corrected for errors (m/s)
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float accNavMag; // magnitude of navigation accel (- used to adjust GPS obs variance (m/s^2)
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Vector3f earthRateNED; // earths angular rate vector in NED (rad/s)
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Vector3f angRate; // angular rate vector in XYZ body axes measured by the IMU (rad/s)
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Vector3f accel; // acceleration vector in XYZ body axes measured by the IMU (m/s^2)
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Vector3f dVelIMU;
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Vector3f dAngIMU;
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float dtIMU; // time lapsed since the last IMU measurement or covariance update (sec)
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uint8_t fusionModeGPS; // 0 = GPS outputs 3D velocity, 1 = GPS outputs 2D velocity, 2 = GPS outputs no velocity
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float innovVelPos[6]; // innovation output
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float varInnovVelPos[6]; // innovation variance output
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float velNED[3]; // North, East, Down velocity obs (m/s)
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float posNE[2]; // North, East position obs (m)
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float hgtMea; // measured height (m)
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float posNED[3]; // North, East Down position (m)
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float innovMag[3]; // innovation output
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float varInnovMag[3]; // innovation variance output
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Vector3f magData; // magnetometer flux radings in X,Y,Z body axes
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float innovVtas; // innovation output
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float varInnovVtas; // innovation variance output
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float VtasMeas; // true airspeed measurement (m/s)
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float magDeclination;
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float latRef; // WGS-84 latitude of reference point (rad)
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float lonRef; // WGS-84 longitude of reference point (rad)
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float hgtRef; // WGS-84 height of reference point (m)
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Vector3f magBias; // states representing magnetometer bias vector in XYZ body axes
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uint8_t covSkipCount; // Number of state prediction frames (IMU daya updates to skip before doing the covariance prediction
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// GPS input data variables
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float gpsCourse;
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float gpsVelD;
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float gpsLat;
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float gpsLon;
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float gpsHgt;
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uint8_t GPSstatus;
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// Baro input
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float baroHgt;
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bool statesInitialised;
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bool fuseVelData; // this boolean causes the posNE and velNED obs to be fused
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bool fusePosData; // this boolean causes the posNE and velNED obs to be fused
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bool fuseHgtData; // this boolean causes the hgtMea obs to be fused
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bool fuseMagData; // boolean true when magnetometer data is to be fused
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bool fuseVtasData; // boolean true when airspeed data is to be fused
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bool onGround; ///< boolean true when the flight vehicle is on the ground (not flying)
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bool staticMode; ///< boolean true if no position feedback is fused
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bool useAirspeed; ///< boolean true if airspeed data is being used
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bool useCompass; ///< boolean true if magnetometer data is being used
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struct ekf_status_report current_ekf_state;
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struct ekf_status_report last_ekf_error;
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bool numericalProtection;
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unsigned storeIndex;
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void UpdateStrapdownEquationsNED();
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void CovariancePrediction(float dt);
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void FuseVelposNED();
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void FuseMagnetometer();
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void FuseAirspeed();
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void zeroRows(float (&covMat)[n_states][n_states], uint8_t first, uint8_t last);
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void zeroCols(float (&covMat)[n_states][n_states], uint8_t first, uint8_t last);
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void quatNorm(float (&quatOut)[4], const float quatIn[4]);
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// store staes along with system time stamp in msces
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void StoreStates(uint64_t timestamp_ms);
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/**
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* Recall the state vector.
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*
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* Recalls the vector stored at closest time to the one specified by msec
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*
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* @return zero on success, integer indicating the number of invalid states on failure.
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* Does only copy valid states, if the statesForFusion vector was initialized
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* correctly by the caller, the result can be safely used, but is a mixture
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* time-wise where valid states were updated and invalid remained at the old
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* value.
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*/
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int RecallStates(float statesForFusion[n_states], uint64_t msec);
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void ResetStoredStates();
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void quat2Tbn(Mat3f &Tbn, const float (&quat)[4]);
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void calcEarthRateNED(Vector3f &omega, float latitude);
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static void eul2quat(float (&quat)[4], const float (&eul)[3]);
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static void quat2eul(float (&eul)[3], const float (&quat)[4]);
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static void calcvelNED(float (&velNED)[3], float gpsCourse, float gpsGndSpd, float gpsVelD);
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static void calcposNED(float (&posNED)[3], float lat, float lon, float hgt, float latRef, float lonRef, float hgtRef);
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static void calcLLH(float (&posNED)[3], float lat, float lon, float hgt, float latRef, float lonRef, float hgtRef);
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static void quat2Tnb(Mat3f &Tnb, const float (&quat)[4]);
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static float sq(float valIn);
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void OnGroundCheck();
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void CovarianceInit();
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void InitialiseFilter(float (&initvelNED)[3], double referenceLat, double referenceLon, float referenceHgt, float declination);
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float ConstrainFloat(float val, float min, float max);
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void ConstrainVariances();
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void ConstrainStates();
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void ForceSymmetry();
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int CheckAndBound();
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void ResetPosition();
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void ResetVelocity();
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void ZeroVariables();
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void GetFilterState(struct ekf_status_report *state);
|
||||
|
||||
void GetLastErrorState(struct ekf_status_report *last_error);
|
||||
|
||||
bool StatesNaN(struct ekf_status_report *err_report);
|
||||
void FillErrorReport(struct ekf_status_report *err);
|
||||
|
||||
void InitializeDynamic(float (&initvelNED)[3], float declination);
|
||||
|
||||
protected:
|
||||
|
||||
bool FilterHealthy();
|
||||
|
||||
void ResetHeight(void);
|
||||
|
||||
void AttitudeInit(float ax, float ay, float az, float mx, float my, float mz, float declination, float *initQuat);
|
||||
|
||||
};
|
||||
|
||||
uint32_t millis();
|
||||
|
||||
|
|
@ -0,0 +1,139 @@
|
|||
|
||||
#include "estimator_utilities.h"
|
||||
|
||||
// Define EKF_DEBUG here to enable the debug print calls
|
||||
// if the macro is not set, these will be completely
|
||||
// optimized out by the compiler.
