PX4-Autopilot/src/modules/mc_pos_control/PositionControl/PositionControl.cpp

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/**
 * @file PositionControl.cpp
 */

#include "PositionControl.hpp"
#include "ControlMath.hpp"
#include <float.h>
#include <mathlib/mathlib.h>
#include <px4_platform_common/defines.h>
#include <geo/geo.h>

using namespace matrix;

const trajectory_setpoint_s PositionControl::empty_trajectory_setpoint = {0, {NAN, NAN, NAN}, {NAN, NAN, NAN}, {NAN, NAN, NAN}, {NAN, NAN, NAN}, NAN, NAN};

void PositionControl::setVelocityGains(const Vector3f &P, const Vector3f &I, const Vector3f &D)
{
	_gain_vel_p = P;
	_gain_vel_i = I;
	_gain_vel_d = D;
}

void PositionControl::setVelocityLimits(const float vel_horizontal, const float vel_up, const float vel_down)
{
	_lim_vel_horizontal = vel_horizontal;
	_lim_vel_up = vel_up;
	_lim_vel_down = vel_down;
}

void PositionControl::setThrustLimits(const float min, const float max)
{
	// make sure there's always enough thrust vector length to infer the attitude
	_lim_thr_min = math::max(min, 10e-4f);
	_lim_thr_max = max;
}

void PositionControl::setHorizontalThrustMargin(const float margin)
{
	_lim_thr_xy_margin = margin;
}

void PositionControl::updateHoverThrust(const float hover_thrust_new)
{
	// Given that the equation for thrust is T = a_sp * Th / g - Th
	// with a_sp = desired acceleration, Th = hover thrust and g = gravity constant,
	// we want to find the acceleration that needs to be added to the integrator in order obtain
	// the same thrust after replacing the current hover thrust by the new one.
	// T' = T => a_sp' * Th' / g - Th' = a_sp * Th / g - Th
	// so a_sp' = (a_sp - g) * Th / Th' + g
	// we can then add a_sp' - a_sp to the current integrator to absorb the effect of changing Th by Th'
	const float previous_hover_thrust = _hover_thrust;
	setHoverThrust(hover_thrust_new);

	_vel_int(2) += (_acc_sp(2) - CONSTANTS_ONE_G) * previous_hover_thrust / _hover_thrust
		       + CONSTANTS_ONE_G - _acc_sp(2);
}

void PositionControl::setState(const PositionControlStates &states)
{
	_pos = states.position;
	_vel = states.velocity;
	_yaw = states.yaw;
	_vel_dot = states.acceleration;
}

void PositionControl::setInputSetpoint(const trajectory_setpoint_s &setpoint)
{
	_pos_sp = Vector3f(setpoint.position);
	_vel_sp = Vector3f(setpoint.velocity);
	_acc_sp = Vector3f(setpoint.acceleration);
	_yaw_sp = setpoint.yaw;
	_yawspeed_sp = setpoint.yawspeed;
}

bool PositionControl::update(const float dt)
{
	bool valid = _inputValid();

	if (valid) {
		_positionControl();
		_velocityControl(dt);

		_yawspeed_sp = PX4_ISFINITE(_yawspeed_sp) ? _yawspeed_sp : 0.f;
		_yaw_sp = PX4_ISFINITE(_yaw_sp) ? _yaw_sp : _yaw; // TODO: better way to disable yaw control
	}

	// There has to be a valid output acceleration and thrust setpoint otherwise something went wrong
	return valid && _acc_sp.isAllFinite() && _thr_sp.isAllFinite();
}

void PositionControl::_positionControl()
{
	// P-position controller
	Vector3f vel_sp_position = (_pos_sp - _pos).emult(_gain_pos_p);
	// Position and feed-forward velocity setpoints or position states being NAN results in them not having an influence
	ControlMath::addIfNotNanVector3f(_vel_sp, vel_sp_position);
	// make sure there are no NAN elements for further reference while constraining
	ControlMath::setZeroIfNanVector3f(vel_sp_position);

	// Constrain horizontal velocity by prioritizing the velocity component along the
	// the desired position setpoint over the feed-forward term.
	_vel_sp.xy() = ControlMath::constrainXY(vel_sp_position.xy(), (_vel_sp - vel_sp_position).xy(), _lim_vel_horizontal);
	// Constrain velocity in z-direction.
	_vel_sp(2) = math::constrain(_vel_sp(2), -_lim_vel_up, _lim_vel_down);
}

void PositionControl::_velocityControl(const float dt)
{
	// Constrain vertical velocity integral
	_vel_int(2) = math::constrain(_vel_int(2), -CONSTANTS_ONE_G, CONSTANTS_ONE_G);

	// PID velocity control
	Vector3f vel_error = _vel_sp - _vel;
	Vector3f acc_sp_velocity = vel_error.emult(_gain_vel_p) + _vel_int - _vel_dot.emult(_gain_vel_d);

	// No control input from setpoints or corresponding states which are NAN
	ControlMath::addIfNotNanVector3f(_acc_sp, acc_sp_velocity);

	_accelerationControl();

	// Integrator anti-windup in vertical direction
	if ((_thr_sp(2) >= -_lim_thr_min && vel_error(2) >= 0.f) ||
	    (_thr_sp(2) <= -_lim_thr_max && vel_error(2) <= 0.f)) {
		vel_error(2) = 0.f;
	}

