px4_autopilot/EKF/EKFGSF_yaw.h

#pragma once

#include <geo/geo.h>
#include <matrix/math.hpp>
#include <mathlib/mathlib.h>

using matrix::AxisAnglef;
using matrix::Dcmf;
using matrix::Eulerf;
using matrix::Matrix3f;
using matrix::Quatf;
using matrix::Vector2f;
using matrix::Vector3f;
using matrix::wrap_pi;

#define N_MODELS_EKFGSF 5

#ifndef M_PI_F
#define M_PI_F 3.14159265f
#endif

#ifndef M_PI_2_F
#define M_PI_2_F 1.57079632f
#endif

#ifndef M_TWOPI_INV
#define M_TWOPI_INV 0.159154943f
#endif

class EKFGSF_yaw
{
public:
    	// Constructor
    	EKFGSF_yaw();

    	// Update Filter States - this should be called whenever new IMU data is available
	void update(const Vector3f del_ang, // IMU delta angle rotation vector meassured in body frame (rad)
                	const Vector3f del_vel, // IMU delta velocity vector meassured in body frame (m/s)
                	const float del_ang_dt, // time interval that del_ang was integrated over (sec)
                	const float del_vel_dt, // time interval that del_vel was integrated over (sec)
                	bool run_EKF,           // set to true when flying or movement is suitable for yaw estimation
                	float airspeed);   	// true airspeed used for centripetal accel compensation - set to 0 when not required.

	void setVelocity(Vector2f velocity,	// NE velocity measurement (m/s)
                     	float accuracy);	// 1-sigma accuracy of velocity measurement (m/s)

	// get solution data for logging
	bool getLogData(float *yaw_composite,
			float *yaw_composite_variance,
			float yaw[N_MODELS_EKFGSF],
			float innov_VN[N_MODELS_EKFGSF],
			float innov_VE[N_MODELS_EKFGSF],
			float weight[N_MODELS_EKFGSF]);

    	// get yaw estimate and the corresponding variance
    	// return false if no yaw estimate available
    	bool getYawData(float *yaw, float *yaw_variance);

private:
	// Parameters - these could be made tuneable
	const float _gyro_noise{1.0e-1f}; 	// yaw rate noise used for covariance prediction (rad/sec)
	const float _accel_noise{2.0f};		// horizontal accel noise used for covariance prediction (m/sec**2)
	const float _tilt_gain{0.2f};		// gain from tilt error to gyro correction for complementary filter (1/sec)
	const float _gyro_bias_gain{0.04f};	// gain applied to integral of gyro correction for complementary filter (1/sec)
	const float _weight_min{0.0f};		// minimum value of an individual model weighting

	// Declarations used by the bank of N_MODELS_EKFGSF AHRS complementary filters

	Vector3f _delta_ang;	// IMU delta angle (rad)
	Vector3f _delta_vel;	// IMU delta velocity (m/s)
	float _delta_ang_dt;	// _delta_ang integration time interval (sec)
	float _delta_vel_dt;	// _delta_vel integration time interval (sec)
	float _true_airspeed;	// true airspeed used for centripetal accel compensation (m/s)

	struct _ahrs_ekf_gsf_struct{
		Dcmf R;				// matrix that rotates a vector from body to earth frame
		Vector3f gyro_bias;		// gyro bias learned and used by the quaternion calculation
		bool aligned{false};		// true when AHRS has been aligned
		float vel_NE[2] {};		// NE velocity vector from last GPS measurement (m/s)
		bool fuse_gps = false;		// true when GPS should be fused on that frame
		float accel_dt = 0;		// time step used when generating _simple_accel_FR data (sec)
	};
	_ahrs_ekf_gsf_struct _ahrs_ekf_gsf[N_MODELS_EKFGSF];
	bool _ahrs_ekf_gsf_tilt_aligned = false;// true the initial tilt alignment has been calculated
	float _ahrs_accel_fusion_gain;		// gain from accel vector tilt error to rate gyro correction used by AHRS calculation
	Vector3f _ahrs_accel;			// low pass filtered body frame specific force vector used by AHRS calculation (m/s/s)
	float _ahrs_accel_norm;			// length of _ahrs_accel specific force vector used by AHRS calculation (m/s/s)

	// calculate the gain from gravity vector misalingment to tilt correction to be used by all AHRS filters
	void ahrsCalcAccelGain();

	// update specified AHRS rotation matrix using IMU and optionally true airspeed data
	void ahrsPredict(const uint8_t model_index);

	// align all AHRS roll and pitch orientations using IMU delta velocity vector
	void ahrsAlignTilt();

	// align all AHRS yaw orientations to initial values
	void ahrsAlignYaw();

	// Efficient propagation of a delta angle in body frame applied to the body to earth frame rotation matrix
	Matrix3f ahrsPredictRotMat(Matrix3f &R, Vector3f &g);

	// Declarations used by a bank of N_MODELS_EKFGSF EKFs

	struct _ekf_gsf_struct{
		matrix::Vector3f X; // Vel North (m/s),  Vel East (m/s), yaw (rad)s
		matrix::SquareMatrix<float, 3> P; // covariance matrix
		float W = 0.0f; // weighting
		matrix::SquareMatrix<float, 2> S; // innovation covariance matrix
		matrix::SquareMatrix<float, 2> S_inverse;  // inverse of the innovation covariance matrix
		float S_det_inverse; // inverse of the innovation covariance matrix determinant
		matrix::Vector2f innov; // Velocity N,E innovation (m/s)
	};
	_ekf_gsf_struct _ekf_gsf[N_MODELS_EKFGSF];
	bool _vel_data_updated;  // true when velocity data has been updated
	bool _run_ekf_gsf;       // true when operating condition is suitable for to run the GSF and EKF models and fuse velocity data
	Vector2f _vel_NE;        // NE velocity observations (m/s)
	float _vel_accuracy;     // 1-sigma accuracy of velocity observations (m/s)
	bool _ekf_gsf_vel_fuse_started;	// true when the EKF's have started fusing velocity data and the prediction and update processing is active

	// initialise states and covariance data for the GSF and EKF filters
	void initialiseEKFGSF();

	// predict state and covariance for the specified EKF using inertial data
	void predictEKF(const uint8_t model_index);

	// update state and covariance for the specified EKF using a NE velocity measurement
	// return false if update failed
	bool updateEKF(const uint8_t model_index);

	inline float sq(float x) { return x * x; };

	// converts Tait-Bryan 312 sequence of rotations from frame 1 to frame 2
	// to the corresponding rotation matrix that rotates from frame 2 to frame 1
	// rot312(0) - First rotation is a RH rotation about the Z axis (rad)
	// rot312(1) - Second rotation is a RH rotation about the X axis (rad)
	// rot312(2) - Third rotation is a RH rotation about the Y axis (rad)
	// See http://www.atacolorado.com/eulersequences.doc
	Dcmf taitBryan312ToRotMat(const Vector3f &rot312);

	// Declarations used by the Gaussian Sum Filter (GSF) that combines the individual EKF yaw estimates

	float _gsf_yaw; 		// yaw estimate (rad)
	float _gsf_yaw_variance; 	// variance of yaw estimate (rad^2)

	// return the probability of the state estimate for the specified EKF assuming a gaussian error distribution
	float gaussianDensity(const uint8_t model_index) const;

	// update the inverse of the innovation covariance matrix
	void updateInnovCovMatInv(const uint8_t model_index);

};