px4_autopilot/attitude_fw/ecl_controller.cpp

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/**
 * @file ecl_controller.cpp
 * Definition of base class for other controllers
 *
 * @author Lorenz Meier <lm@inf.ethz.ch>
 * @author Thomas Gubler <thomasgubler@gmail.com>
 *
 * Acknowledgements:
 *
 *   The control design is based on a design
 *   by Paul Riseborough and Andrew Tridgell, 2013,
 *   which in turn is based on initial work of
 *   Jonathan Challinger, 2012.
 */

#include "ecl_controller.h"

#include <stdio.h>
#include <mathlib/mathlib.h>

ECL_Controller::ECL_Controller(const char *name) :
	_last_run(0),
	_tc(0.1f),
	_k_p(0.0f),
	_k_i(0.0f),
	_k_ff(0.0f),
	_integrator_max(0.0f),
	_max_rate(0.0f),
	_last_output(0.0f),
	_integrator(0.0f),
	_rate_error(0.0f),
	_rate_setpoint(0.0f),
	_bodyrate_setpoint(0.0f),
	_perf_name()
{
	/* Init performance counter */
	snprintf(_perf_name, sizeof(_perf_name), "fw att control %s nonfinite input", name);
	_nonfinite_input_perf = perf_alloc(PC_COUNT, _perf_name);
}

ECL_Controller::~ECL_Controller()
{
	perf_free(_nonfinite_input_perf);
}

void ECL_Controller::reset_integrator()
{
	_integrator = 0.0f;
}

void ECL_Controller::set_time_constant(float time_constant)
{
	if (time_constant > 0.1f && time_constant < 3.0f) {
		_tc = time_constant;
	}
}

void ECL_Controller::set_k_p(float k_p)
{
	_k_p = k_p;
}

void ECL_Controller::set_k_i(float k_i)
{
	_k_i = k_i;
}

void ECL_Controller::set_k_ff(float k_ff)
{
	_k_ff = k_ff;
}

void ECL_Controller::set_integrator_max(float max)
{
	_integrator_max = max;
}

void ECL_Controller::set_max_rate(float max_rate)
{
	_max_rate = max_rate;
}

float ECL_Controller::get_rate_error()
{
	return _rate_error;
}

float ECL_Controller::get_desired_rate()
{
	return _rate_setpoint;
}

float ECL_Controller::get_desired_bodyrate()
{
	return _bodyrate_setpoint;
}

float ECL_Controller::constrain_airspeed(float airspeed, float minspeed, float maxspeed) {
	float airspeed_result = airspeed;
	if (!PX4_ISFINITE(airspeed)) {
		/* airspeed is NaN, +- INF or not available, pick center of band */
		airspeed_result = 0.5f * (minspeed + maxspeed);
	} else if (airspeed < minspeed) {
		airspeed_result = minspeed;
	}
	return airspeed_result;
}