	// Prioritize vertical control while keeping a horizontal margin
	const Vector2f thrust_sp_xy(_thr_sp);
	const float thrust_sp_xy_norm = thrust_sp_xy.norm();
	const float thrust_max_squared = math::sq(_lim_thr_max);

	// Determine how much vertical thrust is left keeping horizontal margin
	const float allocated_horizontal_thrust = math::min(thrust_sp_xy_norm, _lim_thr_xy_margin);
	const float thrust_z_max_squared = thrust_max_squared - math::sq(allocated_horizontal_thrust);

	// Saturate maximal vertical thrust
	_thr_sp(2) = math::max(_thr_sp(2), -sqrtf(thrust_z_max_squared));

	// Determine how much horizontal thrust is left after prioritizing vertical control
	const float thrust_max_xy_squared = thrust_max_squared - math::sq(_thr_sp(2));
	float thrust_max_xy = 0.f;

	if (thrust_max_xy_squared > 0.f) {
		thrust_max_xy = sqrtf(thrust_max_xy_squared);
	}

	// Saturate thrust in horizontal direction
	if (thrust_sp_xy_norm > thrust_max_xy) {
		_thr_sp.xy() = thrust_sp_xy / thrust_sp_xy_norm * thrust_max_xy;
	}

	// Use tracking Anti-Windup for horizontal direction: during saturation, the integrator is used to unsaturate the output
	// see Anti-Reset Windup for PID controllers, L.Rundqwist, 1990
	const Vector2f acc_sp_xy_produced = Vector2f(_thr_sp) * (CONSTANTS_ONE_G / _hover_thrust);
	const float arw_gain = 2.f / _gain_vel_p(0);

	// The produced acceleration can be greater or smaller than the desired acceleration due to the saturations and the actual vertical thrust (computed independently).
	// The ARW loop needs to run if the signal is saturated only.
	const Vector2f acc_sp_xy = _acc_sp.xy();
	const Vector2f acc_limited_xy = (acc_sp_xy.norm_squared() > acc_sp_xy_produced.norm_squared())
					? acc_sp_xy_produced
					: acc_sp_xy;
	vel_error.xy() = Vector2f(vel_error) - arw_gain * (acc_sp_xy - acc_limited_xy);

	// Make sure integral doesn't get NAN
	ControlMath::setZeroIfNanVector3f(vel_error);
	// Update integral part of velocity control
	_vel_int += vel_error.emult(_gain_vel_i) * dt;
}

void PositionControl::_accelerationControl()
{
	// Assume standard acceleration due to gravity in vertical direction for attitude generation
	Vector3f body_z = Vector3f(-_acc_sp(0), -_acc_sp(1), CONSTANTS_ONE_G).normalized();
	ControlMath::limitTilt(body_z, Vector3f(0, 0, 1), _lim_tilt);
	// Scale thrust assuming hover thrust produces standard gravity
	float collective_thrust = _acc_sp(2) * (_hover_thrust / CONSTANTS_ONE_G) - _hover_thrust;
	// Project thrust to planned body attitude
	collective_thrust /= (Vector3f(0, 0, 1).dot(body_z));
	collective_thrust = math::min(collective_thrust, -_lim_thr_min);
	_thr_sp = body_z * collective_thrust;
}

bool PositionControl::_inputValid()
{
	bool valid = true;

	// Every axis x, y, z needs to have some setpoint
	for (int i = 0; i <= 2; i++) {
		valid = valid && (PX4_ISFINITE(_pos_sp(i)) || PX4_ISFINITE(_vel_sp(i)) || PX4_ISFINITE(_acc_sp(i)));
	}

	// x and y input setpoints always have to come in pairs
	valid = valid && (PX4_ISFINITE(_pos_sp(0)) == PX4_ISFINITE(_pos_sp(1)));
	valid = valid && (PX4_ISFINITE(_vel_sp(0)) == PX4_ISFINITE(_vel_sp(1)));
	valid = valid && (PX4_ISFINITE(_acc_sp(0)) == PX4_ISFINITE(_acc_sp(1)));

	// For each controlled state the estimate has to be valid
	for (int i = 0; i <= 2; i++) {
		if (PX4_ISFINITE(_pos_sp(i))) {
			valid = valid && PX4_ISFINITE(_pos(i));
		}

		if (PX4_ISFINITE(_vel_sp(i))) {
			valid = valid && PX4_ISFINITE(_vel(i)) && PX4_ISFINITE(_vel_dot(i));
		}
	}

	return valid;
}

void PositionControl::getLocalPositionSetpoint(vehicle_local_position_setpoint_s &local_position_setpoint) const
{
	local_position_setpoint.x = _pos_sp(0);
	local_position_setpoint.y = _pos_sp(1);
	local_position_setpoint.z = _pos_sp(2);
	local_position_setpoint.yaw = _yaw_sp;
	local_position_setpoint.yawspeed = _yawspeed_sp;
	local_position_setpoint.vx = _vel_sp(0);
	local_position_setpoint.vy = _vel_sp(1);
	local_position_setpoint.vz = _vel_sp(2);
	_acc_sp.copyTo(local_position_setpoint.acceleration);
	_thr_sp.copyTo(local_position_setpoint.thrust);
}

void PositionControl::getAttitudeSetpoint(vehicle_attitude_setpoint_s &attitude_setpoint) const
{
	ControlMath::thrustToAttitude(_thr_sp, _yaw_sp, attitude_setpoint);
	attitude_setpoint.yaw_sp_move_rate = _yawspeed_sp;
}