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/****************************************************************************
*
* Copyright (c) 2013, 2014 PX4 Development Team. All rights reserved.
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
* are met:
*
* 1. Redistributions of source code must retain the above copyright
* notice, this list of conditions and the following disclaimer.
* 2. Redistributions in binary form must reproduce the above copyright
* notice, this list of conditions and the following disclaimer in
* the documentation and/or other materials provided with the
* distribution.
* 3. Neither the name PX4 nor the names of its contributors may be
* used to endorse or promote products derived from this software
* without specific prior written permission.
*
* THIS SOFTWARE IS PROVIDED BY THE COPYRIGHT HOLDERS AND CONTRIBUTORS
* "AS IS" AND ANY EXPRESS OR IMPLIED WARRANTIES, INCLUDING, BUT NOT
* LIMITED TO, THE IMPLIED WARRANTIES OF MERCHANTABILITY AND FITNESS
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* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
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* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
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****************************************************************************/
/**
* @file mc_att_control.h
* Multicopter attitude controller.
*
* @author Tobias Naegeli <naegelit@student.ethz.ch>
* @author Lorenz Meier <lm@inf.ethz.ch>
* @author Anton Babushkin <anton.babushkin@me.com>
* @author Thomas Gubler <thomasgubler@gmail.com>
* @author Julian Oes <julian@oes.ch>
* @author Roman Bapst <bapstr@ethz.ch>
*
* The controller has two loops: P loop for angular error and PD loop for angular rate error.
* Desired rotation calculated keeping in mind that yaw response is normally slower than roll/pitch.
* For small deviations controller rotates copter to have shortest path of thrust vector and independently rotates around yaw,
* so actual rotation axis is not constant. For large deviations controller rotates copter around fixed axis.
* These two approaches fused seamlessly with weight depending on angular error.
* When thrust vector directed near-horizontally (e.g. roll ~= PI/2) yaw setpoint ignored because of singularity.
* Controller doesn't use Euler angles for work, they generated only for more human-friendly control and logging.
* If rotation matrix setpoint is invalid it will be generated from Euler angles for compatibility with old position controllers.
*/
#include <px4.h>
#include <stdlib.h>
#include <string.h>
#include <unistd.h>
#include <errno.h>
#include <math.h>
#include <poll.h>
#include <drivers/drv_hrt.h>
#include <arch/board/board.h>
#include <systemlib/param/param.h>
#include <systemlib/err.h>
#include <systemlib/perf_counter.h>
#include <systemlib/systemlib.h>
#include <systemlib/circuit_breaker.h>
#include <lib/mathlib/mathlib.h>
#include <lib/geo/geo.h>
#include "mc_att_control_base.h"
class MulticopterAttitudeControl :
public MulticopterAttitudeControlBase
{
public:
/**
* Constructor
*/
MulticopterAttitudeControl();
/**
* Destructor, also kills the sensors task.
*/
~MulticopterAttitudeControl();
void handle_vehicle_attitude(const PX4_TOPIC_T(vehicle_attitude) &msg);
void spin() { n.spin(); }
private:
bool _task_should_exit; /**< if true, sensor task should exit */
int _control_task; /**< task handle for sensor task */
bool _actuators_0_circuit_breaker_enabled; /**< circuit breaker to suppress output */
int _v_att_sub; /**< vehicle attitude subscription */
int _v_att_sp_sub; /**< vehicle attitude setpoint subscription */
int _v_rates_sp_sub; /**< vehicle rates setpoint subscription */
int _v_control_mode_sub; /**< vehicle control mode subscription */
int _params_sub; /**< parameter updates subscription */
int _manual_control_sp_sub; /**< manual control setpoint subscription */
int _armed_sub; /**< arming status subscription */
orb_advert_t _att_sp_pub; /**< attitude setpoint publication */
orb_advert_t _v_rates_sp_pub; /**< rate setpoint publication */
orb_advert_t _actuators_0_pub; /**< attitude actuator controls publication */
px4::NodeHandle n;
struct {
px4_param_t roll_p;
px4_param_t roll_rate_p;
px4_param_t roll_rate_i;
px4_param_t roll_rate_d;
px4_param_t pitch_p;
px4_param_t pitch_rate_p;
px4_param_t pitch_rate_i;
px4_param_t pitch_rate_d;
px4_param_t yaw_p;
px4_param_t yaw_rate_p;
px4_param_t yaw_rate_i;
px4_param_t yaw_rate_d;
px4_param_t yaw_ff;
px4_param_t yaw_rate_max;
px4_param_t man_roll_max;
px4_param_t man_pitch_max;
px4_param_t man_yaw_max;
px4_param_t acro_roll_max;
px4_param_t acro_pitch_max;
px4_param_t acro_yaw_max;
} _params_handles; /**< handles for interesting parameters */
perf_counter_t _loop_perf; /**< loop performance counter */
/**
* Update our local parameter cache.
*/
int parameters_update();
};
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