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ardupilot/libraries/AP_DCM/AP_DCM.cpp

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#define RADX100 0.000174532925
#define DEGX100 5729.57795
/*
APM_DCM_FW.cpp - DCM AHRS Library, fixed wing version, for Ardupilot Mega
Code by Doug Weibel, Jordi Muñoz and Jose Julio. DIYDrones.com
This library works with the ArduPilot Mega and "Oilpan"
This library is free software; you can redistribute it and/or
modify it under the terms of the GNU Lesser General Public
License as published by the Free Software Foundation; either
version 2.1 of the License, or (at your option) any later version.
Methods:
update_DCM() : Updates the AHRS by integrating the rotation matrix over time using the IMU object data
get_gyro() : Returns gyro vector corrected for bias
get_accel() : Returns accelerometer vector
get_dcm_matrix() : Returns dcm matrix
*/
#include <AP_DCM.h>
#define OUTPUTMODE 1 // This is just used for debugging, remove later
#define ToRad(x) (x*0.01745329252) // *pi/180
#define ToDeg(x) (x*57.2957795131) // *180/pi
//#define Kp_ROLLPITCH 0.05967 // .0014 * 418/9.81 Pitch&Roll Drift Correction Proportional Gain
//#define Ki_ROLLPITCH 0.00001278 // 0.0000003 * 418/9.81 Pitch&Roll Drift Correction Integrator Gain
//#define Ki_ROLLPITCH 0.0 // 0.0000003 * 418/9.81 Pitch&Roll Drift Correction Integrator Gain
//#define Kp_YAW 0.8 // Yaw Drift Correction Porportional Gain
//#define Ki_YAW 0.00004 // Yaw Drift CorrectionIntegrator Gain
#define SPEEDFILT 300 // centimeters/second
#define ADC_CONSTRAINT 900
void
AP_DCM::set_compass(Compass *compass)
{
_compass = compass;
}
/**************************************************/
void
AP_DCM::update_DCM_fast(void)
{
float delta_t;
_imu->update();
_gyro_vector = _imu->get_gyro(); // Get current values for IMU sensors
_accel_vector = _imu->get_accel(); // Get current values for IMU sensors
delta_t = _imu->get_delta_time();
matrix_update(delta_t); // Integrate the DCM matrix
switch(_toggle++){
case 0:
normalize(); // Normalize the DCM matrix
break;
case 1:
//drift_correction(); // Normalize the DCM matrix
euler_rp(); // Calculate pitch, roll, yaw for stabilization and navigation
break;
case 2:
drift_correction(); // Normalize the DCM matrix
break;
case 3:
//drift_correction(); // Normalize the DCM matrix
euler_rp(); // Calculate pitch, roll, yaw for stabilization and navigation
break;
case 4:
euler_yaw();
break;
default:
euler_rp(); // Calculate pitch, roll, yaw for stabilization and navigation
_toggle = 0;
//drift_correction(); // Normalize the DCM matrix
break;
}
}
/**************************************************/
void
AP_DCM::update_DCM(void)
{
float delta_t;
_imu->update();
_gyro_vector = _imu->get_gyro(); // Get current values for IMU sensors
_accel_vector = _imu->get_accel(); // Get current values for IMU sensors
delta_t = _imu->get_delta_time();
matrix_update(delta_t); // Integrate the DCM matrix
normalize(); // Normalize the DCM matrix
drift_correction(); // Perform drift correction
euler_angles(); // Calculate pitch, roll, yaw for stabilization and navigation
}