|
||||
//#define EKF_DEBUG
|
||||
|
||||
#ifdef EKF_DEBUG
|
||||
#include <stdio.h>
|
||||
|
||||
static void
|
||||
ekf_debug_print(const char *fmt, va_list args)
|
||||
{
|
||||
fprintf(stderr, "%s: ", "[ekf]");
|
||||
vfprintf(stderr, fmt, args);
|
||||
|
||||
fprintf(stderr, "\n");
|
||||
}
|
||||
|
||||
void
|
||||
ekf_debug(const char *fmt, ...)
|
||||
{
|
||||
va_list args;
|
||||
|
||||
va_start(args, fmt);
|
||||
ekf_debug_print(fmt, args);
|
||||
}
|
||||
|
||||
#else
|
||||
|
||||
void ekf_debug(const char *fmt, ...) { while(0){} }
|
||||
#endif
|
||||
|
||||
float Vector3f::length(void) const
|
||||
{
|
||||
return sqrt(x*x + y*y + z*z);
|
||||
}
|
||||
|
||||
void Vector3f::zero(void)
|
||||
{
|
||||
x = 0.0f;
|
||||
y = 0.0f;
|
||||
z = 0.0f;
|
||||
}
|
||||
|
||||
Mat3f::Mat3f() {
|
||||
identity();
|
||||
}
|
||||
|
||||
void Mat3f::identity() {
|
||||
x.x = 1.0f;
|
||||
x.y = 0.0f;
|
||||
x.z = 0.0f;
|
||||
|
||||
y.x = 0.0f;
|
||||
y.y = 1.0f;
|
||||
y.z = 0.0f;
|
||||
|
||||
z.x = 0.0f;
|
||||
z.y = 0.0f;
|
||||
z.z = 1.0f;
|
||||
}
|
||||
|
||||
Mat3f Mat3f::transpose(void) const
|
||||
{
|
||||
Mat3f ret = *this;
|
||||
swap_var(ret.x.y, ret.y.x);
|
||||
swap_var(ret.x.z, ret.z.x);
|
||||
swap_var(ret.y.z, ret.z.y);
|
||||
return ret;
|
||||
}
|
||||
|
||||
// overload + operator to provide a vector addition
|
||||
Vector3f operator+( Vector3f vecIn1, Vector3f vecIn2)
|
||||
{
|
||||
Vector3f vecOut;
|
||||
vecOut.x = vecIn1.x + vecIn2.x;
|
||||
vecOut.y = vecIn1.y + vecIn2.y;
|
||||
vecOut.z = vecIn1.z + vecIn2.z;
|
||||
return vecOut;
|
||||
}
|
||||
|
||||
// overload - operator to provide a vector subtraction
|
||||
Vector3f operator-( Vector3f vecIn1, Vector3f vecIn2)
|
||||
{
|
||||
Vector3f vecOut;
|
||||
vecOut.x = vecIn1.x - vecIn2.x;
|
||||
vecOut.y = vecIn1.y - vecIn2.y;
|
||||
vecOut.z = vecIn1.z - vecIn2.z;
|
||||
return vecOut;
|
||||
}
|
||||
|
||||
// overload * operator to provide a matrix vector product
|
||||
Vector3f operator*( Mat3f matIn, Vector3f vecIn)
|
||||
{
|
||||
Vector3f vecOut;
|
||||
vecOut.x = matIn.x.x*vecIn.x + matIn.x.y*vecIn.y + matIn.x.z*vecIn.z;
|
||||
vecOut.y = matIn.y.x*vecIn.x + matIn.y.y*vecIn.y + matIn.y.z*vecIn.z;
|
||||
vecOut.z = matIn.x.x*vecIn.x + matIn.z.y*vecIn.y + matIn.z.z*vecIn.z;
|
||||
return vecOut;
|
||||
}
|
||||
|
||||
// overload % operator to provide a vector cross product
|
||||
Vector3f operator%( Vector3f vecIn1, Vector3f vecIn2)
|
||||
{
|
||||
Vector3f vecOut;
|
||||
vecOut.x = vecIn1.y*vecIn2.z - vecIn1.z*vecIn2.y;
|
||||
vecOut.y = vecIn1.z*vecIn2.x - vecIn1.x*vecIn2.z;
|
||||
vecOut.z = vecIn1.x*vecIn2.y - vecIn1.y*vecIn2.x;
|
||||
return vecOut;
|
||||
}
|
||||
|
||||
// overload * operator to provide a vector scaler product
|
||||
Vector3f operator*(Vector3f vecIn1, float sclIn1)
|
||||
{
|
