ardupilot/libraries/AP_DCM/AP_DCM.cpp

#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 Mu<EFBFBD>oz 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(void)
{
	if (_compass != NULL) {
		_compass->null_offsets_disable();		
	}
	_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;
	_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 (_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
	}
}

/*************************************************
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 <EFBFBD>renormalization<EFBFBD>.
*/
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();
	}
}

/**************************************************/
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;
			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)
{
	#if (OUTPUTMODE == 2)				 // Only accelerometer info (debugging purposes)
	roll 		= atan2(_accel_vector.y, -_accel_vector.z);		// atan2(acc_y, acc_z)
	pitch 		= asin((_accel_vector.x) / (double)9.81); // asin(acc_x)
	yaw 			= 0;
	#else
	pitch 		= -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)
{
	pitch 			= -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;
}