stabilization_attitude_heli_indi.h

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/*
 * Copyright (C) 2008-2009 Antoine Drouin <poinix@gmail.com>
 *
 * This file is part of paparazzi.
 *
 * paparazzi is free software; you can redistribute it and/or modify
 * it under the terms of the GNU General Public License as published by
 * the Free Software Foundation; either version 2, or (at your option)
 * any later version.
 *
 * paparazzi is distributed in the hope that it will be useful,
 * but WITHOUT ANY WARRANTY; without even the implied warranty of
 * MERCHANTABILITY or FITNESS FOR A PARTICULAR PURPOSE.  See the
 * GNU General Public License for more details.
 *
 * You should have received a copy of the GNU General Public License
 * along with paparazzi; see the file COPYING.  If not, write to
 * the Free Software Foundation, 59 Temple Place - Suite 330,
 * Boston, MA 02111-1307, USA.
 */
 
#ifndef STABILIZATION_ATTITUDE_HELI_INDI_H
#define STABILIZATION_ATTITUDE_HELI_INDI_H
 
#include "firmwares/rotorcraft/stabilization/stabilization_attitude.h"
#include "math/pprz_algebra_int.h"
#include "filters/notch_filter.h"
#include "filters/delayed_first_order_lowpass_filter.h"
 
#define __k 1
#define INDI_NR_FILTERS 2
#define INDI_DOF 4
#define INDI_ROLL 0
#define INDI_PITCH 1
#define INDI_YAW 2
#define INDI_THRUST 3
#define INDI_YAW_BUFFER_SIZE 9
 
struct HeliIndiGains {
  int32_t roll_p;
  int32_t pitch_p;
  int32_t yaw_p;
  int32_t yaw_d;
};
 
/* All these values are in the struct to make it easier for logging */
struct IndiController_int {
  int32_t reference[INDI_DOF];                                      
  int32_t error[INDI_DOF];                                          
  int32_t invG[INDI_DOF][INDI_DOF];                                 
  int32_t du[INDI_DOF];                                             
  int32_t u_setpoint[INDI_DOF];                                     
  int32_t actuator_out[INDI_DOF];                                   
  int32_t command_out[2][INDI_DOF];                                 
  int32_t filtered_actuator[INDI_NR_FILTERS][INDI_DOF];             
  int32_t measurement[INDI_DOF];                                    
  int32_t filtered_measurement[INDI_NR_FILTERS][INDI_DOF];          
  int32_t pitch_comp_angle;                                         
  int32_t roll_comp_angle;                                          
  bool enable_notch;                                                
  int16_t motor_rpm;                                                
  float sp_offset_roll;                                             
  float sp_offset_pitch;                                            
  void (*apply_compensator_filters)(int32_t _out[], int32_t _in[]);
  void (*apply_actuator_models)(int32_t _out[], int32_t _in[]);
  void (*apply_actuator_filters[INDI_NR_FILTERS])(int32_t _out[], int32_t _in[]);
  void (*apply_measurement_filters[INDI_NR_FILTERS])(int32_t _out[], int32_t _in[]);
};
 
extern struct delayed_first_order_lowpass_filter_t actuator_model[INDI_DOF];
extern struct HeliIndiGains heli_indi_gains;
 
extern void stabilization_attitude_heli_indi_init(void);
extern void stabilization_attitude_heli_indi_set_steadystate_pitch(float pitch);
extern void stabilization_attitude_heli_indi_set_steadystate_roll(float roll);
extern void stabilization_attitude_heli_indi_set_steadystate_pitchroll(void);
 
#endif /* STABILIZATION_ATTITUDE_HELI_INDI_H */