PX4-Autopilot/src/modules/ekf2/EKF/airspeed_fusion.cpp

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/**
 * @file airspeed_fusion.cpp
 * airspeed fusion methods.
 * equations generated using EKF/python/ekf_derivation/main.py
 *
 * @author Carl Olsson <carlolsson.co@gmail.com>
 * @author Roman Bast <bapstroman@gmail.com>
 * @author Paul Riseborough <p_riseborough@live.com.au>
 *
 */

#include "ekf.h"

#include <ekf_derivation/generated/compute_airspeed_h_and_k.h>
#include <ekf_derivation/generated/compute_airspeed_innov_and_innov_var.h>
#include <ekf_derivation/generated/compute_wind_init_and_cov_from_airspeed.h>

#include <mathlib/mathlib.h>

void Ekf::controlAirDataFusion(const imuSample &imu_delayed)
{
	// control activation and initialisation/reset of wind states required for airspeed fusion

	// If both airspeed and sideslip fusion have timed out and we are not using a drag observation model then we no longer have valid wind estimates
	const bool airspeed_timed_out = isTimedOut(_aid_src_airspeed.time_last_fuse, (uint64_t)10e6);
	const bool sideslip_timed_out = isTimedOut(_aid_src_sideslip.time_last_fuse, (uint64_t)10e6);

	if (_control_status.flags.fake_pos || (airspeed_timed_out && sideslip_timed_out && (_params.drag_ctrl == 0))) {
		_control_status.flags.wind = false;
	}

#if defined(CONFIG_EKF2_GNSS)
	// clear yaw estimator airspeed (updated later with true airspeed if airspeed fusion is active)
	if (_control_status.flags.fixed_wing) {
		if (_control_status.flags.in_air && !_control_status.flags.vehicle_at_rest) {
			if (!_control_status.flags.fuse_aspd) {
				_yawEstimator.setTrueAirspeed(_params.EKFGSF_tas_default);
			}

		} else {
			_yawEstimator.setTrueAirspeed(0.f);
		}
	}
#endif // CONFIG_EKF2_GNSS

	if (_params.arsp_thr <= 0.f) {
		stopAirspeedFusion();
		return;
	}

	if (_airspeed_buffer && _airspeed_buffer->pop_first_older_than(imu_delayed.time_us, &_airspeed_sample_delayed)) {

		const airspeedSample &airspeed_sample = _airspeed_sample_delayed;

		updateAirspeed(airspeed_sample, _aid_src_airspeed);

		_innov_check_fail_status.flags.reject_airspeed = _aid_src_airspeed.innovation_rejected; // TODO: remove this redundant flag

		const bool continuing_conditions_passing = _control_status.flags.in_air && _control_status.flags.fixed_wing && !_control_status.flags.fake_pos;
		const bool is_airspeed_significant = airspeed_sample.true_airspeed > _params.arsp_thr;
		const bool is_airspeed_consistent = (_aid_src_airspeed.test_ratio > 0.f && _aid_src_airspeed.test_ratio < 1.f);
		const bool starting_conditions_passing = continuing_conditions_passing && is_airspeed_significant
		                                         && (is_airspeed_consistent || !_control_status.flags.wind); // if wind isn't already estimated, the states are reset when starting airspeed fusion

		if (_control_status.flags.fuse_aspd) {
			if (continuing_conditions_passing) {
				if (is_airspeed_significant) {
					fuseAirspeed(airspeed_sample, _aid_src_airspeed);
				}

#if defined(CONFIG_EKF2_GNSS)
				_yawEstimator.setTrueAirspeed(airspeed_sample.true_airspeed);
#endif // CONFIG_EKF2_GNSS

				const bool is_fusion_failing = isTimedOut(_aid_src_airspeed.time_last_fuse, (uint64_t)10e6);

				if (is_fusion_failing) {
					stopAirspeedFusion();
				}

			} else {
				stopAirspeedFusion();
			}

		} else if (starting_conditions_passing) {
			ECL_INFO("starting airspeed fusion");

			// If starting wind state estimation, reset the wind states and covariances before fusing any data
			// Also catch the case where sideslip fusion enabled wind estimation recently and didn't converge yet.
			const Vector2f wind_var_xy = getWindVelocityVariance();

			if (!_control_status.flags.wind || (wind_var_xy(0) + wind_var_xy(1) > sq(_params.initial_wind_uncertainty))) {
				// activate the wind states
				_control_status.flags.wind = true;
				// reset the wind speed states and corresponding covariances
				resetWindUsingAirspeed(airspeed_sample);
			}

