fly316/PX4-Autopilot
7
0
Fork 0
mirror of https://gitee.com/mirrors_PX4/PX4-Autopilot.git synced 2026-04-14 10:07:39 +08:00
Code Issues Packages Projects Releases Wiki Activity

Remove unused estimator

Browse Source
This commit is contained in:
Lorenz Meier 2015-07-14 10:46:44 +02:00
parent 1ecbb73394
commit 5a2ed4a476
6 changed files with 0 additions and 830 deletions
Show Stats Download Patch File Download Diff File Expand all files Collapse all files

1
makefiles/nuttx/config_px4fmu-v2_test.mk
View File

@ -88,7 +88,6 @@ MODULES += examples/px4_simple_app
#
# Drivers / modules to test build, but not useful for test environment
#
MODULES += modules/attitude_estimator_so3
MODULES += drivers/pca8574
#

3
src/modules/attitude_estimator_so3/README
View File

@ -1,3 +0,0 @@
Synopsis
nsh> attitude_estimator_so3_comp start

661
src/modules/attitude_estimator_so3/attitude_estimator_so3_main.cpp
View File

@ -1,661 +0,0 @@
/****************************************************************************
*
* Copyright (c) 2013 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
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/*
* @file attitude_estimator_so3_main.cpp
*
* @author Hyon Lim <limhyon@gmail.com>
* @author Anton Babushkin <anton.babushkin@me.com>
*
* Implementation of nonlinear complementary filters on the SO(3).
* This code performs attitude estimation by using accelerometer, gyroscopes and magnetometer.
* Result is provided as quaternion, 1-2-3 Euler angle and rotation matrix.
*
* Theory of nonlinear complementary filters on the SO(3) is based on [1].
* Quaternion realization of [1] is based on [2].
* Optmized quaternion update code is based on Sebastian Madgwick's implementation.
*
* References
* [1] Mahony, R.; Hamel, T.; Pflimlin, Jean-Michel, "Nonlinear Complementary Filters on the Special Orthogonal Group," Automatic Control, IEEE Transactions on , vol.53, no.5, pp.1203,1218, June 2008
* [2] Euston, M.; Coote, P.; Mahony, R.; Jonghyuk Kim; Hamel, T., "A complementary filter for attitude estimation of a fixed-wing UAV," Intelligent Robots and Systems, 2008. IROS 2008. IEEE/RSJ International Conference on , vol., no., pp.340,345, 22-26 Sept. 2008
*/
#include <px4_config.h>
#include <unistd.h>
#include <stdlib.h>
#include <string.h>
#include <stdio.h>
#include <stdbool.h>
#include <poll.h>
#include <fcntl.h>
#include <float.h>
#include <nuttx/sched.h>
#include <sys/prctl.h>
#include <termios.h>
#include <errno.h>
#include <limits.h>
#include <math.h>
#include <uORB/uORB.h>
#include <uORB/topics/debug_key_value.h>
#include <uORB/topics/sensor_combined.h>
#include <uORB/topics/vehicle_attitude.h>
#include <uORB/topics/vehicle_control_mode.h>
#include <uORB/topics/parameter_update.h>
#include <drivers/drv_hrt.h>
#include <systemlib/systemlib.h>
#include <systemlib/perf_counter.h>
#include <systemlib/err.h>
#ifdef __cplusplus
extern "C" {
#endif
#include "attitude_estimator_so3_params.h"
#ifdef __cplusplus
}
#endif
extern "C" __EXPORT int attitude_estimator_so3_main(int argc, char *argv[]);
static bool thread_should_exit = false; /**< Deamon exit flag */
static bool thread_running = false; /**< Deamon status flag */
static int attitude_estimator_so3_task; /**< Handle of deamon task / thread */
//! Auxiliary variables to reduce number of repeated operations
static float q0 = 1.0f, q1 = 0.0f, q2 = 0.0f, q3 = 0.0f; /** quaternion of sensor frame relative to auxiliary frame */
static float dq0 = 0.0f, dq1 = 0.0f, dq2 = 0.0f, dq3 = 0.0f; /** quaternion of sensor frame relative to auxiliary frame */
static float gyro_bias[3] = {0.0f, 0.0f, 0.0f}; /** bias estimation */
static float q0q0, q0q1, q0q2, q0q3;
static float q1q1, q1q2, q1q3;
static float q2q2, q2q3;
static float q3q3;
static bool bFilterInit = false;
/**
* Mainloop of attitude_estimator_so3.
*/
int attitude_estimator_so3_thread_main(int argc, char *argv[]);
/**
* Print the correct usage.
*/
static void usage(const char *reason);