/**************************************************/
//For Debugging
/*
void
printm(const char *l, Matrix3f &m)
{ Serial.println(" "); Serial.println(l);
Serial.print(m.a.x, 12); Serial.print(" "); Serial.print(m.a.y, 12); Serial.print(" "); Serial.println(m.a.z, 12);
Serial.print(m.b.x, 12); Serial.print(" "); Serial.print(m.b.y, 12); Serial.print(" "); Serial.println(m.b.z, 12);
Serial.print(m.c.x, 12); Serial.print(" "); Serial.print(m.c.y, 12); Serial.print(" "); Serial.println(m.c.z, 12);
Serial.print(*(uint32_t *)&(m.a.x), HEX); Serial.print(" "); Serial.print(*(uint32_t *)&(m.a.y), HEX); Serial.print(" "); Serial.println(*(uint32_t *)&(m.a.z), HEX);
Serial.print(*(uint32_t *)&(m.b.x), HEX); Serial.print(" "); Serial.print(*(uint32_t *)&(m.b.y), HEX); Serial.print(" "); Serial.println(*(uint32_t *)&(m.b.z), HEX);
Serial.print(*(uint32_t *)&(m.c.x), HEX); Serial.print(" "); Serial.print(*(uint32_t *)&(m.c.y), HEX); Serial.print(" "); Serial.println(*(uint32_t *)&(m.c.z), HEX);
}
*/
/**************************************************/
void
AP_DCM::matrix_update(float _G_Dt)
{
Matrix3f update_matrix;
Matrix3f temp_matrix;
_omega_integ_corr = _gyro_vector + _omega_I; // Used for _centripetal correction (theoretically better than _omega)
_omega = _omega_integ_corr + _omega_P; // Equation 16, adding proportional and integral correction terms
if(_centripetal &&
_gps != NULL &&
_gps->status() == GPS::GPS_OK) {
// Remove _centripetal acceleration.
accel_adjust();
}
#if OUTPUTMODE == 1
float tmp = _G_Dt * _omega.x;
update_matrix.b.z = -tmp; // -delta Theta x
update_matrix.c.y = tmp; // delta Theta x
tmp = _G_Dt * _omega.y;
update_matrix.c.x = -tmp; // -delta Theta y
update_matrix.a.z = tmp; // delta Theta y
tmp = _G_Dt * _omega.z;
update_matrix.b.x = tmp; // delta Theta z
update_matrix.a.y = -tmp; // -delta Theta z
update_matrix.a.x = 0;
update_matrix.b.y = 0;
update_matrix.c.z = 0;
#else // Uncorrected data (no drift correction)
update_matrix.a.x = 0;
update_matrix.a.y = -_G_Dt * _gyro_vector.z;
update_matrix.a.z = _G_Dt * _gyro_vector.y;
update_matrix.b.x = _G_Dt * _gyro_vector.z;
update_matrix.b.y = 0;
update_matrix.b.z = -_G_Dt * _gyro_vector.x;
update_matrix.c.x = -_G_Dt * _gyro_vector.y;
update_matrix.c.y = _G_Dt * _gyro_vector.x;
update_matrix.c.z = 0;
#endif
temp_matrix = _dcm_matrix * update_matrix;
_dcm_matrix = _dcm_matrix + temp_matrix; // Equation 17
}
/**************************************************/
void
AP_DCM::accel_adjust(void)
{
Vector3f veloc, temp;
veloc.x = _gps->ground_speed / 100; // We are working with acceleration in m/s^2 units
// We are working with a modified version of equation 26 as our IMU object reports acceleration in the positive axis direction as positive
//_accel_vector -= _omega_integ_corr % _veloc; // Equation 26 This line is giving the compiler a problem so we break it up below
temp.x = 0;
temp.y = _omega_integ_corr.z * veloc.x; // only computing the non-zero terms
temp.z = -1.0f * _omega_integ_corr.y * veloc.x; // After looking at the compiler issue lets remove _veloc and simlify
_accel_vector -= temp;
}
/*