			_control_status.flags.fuse_aspd = true;
		}

	} else if (_control_status.flags.fuse_aspd && !isRecent(_airspeed_sample_delayed.time_us, (uint64_t)1e6)) {
		ECL_WARN("Airspeed data stopped");
		stopAirspeedFusion();
	}
}

void Ekf::updateAirspeed(const airspeedSample &airspeed_sample, estimator_aid_source1d_s &aid_src) const
{
	// reset flags
	resetEstimatorAidStatus(aid_src);

	// Variance for true airspeed measurement - (m/sec)^2
	const float R = sq(math::constrain(_params.eas_noise, 0.5f, 5.0f) *
			   math::constrain(airspeed_sample.eas2tas, 0.9f, 10.0f));

	float innov = 0.f;
	float innov_var = 0.f;
	sym::ComputeAirspeedInnovAndInnovVar(_state.vector(), P, airspeed_sample.true_airspeed, R, FLT_EPSILON, &innov, &innov_var);

	aid_src.observation = airspeed_sample.true_airspeed;
	aid_src.observation_variance = R;
	aid_src.innovation = innov;
	aid_src.innovation_variance = innov_var;

	aid_src.timestamp_sample = airspeed_sample.time_us;

	const float innov_gate = fmaxf(_params.tas_innov_gate, 1.f);
	setEstimatorAidStatusTestRatio(aid_src, innov_gate);
}

void Ekf::fuseAirspeed(const airspeedSample &airspeed_sample, estimator_aid_source1d_s &aid_src)
{
	if (aid_src.innovation_rejected) {
		return;
	}

	// determine if we need the airspeed fusion to correct states other than wind
	const bool update_wind_only = !_control_status.flags.wind_dead_reckoning;

	const float innov_var = aid_src.innovation_variance;

	if (innov_var < aid_src.observation_variance || innov_var < FLT_EPSILON) {
		// Reset the estimator covariance matrix
		// if we are getting aiding from other sources, warn and reset the wind states and covariances only
		const char *action_string = nullptr;

		if (update_wind_only) {
			resetWindUsingAirspeed(airspeed_sample);
			action_string = "wind";

		} else {
			initialiseCovariance();
			_state.wind_vel.setZero();
			action_string = "full";
		}

		ECL_ERR("airspeed badly conditioned - %s covariance reset", action_string);

		_fault_status.flags.bad_airspeed = true;

		return;
	}

	_fault_status.flags.bad_airspeed = false;

	VectorState H; // Observation jacobian
	VectorState K; // Kalman gain vector

	sym::ComputeAirspeedHAndK(_state.vector(), P, innov_var, FLT_EPSILON, &H, &K);

	if (update_wind_only) {
		const Vector2f K_wind = K.slice<State::wind_vel.dof, 1>(State::wind_vel.idx, 0);
		K.setZero();
		K.slice<State::wind_vel.dof, 1>(State::wind_vel.idx, 0) = K_wind;
	}

	const bool is_fused = measurementUpdate(K, aid_src.innovation_variance, aid_src.innovation);

	aid_src.fused = is_fused;
	_fault_status.flags.bad_airspeed = !is_fused;

	if (is_fused) {
		aid_src.time_last_fuse = _time_delayed_us;
	}
}

void Ekf::stopAirspeedFusion()
{
	if (_control_status.flags.fuse_aspd) {
		ECL_INFO("stopping airspeed fusion");
		resetEstimatorAidStatus(_aid_src_airspeed);
		_control_status.flags.fuse_aspd = false;

#if defined(CONFIG_EKF2_GNSS)
		_yawEstimator.setTrueAirspeed(NAN);
#endif // CONFIG_EKF2_GNSS
	}
}

void Ekf::resetWindUsingAirspeed(const airspeedSample &airspeed_sample)
{
	constexpr float sideslip_var = sq(math::radians(15.0f));

	const float euler_yaw = getEulerYaw(_R_to_earth);
	const float airspeed_var = sq(math::constrain(_params.eas_noise, 0.5f, 5.0f) * math::constrain(airspeed_sample.eas2tas, 0.9f, 10.0f));

	matrix::SquareMatrix<float, State::wind_vel.dof> P_wind;
	sym::ComputeWindInitAndCovFromAirspeed(_state.vel, euler_yaw, airspeed_sample.true_airspeed, getVelocityVariance(), getYawVar(), sideslip_var, airspeed_var, &_state.wind_vel, &P_wind);

	resetStateCovariance<State::wind_vel>(P_wind);

	ECL_INFO("reset wind using airspeed to (%.3f, %.3f)", (double)_state.wind_vel(0), (double)_state.wind_vel(1));

	_aid_src_airspeed.time_last_fuse = _time_delayed_us;
}