/* Function prototypes */
float invSqrt(float number);
void NonlinearSO3AHRSinit(float ax, float ay, float az, float mx, float my, float mz);
void NonlinearSO3AHRSupdate(float gx, float gy, float gz, float ax, float ay, float az, float mx, float my, float mz, float twoKp, float twoKi, float dt);
static void
usage(const char *reason)
{
if (reason)
fprintf(stderr, "%s\n", reason);
fprintf(stderr, "usage: attitude_estimator_so3 {start|stop|status}\n");
exit(1);
}
/**
* The attitude_estimator_so3 app only briefly exists to start
* the background job. The stack size assigned in the
* Makefile does only apply to this management task.
*
* The actual stack size should be set in the call
* to px4_task_spawn_cmd().
*/
int attitude_estimator_so3_main(int argc, char *argv[])
{
if (argc < 2) {
usage("missing command");
}
if (!strcmp(argv[1], "start")) {
if (thread_running) {
warnx("already running\n");
/* this is not an error */
exit(0);
}
thread_should_exit = false;
attitude_estimator_so3_task = px4_task_spawn_cmd("attitude_estimator_so3",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 5,
14000,
attitude_estimator_so3_thread_main,
(argv) ? (char * const *)&argv[2] : (char * const *)NULL);
exit(0);
}
if (!strcmp(argv[1], "stop")) {
thread_should_exit = true;
while (thread_running){
usleep(200000);
}
warnx("stopped");
exit(0);
}
if (!strcmp(argv[1], "status")) {
if (thread_running) {
warnx("running");
exit(0);
} else {
warnx("not started");
exit(1);
}
exit(0);
}
usage("unrecognized command");
exit(1);
}
//---------------------------------------------------------------------------------------------------
// Fast inverse square-root
// See: http://en.wikipedia.org/wiki/Fast_inverse_square_root
float invSqrt(float number)
{
volatile long i;
volatile float x, y;
volatile const float f = 1.5F;
x = number * 0.5F;
y = number;
i = * (( long * ) &y);
i = 0x5f375a86 - ( i >> 1 );
y = * (( float * ) &i);
y = y * ( f - ( x * y * y ) );
return y;
}
//! Using accelerometer, sense the gravity vector.
//! Using magnetometer, sense yaw.
void NonlinearSO3AHRSinit(float ax, float ay, float az, float mx, float my, float mz)
{
float initialRoll, initialPitch;
float cosRoll, sinRoll, cosPitch, sinPitch;
float magX, magY;
float initialHdg, cosHeading, sinHeading;
initialRoll = atan2(-ay, -az);
initialPitch = atan2(ax, -az);
cosRoll = cosf(initialRoll);
sinRoll = sinf(initialRoll);
cosPitch = cosf(initialPitch);
sinPitch = sinf(initialPitch);
magX = mx * cosPitch + my * sinRoll * sinPitch + mz * cosRoll * sinPitch;
magY = my * cosRoll - mz * sinRoll;
initialHdg = atan2f(-magY, magX);
cosRoll = cosf(initialRoll * 0.5f);
sinRoll = sinf(initialRoll * 0.5f);
cosPitch = cosf(initialPitch * 0.5f);
sinPitch = sinf(initialPitch * 0.5f);
cosHeading = cosf(initialHdg * 0.5f);
sinHeading = sinf(initialHdg * 0.5f);
q0 = cosRoll * cosPitch * cosHeading + sinRoll * sinPitch * sinHeading;
q1 = sinRoll * cosPitch * cosHeading - cosRoll * sinPitch * sinHeading;
q2 = cosRoll * sinPitch * cosHeading + sinRoll * cosPitch * sinHeading;
q3 = cosRoll * cosPitch * sinHeading - sinRoll * sinPitch * cosHeading;
// auxillary variables to reduce number of repeated operations, for 1st pass
q0q0 = q0 * q0;
q0q1 = q0 * q1;
q0q2 = q0 * q2;
q0q3 = q0 * q3;
q1q1 = q1 * q1;
q1q2 = q1 * q2;
q1q3 = q1 * q3;
q2q2 = q2 * q2;
q2q3 = q2 * q3;
q3q3 = q3 * q3;
}
void NonlinearSO3AHRSupdate(float gx, float gy, float gz, float ax, float ay, float az, float mx, float my, float mz, float twoKp, float twoKi, float dt)
{
float recipNorm;
float halfex = 0.0f, halfey = 0.0f, halfez = 0.0f;
// Make filter converge to initial solution faster
// This function assumes you are in static position.
// WARNING : in case air reboot, this can cause problem. But this is very unlikely happen.
if(bFilterInit == false) {
NonlinearSO3AHRSinit(ax,ay,az,mx,my,mz);
bFilterInit = true;
}
//! If magnetometer measurement is available, use it.
if(!((mx == 0.0f) && (my == 0.0f) && (mz == 0.0f))) {
