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/**
 * @file ecl_yaw_controller.cpp
 * Implementation of a simple orthogonal coordinated turn yaw PID controller.
 *
 * Authors and acknowledgements in header.
 */

#include "ecl_yaw_controller.h"
#include <float.h>
#include <lib/geo/geo.h>
#include <mathlib/mathlib.h>

float ECL_YawController::control_attitude(const float dt, const ECL_ControlData &ctl_data)
{
	/* Do not calculate control signal with bad inputs */
	if (!(PX4_ISFINITE(ctl_data.roll) &&
	      PX4_ISFINITE(ctl_data.pitch) &&
	      PX4_ISFINITE(ctl_data.roll_rate_setpoint) &&
	      PX4_ISFINITE(ctl_data.pitch_rate_setpoint))) {

		return _rate_setpoint;
	}

	float constrained_roll;
	bool inverted = false;

	/* roll is used as feedforward term and inverted flight needs to be considered */
	if (fabsf(ctl_data.roll) < math::radians(90.0f)) {
		/* not inverted, but numerically still potentially close to infinity */
		constrained_roll = math::constrain(ctl_data.roll, math::radians(-80.0f), math::radians(80.0f));

	} else {
		inverted = true;

		// inverted flight, constrain on the two extremes of -pi..+pi to avoid infinity
		//note: the ranges are extended by 10 deg here to avoid numeric resolution effects
		if (ctl_data.roll > 0.0f) {
			/* right hemisphere */
			constrained_roll = math::constrain(ctl_data.roll, math::radians(100.0f), math::radians(180.0f));

		} else {
			/* left hemisphere */
			constrained_roll = math::constrain(ctl_data.roll, math::radians(-180.0f), math::radians(-100.0f));
		}
	}

	constrained_roll = math::constrain(constrained_roll, -fabsf(ctl_data.roll_setpoint), fabsf(ctl_data.roll_setpoint));


	if (!inverted) {
		/* Calculate desired yaw rate from coordinated turn constraint / (no side forces) */
		_rate_setpoint = tanf(constrained_roll) * cosf(ctl_data.pitch) * CONSTANTS_ONE_G / (ctl_data.airspeed <
				 ctl_data.airspeed_min ? ctl_data.airspeed_min : ctl_data.airspeed);
	}

	if (!PX4_ISFINITE(_rate_setpoint)) {
		PX4_WARN("yaw rate sepoint not finite");
		_rate_setpoint = 0.0f;
	}

	return _rate_setpoint;
}

float ECL_YawController::control_bodyrate(const float dt, const ECL_ControlData &ctl_data)
{
	/* Do not calculate control signal with bad inputs */
	if (!(PX4_ISFINITE(ctl_data.roll) &&
	      PX4_ISFINITE(ctl_data.pitch) &&
	      PX4_ISFINITE(ctl_data.body_y_rate) &&
	      PX4_ISFINITE(ctl_data.body_z_rate) &&
	      PX4_ISFINITE(ctl_data.pitch_rate_setpoint) &&
	      PX4_ISFINITE(ctl_data.airspeed_min) &&
	      PX4_ISFINITE(ctl_data.airspeed_max) &&
	      PX4_ISFINITE(ctl_data.scaler))) {

		return math::constrain(_last_output, -1.0f, 1.0f);
	}

	/* Calculate body angular rate error */
	_rate_error = _bodyrate_setpoint - ctl_data.body_z_rate;

	if (!ctl_data.lock_integrator && _k_i > 0.0f) {

		/* Integral term scales with 1/IAS^2 */
		float id = _rate_error * dt * ctl_data.scaler * ctl_data.scaler;

		/*
		 * anti-windup: do not allow integrator to increase if actuator is at limit
		 */
		if (_last_output < -1.0f) {
			/* only allow motion to center: increase value */
			id = math::max(id, 0.0f);

		} else if (_last_output > 1.0f) {
			/* only allow motion to center: decrease value */
			id = math::min(id, 0.0f);
		}

		/* add and constrain */
		_integrator = math::constrain(_integrator + id * _k_i, -_integrator_max, _integrator_max);
	}

	/* Apply PI rate controller and store non-limited output */
	/* FF terms scales with 1/TAS and P,I with 1/IAS^2 */
	_last_output = _bodyrate_setpoint * _k_ff * ctl_data.scaler +
		       _rate_error * _k_p * ctl_data.scaler * ctl_data.scaler
		       + _integrator;

	return math::constrain(_last_output, -1.0f, 1.0f);
}

float ECL_YawController::control_euler_rate(const float dt, const ECL_ControlData &ctl_data, float bodyrate_ff)
{
	/* Transform setpoint to body angular rates (jacobian) */
	_bodyrate_setpoint = -sinf(ctl_data.roll) * ctl_data.pitch_rate_setpoint +
			     cosf(ctl_data.roll) * cosf(ctl_data.pitch) * _rate_setpoint + bodyrate_ff;

	set_bodyrate_setpoint(_bodyrate_setpoint);

	return control_bodyrate(dt, ctl_data);
}