||||
Vector3f vecOut;
|
||||
vecOut.x = vecIn1.x * sclIn1;
|
||||
vecOut.y = vecIn1.y * sclIn1;
|
||||
vecOut.z = vecIn1.z * sclIn1;
|
||||
return vecOut;
|
||||
}
|
||||
|
||||
// overload * operator to provide a vector scaler product
|
||||
Vector3f operator*(float sclIn1, Vector3f vecIn1)
|
||||
{
|
||||
Vector3f vecOut;
|
||||
vecOut.x = vecIn1.x * sclIn1;
|
||||
vecOut.y = vecIn1.y * sclIn1;
|
||||
vecOut.z = vecIn1.z * sclIn1;
|
||||
return vecOut;
|
||||
}
|
||||
|
||||
void swap_var(float &d1, float &d2)
|
||||
{
|
||||
float tmp = d1;
|
||||
d1 = d2;
|
||||
d2 = tmp;
|
||||
}
|
||||
|
|
@ -0,0 +1,79 @@
|
|||
#include <math.h>
|
||||
#include <stdint.h>
|
||||
|
||||
#pragma once
|
||||
|
||||
#define GRAVITY_MSS 9.80665f
|
||||
#define deg2rad 0.017453292f
|
||||
#define rad2deg 57.295780f
|
||||
#define pi 3.141592657f
|
||||
#define earthRate 0.000072921f
|
||||
#define earthRadius 6378145.0f
|
||||
#define earthRadiusInv 1.5678540e-7f
|
||||
|
||||
class Vector3f
|
||||
{
|
||||
private:
|
||||
public:
|
||||
float x;
|
||||
float y;
|
||||
float z;
|
||||
|
||||
float length(void) const;
|
||||
void zero(void);
|
||||
};
|
||||
|
||||
class Mat3f
|
||||
{
|
||||
private:
|
||||
public:
|
||||
Vector3f x;
|
||||
Vector3f y;
|
||||
Vector3f z;
|
||||
|
||||
Mat3f();
|
||||
|
||||
void identity();
|
||||
Mat3f transpose(void) const;
|
||||
};
|
||||
|
||||
Vector3f operator*(float sclIn1, Vector3f vecIn1);
|
||||
Vector3f operator+( Vector3f vecIn1, Vector3f vecIn2);
|
||||
Vector3f operator-( Vector3f vecIn1, Vector3f vecIn2);
|
||||
Vector3f operator*( Mat3f matIn, Vector3f vecIn);
|
||||
Vector3f operator%( Vector3f vecIn1, Vector3f vecIn2);
|
||||
Vector3f operator*(Vector3f vecIn1, float sclIn1);
|
||||
|
||||
void swap_var(float &d1, float &d2);
|
||||
|
||||
const unsigned int n_states = 21;
|
||||
const unsigned int data_buffer_size = 50;
|
||||
|
||||
enum GPS_FIX {
|
||||
GPS_FIX_NOFIX = 0,
|
||||
GPS_FIX_2D = 2,
|
||||
GPS_FIX_3D = 3
|
||||
};
|
||||
|
||||
struct ekf_status_report {
|
||||
bool velHealth;
|
||||
bool posHealth;
|
||||
bool hgtHealth;
|
||||
bool velTimeout;
|
||||
bool posTimeout;
|
||||
bool hgtTimeout;
|
||||
uint32_t velFailTime;
|
||||
uint32_t posFailTime;
|
||||
uint32_t hgtFailTime;
|
||||
float states[n_states];
|
||||
bool angNaN;
|
||||
bool summedDelVelNaN;
|
||||
bool KHNaN;
|
||||
bool KHPNaN;
|
||||
bool PNaN;
|
||||
bool covarianceNaN;
|
||||
bool kalmanGainsNaN;
|
||||
bool statesNaN;
|
||||
};
|
||||
|
||||
void ekf_debug(const char *fmt, ...);
|
||||
|
|
@ -39,4 +39,5 @@ MODULE_COMMAND = ekf_att_pos_estimator
|
|||
|
||||
SRCS = ekf_att_pos_estimator_main.cpp \
|
||||
ekf_att_pos_estimator_params.c \
|
||||
estimator.cpp
|
||||
estimator_21states.cpp \
|
||||
estimator_utilities.cpp
|
||||
|
|
|
|||
Loading…
Reference in New Issue