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stabilization_attitude_euler_int.c
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stabilization_attitude_euler_int.c
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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.
*/
#include "firmwares/rotorcraft/stabilization.h"
#include "state.h"
#include "subsystems/radio_control.h"
#include "firmwares/rotorcraft/stabilization/stabilization_attitude_rc_setpoint.h"
#include "generated/airframe.h"
struct Int32AttitudeGains stabilization_gains;
/* warn if some gains are still negative */
#if (STABILIZATION_ATTITUDE_PHI_PGAIN < 0) || \
(STABILIZATION_ATTITUDE_THETA_PGAIN < 0) || \
(STABILIZATION_ATTITUDE_PSI_PGAIN < 0) || \
(STABILIZATION_ATTITUDE_PHI_DGAIN < 0) || \
(STABILIZATION_ATTITUDE_THETA_DGAIN < 0) || \
(STABILIZATION_ATTITUDE_PSI_DGAIN < 0) || \
(STABILIZATION_ATTITUDE_PHI_IGAIN < 0) || \
(STABILIZATION_ATTITUDE_THETA_IGAIN < 0) || \
(STABILIZATION_ATTITUDE_PSI_IGAIN < 0)
#warning "ALL control gains are now positive!!!"
#endif
struct Int32Eulers stabilization_att_sum_err;
int32_t stabilization_att_fb_cmd[COMMANDS_NB];
int32_t stabilization_att_ff_cmd[COMMANDS_NB];
void stabilization_attitude_init(void) {
stabilization_attitude_ref_init();
VECT3_ASSIGN(stabilization_gains.p,
STABILIZATION_ATTITUDE_PHI_PGAIN,
STABILIZATION_ATTITUDE_THETA_PGAIN,
STABILIZATION_ATTITUDE_PSI_PGAIN);
VECT3_ASSIGN(stabilization_gains.d,
STABILIZATION_ATTITUDE_PHI_DGAIN,
STABILIZATION_ATTITUDE_THETA_DGAIN,
STABILIZATION_ATTITUDE_PSI_DGAIN);
VECT3_ASSIGN(stabilization_gains.i,
STABILIZATION_ATTITUDE_PHI_IGAIN,
STABILIZATION_ATTITUDE_THETA_IGAIN,
STABILIZATION_ATTITUDE_PSI_IGAIN);
VECT3_ASSIGN(stabilization_gains.dd,
STABILIZATION_ATTITUDE_PHI_DDGAIN,
STABILIZATION_ATTITUDE_THETA_DDGAIN,
STABILIZATION_ATTITUDE_PSI_DDGAIN);
INT_EULERS_ZERO( stabilization_att_sum_err );
}
void stabilization_attitude_read_rc(bool_t in_flight) {
stabilization_attitude_read_rc_setpoint_eulers(&stab_att_sp_euler, in_flight);
}
void stabilization_attitude_enter(void) {
stab_att_sp_euler.psi = stateGetNedToBodyEulers_i()->psi;
reset_psi_ref_from_body();
INT_EULERS_ZERO( stabilization_att_sum_err );
}
#define OFFSET_AND_ROUND(_a, _b) (((_a)+(1<<((_b)-1)))>>(_b))
#define OFFSET_AND_ROUND2(_a, _b) (((_a)+(1<<((_b)-1))-((_a)<0?1:0))>>(_b))
#define MAX_SUM_ERR 4000000
void stabilization_attitude_run(bool_t in_flight) {
/* update reference */
stabilization_attitude_ref_update();
/* compute feedforward command */
stabilization_att_ff_cmd[COMMAND_ROLL] =
OFFSET_AND_ROUND(stabilization_gains.dd.x * stab_att_ref_accel.p, 5);
stabilization_att_ff_cmd[COMMAND_PITCH] =
OFFSET_AND_ROUND(stabilization_gains.dd.y * stab_att_ref_accel.q, 5);