reset the DCM matrix and omega. Used on ground start, and on
extreme errors in the matrix
*/
void
AP_DCM::matrix_reset(bool recover_eulers)
{
if (_compass != NULL) {
_compass->null_offsets_disable();
}
// reset the integration terms
_omega_I.x = 0.0f;
_omega_I.y = 0.0f;
_omega_I.z = 0.0f;
_omega_P = _omega_I;
_omega_integ_corr = _omega_I;
_omega = _omega_I;
_error_roll_pitch = _omega_I;
_error_yaw = _omega_I;
_errorCourse = 0;
// if the caller wants us to try to recover to the current
// attitude then calculate the dcm matrix from the current
// roll/pitch/yaw values
if (recover_eulers && !isnan(roll) && !isnan(pitch) && !isnan(yaw)) {
float cp = cos(pitch);
float sp = sin(pitch);
float sr = sin(roll);
float cr = cos(roll);
float sy = sin(yaw);
float cy = cos(yaw);
//Serial.printf("setting DCM matrix to %f %f %f\n", ToDeg(roll), ToDeg(pitch), ToDeg(yaw));
_dcm_matrix.a.x = cp * cy;
_dcm_matrix.a.y = (sr * sp * cy) - (cr * sy);
_dcm_matrix.a.z = (cr * sp * cy) + (sr * sy);
_dcm_matrix.b.x = cp * sy;
_dcm_matrix.b.y = (sr * sp * sy) + (cr * cy);
_dcm_matrix.b.z = (cr * sp * sy) - (sr * cy);
_dcm_matrix.c.x = -sp;
_dcm_matrix.c.y = sr * cp;
_dcm_matrix.c.z = cr * cp;
} else {
// otherwise make it flat
//Serial.printf("zeroing DCM matrix\n");
_dcm_matrix.a.x = 1.0f;
_dcm_matrix.a.y = 0.0f;
_dcm_matrix.a.z = 0.0f;
_dcm_matrix.b.x = 0.0f;
_dcm_matrix.b.y = 1.0f;
_dcm_matrix.b.z = 0.0f;
_dcm_matrix.c.x = 0.0f;
_dcm_matrix.c.y = 0.0f;
_dcm_matrix.c.z = 1.0f;
}
if (_compass != NULL) {
_compass->null_offsets_enable(); // This call is needed to restart the nulling
// Otherwise the reset in the DCM matrix can mess up
// the nulling
}
}
/*
check the DCM matrix for pathological values
*/
void
AP_DCM::check_matrix(void)
{
if (_dcm_matrix.is_nan()) {
//Serial.printf("ERROR: DCM matrix NAN\n");
SITL_debug("ERROR: DCM matrix NAN\n");
renorm_blowup_count++;
matrix_reset(true);
return;
}
// some DCM matrix values can lead to an out of range error in
// the pitch calculation via asin(). These NaN values can
// feed back into the rest of the DCM matrix via the
// error_course value.
if (!(_dcm_matrix.c.x < 1.0 &&
_dcm_matrix.c.x > -1.0)) {
// We have an invalid matrix. Force a normalisation.
renorm_range_count++;
normalize();
if (_dcm_matrix.is_nan() ||
fabs(_dcm_matrix.c.x) > 10) {
// normalisation didn't fix the problem! We're
// in real trouble. All we can do is reset
//Serial.printf("ERROR: DCM matrix error. _dcm_matrix.c.x=%f\n",
// _dcm_matrix.c.x);
SITL_debug("ERROR: DCM matrix error. _dcm_matrix.c.x=%f\n",
_dcm_matrix.c.x);
renorm_blowup_count++;
matrix_reset(true);
}
}
}
/*************************************************
Direction Cosine Matrix IMU: Theory
William Premerlani and Paul Bizard
Numerical errors will gradually reduce the orthogonality conditions expressed by equation 5
to approximations rather than identities. In effect, the axes in the two frames of reference no
longer describe a rigid body. Fortunately, numerical error accumulates very slowly, so it is a
simple matter to stay ahead of it.
We call the process of enforcing the orthogonality conditions ÒrenormalizationÓ.
