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multirotor_attitude_control performance improved, tested in flight. PID library new functionality and bugfixes.

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This commit is contained in:
Anton Babushkin
2013-06-20 19:25:37 +04:00
parent 85b5da8078
commit 5cb1f4662f
7 changed files with 70 additions and 71 deletions
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src/modules/multirotor_att_control/multirotor_attitude_control.c
+2 -8
View File
@@ -163,16 +163,12 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
static uint64_t last_run = 0;
static uint64_t last_input = 0;
float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
float dT_input = (hrt_absolute_time() - last_input) / 1000000.0f;
last_run = hrt_absolute_time();
if (last_input != att_sp->timestamp) {
last_input = att_sp->timestamp;
}
static int sensor_delay;
sensor_delay = hrt_absolute_time() - att->timestamp;
static int motor_skip_counter = 0;
static PID_t pitch_controller;
@@ -190,10 +186,8 @@ void multirotor_control_attitude(const struct vehicle_attitude_setpoint_s *att_s
parameters_init(&h);
parameters_update(&h, &p);
pid_init(&pitch_controller, p.att_p, p.att_i, p.att_d, 1000.0f,
1000.0f, PID_MODE_DERIVATIV_SET);
pid_init(&roll_controller, p.att_p, p.att_i, p.att_d, 1000.0f,
1000.0f, PID_MODE_DERIVATIV_SET);
pid_init(&pitch_controller, p.att_p, p.att_i, p.att_d, 1000.0f, 1000.0f, PID_MODE_DERIVATIV_SET, 0.0f);
pid_init(&roll_controller, p.att_p, p.att_i, p.att_d, 1000.0f, 1000.0f, PID_MODE_DERIVATIV_SET, 0.0f);
initialized = true;
}
src/modules/multirotor_att_control/multirotor_rate_control.c
+22 -29
View File
@@ -1,8 +1,9 @@
/****************************************************************************
*
* Copyright (C) 2012 PX4 Development Team. All rights reserved.
* Copyright (C) 2013 PX4 Development Team. All rights reserved.
* Author: Tobias Naegeli <naegelit@student.ethz.ch>
* Lorenz Meier <lm@inf.ethz.ch>
* Anton Babushkin <anton.babushkin@me.com>
*
* Redistribution and use in source and binary forms, with or without
* modification, are permitted provided that the following conditions
@@ -40,6 +41,7 @@
*
* @author Tobias Naegeli <naegelit@student.ethz.ch>
* @author Lorenz Meier <lm@inf.ethz.ch>
* @author Anton Babushkin <anton.babushkin@me.com>
*/
#include "multirotor_rate_control.h"
@@ -150,14 +152,10 @@ static int parameters_update(const struct mc_rate_control_param_handles *h, stru
void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
const float rates[], struct actuator_controls_s *actuators)
{
static float roll_control_last = 0;
static float pitch_control_last = 0;
static uint64_t last_run = 0;
const float deltaT = (hrt_absolute_time() - last_run) / 1000000.0f;
static uint64_t last_input = 0;
float dT_input = (hrt_absolute_time() - last_input) / 1000000.0f;
if (last_input != rate_sp->timestamp) {
last_input = rate_sp->timestamp;
}
@@ -166,6 +164,9 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
static int motor_skip_counter = 0;
static PID_t pitch_rate_controller;
static PID_t roll_rate_controller;
static struct mc_rate_control_params p;
static struct mc_rate_control_param_handles h;
@@ -176,43 +177,35 @@ void multirotor_control_rates(const struct vehicle_rates_setpoint_s *rate_sp,
parameters_init(&h);
parameters_update(&h, &p);
initialized = true;
pid_init(&pitch_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f, PID_MODE_DERIVATIV_CALC_NO_SP, 0.003f);
pid_init(&roll_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f, PID_MODE_DERIVATIV_CALC_NO_SP, 0.003f);
}
/* load new parameters with lower rate */
if (motor_skip_counter % 2500 == 0) {
/* update parameters from storage */
parameters_update(&h, &p);
// warnx("rate ctrl: p.yawrate_p: %8.4f, loop: %d Hz, input: %d Hz",
// (double)p.yawrate_p, (int)(1.0f/deltaT), (int)(1.0f/dT_input));
pid_set_parameters(&pitch_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f);
pid_set_parameters(&roll_rate_controller, p.attrate_p, p.attrate_i, p.attrate_d, 1.0f, 1.0f);
}
/* calculate current control outputs */
/* reset integral if on ground */
if (rate_sp->thrust < 0.01f) {
pid_reset_integral(&pitch_rate_controller);
pid_reset_integral(&roll_rate_controller);
}
/* control pitch (forward) output */
float pitch_control = p.attrate_p * (rate_sp->pitch - rates[1]) - (p.attrate_d * pitch_control_last);
/* increase resilience to faulty control inputs */
if (isfinite(pitch_control)) {
pitch_control_last = pitch_control;
} else {
pitch_control = 0.0f;
warnx("rej. NaN ctrl pitch");
}
float pitch_control = pid_calculate(&pitch_rate_controller, rate_sp->pitch ,
rates[1], 0.0f, deltaT);
/* control roll (left/right) output */
float roll_control = p.attrate_p * (rate_sp->roll - rates[0]) - (p.attrate_d * roll_control_last);
float roll_control = pid_calculate(&roll_rate_controller, rate_sp->roll ,
rates[0], 0.0f, deltaT);
/* increase resilience to faulty control inputs */
if (isfinite(roll_control)) {
roll_control_last = roll_control;
} else {
roll_control = 0.0f;
warnx("rej. NaN ctrl roll");
}
/* control yaw rate */
/* control yaw rate */ //XXX use library here
float yaw_rate_control = p.yawrate_p * (rate_sp->yaw - rates[2]);
/* increase resilience to faulty control inputs */