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PX4-Autopilot/src/modules/fw_att_control/ecl_controller.h
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2022-08-19 09:40:48 +02:00

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/****************************************************************************
*
* Copyright (c) 2020-2022 PX4 Development Team. All rights reserved.
*
* Redistribution and use in source and binary forms, with or without
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*
* 1. Redistributions of source code must retain the above copyright
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* 2. Redistributions in binary form must reproduce the above copyright
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* 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
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/**
* @file ecl_controller.h
* 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.
*/
#pragma once
#include <drivers/drv_hrt.h>
#include <px4_log.h>
struct ECL_ControlData {
float roll;
float pitch;
float yaw;
float body_x_rate;
float body_y_rate;
float body_z_rate;
float roll_setpoint;
float pitch_setpoint;
float yaw_setpoint;
float euler_roll_rate_setpoint;
float euler_pitch_rate_setpoint;
float euler_yaw_rate_setpoint;
float airspeed_min;
float airspeed_max;
float airspeed;
float groundspeed;
float groundspeed_scaler;
};
class ECL_Controller
{
public:
ECL_Controller();
virtual ~ECL_Controller() = default;
/**
* @brief Calculates both euler and body rate setpoints. Has different implementations for all body axes.
*
* @param dt Time step [s]
* @param ctrl_data Various control inputs (attitude, body rates, attitdue stepoints, euler rate setpoints, current speeed)
* @return Body rate setpoint [rad/s]
*/
virtual float control_attitude(const float dt, const ECL_ControlData &ctl_data) = 0;
/* Setters */
void set_time_constant(float time_constant);
void set_k_p(float k_p);
void set_k_i(float k_i);
void set_k_ff(float k_ff);
void set_integrator_max(float max);
void set_max_rate(float max_rate);
/* Getters */
float get_euler_rate_setpoint();
float get_body_rate_setpoint();
float get_integrator();
void reset_integrator();
protected:
uint64_t _last_run;
float _tc;
float _k_p;
float _k_i;
float _k_ff;
float _integrator_max;
float _max_rate;
float _last_output;
float _integrator;
float _euler_rate_setpoint;
float _body_rate_setpoint;
float constrain_airspeed(float airspeed, float minspeed, float maxspeed);
};