*/
void
AP_DCM::normalize(void)
{
float error = 0;
Vector3f temporary[3];
int problem = 0;
error = _dcm_matrix.a * _dcm_matrix.b; // eq.18
temporary[0] = _dcm_matrix.b;
temporary[1] = _dcm_matrix.a;
temporary[0] = _dcm_matrix.a - (temporary[0] * (0.5f * error)); // eq.19
temporary[1] = _dcm_matrix.b - (temporary[1] * (0.5f * error)); // eq.19
temporary[2] = temporary[0] % temporary[1]; // c= a x b // eq.20
_dcm_matrix.a = renorm(temporary[0], problem);
_dcm_matrix.b = renorm(temporary[1], problem);
_dcm_matrix.c = renorm(temporary[2], problem);
if (problem == 1) { // Our solution is blowing up and we will force back to initial condition. Hope we are not upside down!
matrix_reset(true);
}
}
/**************************************************/
Vector3f
AP_DCM::renorm(Vector3f const &a, int &problem)
{
float renorm_val;
// numerical errors will slowly build up over time in DCM,
// causing inaccuracies. We can keep ahead of those errors
// using the renormalization technique from the DCM IMU paper
// (see equations 18 to 21).
// For APM we don't bother with the taylor expansion
// optimisation from the paper as on our 2560 CPU the cost of
// the sqrt() is 44 microseconds, and the small time saving of
// the taylor expansion is not worth the potential of
// additional error buildup.
// Note that we can get significant renormalisation values
// when we have a larger delta_t due to a glitch eleswhere in
// APM, such as a I2c timeout or a set of EEPROM writes. While
// we would like to avoid these if possible, if it does happen
// we don't want to compound the error by making DCM less
// accurate.
renorm_val = 1.0 / sqrt(a * a);
if (!(renorm_val < 2.0 && renorm_val > 0.5)) {
// this is larger than it should get - log it as a warning
renorm_range_count++;
if (!(renorm_val < 1.0e6 && renorm_val > 1.0e-6)) {
// we are getting values which are way out of
// range, we will reset the matrix and hope we
// can recover our attitude using drift
// correction before we hit the ground!
problem = 1;
//Serial.printf("ERROR: DCM renormalisation error. renorm_val=%f\n",
// renorm_val);
SITL_debug("ERROR: DCM renormalisation error. renorm_val=%f\n",
renorm_val);
renorm_blowup_count++;
}
}
return (a * renorm_val);
}
/**************************************************/
void
AP_DCM::drift_correction(void)
{
//Compensation the Roll, Pitch and Yaw drift.
//float mag_heading_x;
//float mag_heading_y;
float error_course = 0;
float accel_magnitude;
float accel_weight;
float integrator_magnitude;
//static float scaled_omega_P[3];
//static float scaled_omega_I[3];
static bool in_motion = false;
Matrix3f rot_mat;
//*****Roll and Pitch***************
// Calculate the magnitude of the accelerometer vector
accel_magnitude = _accel_vector.length() / 9.80665f;
// Dynamic weighting of accelerometer info (reliability filter)
// Weight for accelerometer info (<0.5G = 0.0, 1G = 1.0 , >1.5G = 0.0)
accel_weight = constrain(1 - _clamp * fabs(1 - accel_magnitude), 0, 1); // upped to (<0.66G = 0.0, 1G = 1.0 , >1.33G = 0.0)
// We monitor the amount that the accelerometer based drift correction is deweighted for performance reporting
_health = constrain(_health+(0.02 * (accel_weight - .5)), 0, 1);
// adjust the ground of reference
_error_roll_pitch = _dcm_matrix.c % _accel_vector; // Equation 27 *** sign changed from prev implementation???