stabilization_att_ff_cmd[COMMAND_YAW] =
OFFSET_AND_ROUND(stabilization_gains.dd.z * stab_att_ref_accel.r, 5);
/* compute feedback command */
/* attitude error */
const struct Int32Eulers att_ref_scaled = {
OFFSET_AND_ROUND(stab_att_ref_euler.phi, (REF_ANGLE_FRAC - INT32_ANGLE_FRAC)),
OFFSET_AND_ROUND(stab_att_ref_euler.theta, (REF_ANGLE_FRAC - INT32_ANGLE_FRAC)),
OFFSET_AND_ROUND(stab_att_ref_euler.psi, (REF_ANGLE_FRAC - INT32_ANGLE_FRAC)) };
struct Int32Eulers att_err;
struct Int32Eulers* ltp_to_body_euler = stateGetNedToBodyEulers_i();
EULERS_DIFF(att_err, att_ref_scaled, (*ltp_to_body_euler));
INT32_ANGLE_NORMALIZE(att_err.psi);
if (in_flight) {
/* update integrator */
EULERS_ADD(stabilization_att_sum_err, att_err);
EULERS_BOUND_CUBE(stabilization_att_sum_err, -MAX_SUM_ERR, MAX_SUM_ERR);
}
else {
INT_EULERS_ZERO(stabilization_att_sum_err);
}
/* rate error */
const struct Int32Rates rate_ref_scaled = {
OFFSET_AND_ROUND(stab_att_ref_rate.p, (REF_RATE_FRAC - INT32_RATE_FRAC)),
OFFSET_AND_ROUND(stab_att_ref_rate.q, (REF_RATE_FRAC - INT32_RATE_FRAC)),
OFFSET_AND_ROUND(stab_att_ref_rate.r, (REF_RATE_FRAC - INT32_RATE_FRAC)) };
struct Int32Rates rate_err;
struct Int32Rates* body_rate = stateGetBodyRates_i();
RATES_DIFF(rate_err, rate_ref_scaled, (*body_rate));
/* PID */
stabilization_att_fb_cmd[COMMAND_ROLL] =
stabilization_gains.p.x * att_err.phi +
stabilization_gains.d.x * rate_err.p +
OFFSET_AND_ROUND2((stabilization_gains.i.x * stabilization_att_sum_err.phi), 10);
stabilization_att_fb_cmd[COMMAND_PITCH] =
stabilization_gains.p.y * att_err.theta +
stabilization_gains.d.y * rate_err.q +
OFFSET_AND_ROUND2((stabilization_gains.i.y * stabilization_att_sum_err.theta), 10);
stabilization_att_fb_cmd[COMMAND_YAW] =
stabilization_gains.p.z * att_err.psi +
stabilization_gains.d.z * rate_err.r +
OFFSET_AND_ROUND2((stabilization_gains.i.z * stabilization_att_sum_err.psi), 10);
/* with P gain of 100, att_err of 180deg (3.14 rad)
* fb cmd: 100 * 3.14 * 2^12 / 2^CMD_SHIFT = 628
* max possible command is 9600
*/
#define CMD_SHIFT 11
/* sum feedforward and feedback */
stabilization_cmd[COMMAND_ROLL] =
OFFSET_AND_ROUND((stabilization_att_fb_cmd[COMMAND_ROLL]+stabilization_att_ff_cmd[COMMAND_ROLL]), CMD_SHIFT);
stabilization_cmd[COMMAND_PITCH] =
OFFSET_AND_ROUND((stabilization_att_fb_cmd[COMMAND_PITCH]+stabilization_att_ff_cmd[COMMAND_PITCH]), CMD_SHIFT);
stabilization_cmd[COMMAND_YAW] =
OFFSET_AND_ROUND((stabilization_att_fb_cmd[COMMAND_YAW]+stabilization_att_ff_cmd[COMMAND_YAW]), CMD_SHIFT);
/* bound the result */
BoundAbs(stabilization_cmd[COMMAND_ROLL], MAX_PPRZ);
BoundAbs(stabilization_cmd[COMMAND_PITCH], MAX_PPRZ);
BoundAbs(stabilization_cmd[COMMAND_YAW], MAX_PPRZ);
}