// error_roll_pitch are in Accel m/s^2 units
// Limit max error_roll_pitch to limit max omega_P and omega_I
_error_roll_pitch.x = constrain(_error_roll_pitch.x, -1.17f, 1.17f);
_error_roll_pitch.y = constrain(_error_roll_pitch.y, -1.17f, 1.17f);
_error_roll_pitch.z = constrain(_error_roll_pitch.z, -1.17f, 1.17f);
_omega_P = _error_roll_pitch * (_kp_roll_pitch * accel_weight);
_omega_I += _error_roll_pitch * (_ki_roll_pitch * accel_weight);
//*****YAW***************
if (_compass && _compass->healthy) {
// We make the gyro YAW drift correction based on compass magnetic heading
error_course = (_dcm_matrix.a.x * _compass->heading_y) - (_dcm_matrix.b.x * _compass->heading_x); // Equation 23, Calculating YAW error
} else if (_gps) {
// Use GPS Ground course to correct yaw gyro drift
if (_gps->ground_speed >= SPEEDFILT) {
_course_over_ground_x = cos(ToRad(_gps->ground_course/100.0));
_course_over_ground_y = sin(ToRad(_gps->ground_course/100.0));
if(in_motion) {
error_course = (_dcm_matrix.a.x * _course_over_ground_y) - (_dcm_matrix.b.x * _course_over_ground_x); // Equation 23, Calculating YAW error
} else {
float cos_psi_err, sin_psi_err;
// This is the case for when we first start moving and reset the DCM so that yaw matches the gps ground course
// This is just to get a reasonable estimate faster
yaw = atan2(_dcm_matrix.b.x, _dcm_matrix.a.x);
cos_psi_err = cos(ToRad(_gps->ground_course/100.0) - yaw);
sin_psi_err = sin(ToRad(_gps->ground_course/100.0) - yaw);
// Rxx = cos psi err, Rxy = - sin psi err, Rxz = 0
// Ryx = sin psi err, Ryy = cos psi err, Ryz = 0
// Rzx = Rzy = 0, Rzz = 1
rot_mat.a.x = cos_psi_err;
rot_mat.a.y = -sin_psi_err;
rot_mat.b.x = sin_psi_err;
rot_mat.b.y = cos_psi_err;
rot_mat.a.z = 0;
rot_mat.b.z = 0;
rot_mat.c.x = 0;
rot_mat.c.y = 0;
rot_mat.c.z = 1.0;
_dcm_matrix = rot_mat * _dcm_matrix;
in_motion = true;
error_course = 0;
}
} else {
error_course = 0;
in_motion = false;
}
}
_error_yaw = _dcm_matrix.c * error_course; // Equation 24, Applys the yaw correction to the XYZ rotation of the aircraft, depeding the position.
_omega_P += _error_yaw * _kp_yaw; // Adding yaw correction to proportional correction vector.
_omega_I += _error_yaw * _ki_yaw; // adding yaw correction to integrator correction vector.
// Here we will place a limit on the integrator so that the integrator cannot ever exceed ~30 degrees/second
integrator_magnitude = _omega_I.length();
if (integrator_magnitude > radians(30)) {
_omega_I *= (radians(30) / integrator_magnitude);
}
//Serial.print("*");
}
/**************************************************/
void
AP_DCM::euler_angles(void)
{
check_matrix();
#if (OUTPUTMODE == 2) // Only accelerometer info (debugging purposes)
roll = atan2(_accel_vector.y, -_accel_vector.z); // atan2(acc_y, acc_z)
pitch = safe_asin((_accel_vector.x) / (double)9.81); // asin(acc_x)
yaw = 0;
#else
pitch = -safe_asin(_dcm_matrix.c.x);
roll = atan2(_dcm_matrix.c.y, _dcm_matrix.c.z);
yaw = atan2(_dcm_matrix.b.x, _dcm_matrix.a.x);
#endif
roll_sensor = degrees(roll) * 100;
pitch_sensor = degrees(pitch) * 100;
yaw_sensor = degrees(yaw) * 100;
if (yaw_sensor < 0)
yaw_sensor += 36000;
}
void
AP_DCM::euler_rp(void)
{
check_matrix();
pitch = -safe_asin(_dcm_matrix.c.x);
roll = atan2(_dcm_matrix.c.y, _dcm_matrix.c.z);
roll_sensor = roll * DEGX100; //degrees(roll) * 100;
pitch_sensor = pitch * DEGX100; //degrees(pitch) * 100;
}
void
AP_DCM::euler_yaw(void)
{
yaw = atan2(_dcm_matrix.b.x, _dcm_matrix.a.x);
yaw_sensor = yaw * DEGX100; //degrees(yaw) * 100;
if (yaw_sensor < 0)
yaw_sensor += 36000;
}
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