float hx, hy, hz, bx, bz;
float halfwx, halfwy, halfwz;
// Normalise magnetometer measurement
// Will sqrt work better? PX4 system is powerful enough?
recipNorm = invSqrt(mx * mx + my * my + mz * mz);
mx *= recipNorm;
my *= recipNorm;
mz *= recipNorm;
// Reference direction of Earth's magnetic field
hx = 2.0f * (mx * (0.5f - q2q2 - q3q3) + my * (q1q2 - q0q3) + mz * (q1q3 + q0q2));
hy = 2.0f * (mx * (q1q2 + q0q3) + my * (0.5f - q1q1 - q3q3) + mz * (q2q3 - q0q1));
hz = 2.0f * mx * (q1q3 - q0q2) + 2.0f * my * (q2q3 + q0q1) + 2.0f * mz * (0.5f - q1q1 - q2q2);
bx = sqrt(hx * hx + hy * hy);
bz = hz;
// Estimated direction of magnetic field
halfwx = bx * (0.5f - q2q2 - q3q3) + bz * (q1q3 - q0q2);
halfwy = bx * (q1q2 - q0q3) + bz * (q0q1 + q2q3);
halfwz = bx * (q0q2 + q1q3) + bz * (0.5f - q1q1 - q2q2);
// Error is sum of cross product between estimated direction and measured direction of field vectors
halfex += (my * halfwz - mz * halfwy);
halfey += (mz * halfwx - mx * halfwz);
halfez += (mx * halfwy - my * halfwx);
}
// Compute feedback only if accelerometer measurement valid (avoids NaN in accelerometer normalisation)
if(!((ax == 0.0f) && (ay == 0.0f) && (az == 0.0f))) {
float halfvx, halfvy, halfvz;
// Normalise accelerometer measurement
recipNorm = invSqrt(ax * ax + ay * ay + az * az);
ax *= recipNorm;
ay *= recipNorm;
az *= recipNorm;
// Estimated direction of gravity and magnetic field
halfvx = q1q3 - q0q2;
halfvy = q0q1 + q2q3;
halfvz = q0q0 - 0.5f + q3q3;
// Error is sum of cross product between estimated direction and measured direction of field vectors
halfex += ay * halfvz - az * halfvy;
halfey += az * halfvx - ax * halfvz;
halfez += ax * halfvy - ay * halfvx;
}
// Apply feedback only when valid data has been gathered from the accelerometer or magnetometer
if(halfex != 0.0f && halfey != 0.0f && halfez != 0.0f) {
// Compute and apply integral feedback if enabled
if(twoKi > 0.0f) {
gyro_bias[0] += twoKi * halfex * dt; // integral error scaled by Ki
gyro_bias[1] += twoKi * halfey * dt;
gyro_bias[2] += twoKi * halfez * dt;
// apply integral feedback
gx += gyro_bias[0];
gy += gyro_bias[1];
gz += gyro_bias[2];
}
else {
gyro_bias[0] = 0.0f; // prevent integral windup
gyro_bias[1] = 0.0f;
gyro_bias[2] = 0.0f;
}
// Apply proportional feedback
gx += twoKp * halfex;
gy += twoKp * halfey;
gz += twoKp * halfez;
}
//! Integrate rate of change of quaternion
#if 0
gx *= (0.5f * dt); // pre-multiply common factors
gy *= (0.5f * dt);
gz *= (0.5f * dt);
#endif
// Time derivative of quaternion. q_dot = 0.5*q\otimes omega.
//! q_k = q_{k-1} + dt*\dot{q}
//! \dot{q} = 0.5*q \otimes P(\omega)
dq0 = 0.5f*(-q1 * gx - q2 * gy - q3 * gz);
dq1 = 0.5f*(q0 * gx + q2 * gz - q3 * gy);
dq2 = 0.5f*(q0 * gy - q1 * gz + q3 * gx);
dq3 = 0.5f*(q0 * gz + q1 * gy - q2 * gx);
q0 += dt*dq0;
q1 += dt*dq1;
q2 += dt*dq2;
q3 += dt*dq3;
// Normalise quaternion
recipNorm = invSqrt(q0 * q0 + q1 * q1 + q2 * q2 + q3 * q3);
q0 *= recipNorm;
q1 *= recipNorm;
q2 *= recipNorm;
q3 *= recipNorm;
// Auxiliary variables to avoid repeated arithmetic
q0q0 = q0 * q0;
q0q1 = q0 * q1;
q0q2 = q0 * q2;
q0q3 = q0 * q3;
q1q1 = q1 * q1;
q1q2 = q1 * q2;
q1q3 = q1 * q3;
q2q2 = q2 * q2;
q2q3 = q2 * q3;
q3q3 = q3 * q3;
}
/*
* Nonliner complementary filter on SO(3), attitude estimator main function.
*
* Estimates the attitude once started.
*
* @param argc number of commandline arguments (plus command name)
* @param argv strings containing the arguments
*/
int attitude_estimator_so3_thread_main(int argc, char *argv[])
{
//! Time constant
float dt = 0.005f;
/* output euler angles */
float euler[3] = {0.0f, 0.0f, 0.0f};
/* Initialization */
float Rot_matrix[9] = {1.f, 0.0f, 0.0f, 0.0f, 1.f, 0.0f, 0.0f, 0.0f, 1.f }; /**< init: identity matrix */
float acc[3] = {0.0f, 0.0f, 0.0f};
float gyro[3] = {0.0f, 0.0f, 0.0f};
float mag[3] = {0.0f, 0.0f, 0.0f};
warnx("main thread started");
struct sensor_combined_s raw;
memset(&raw, 0, sizeof(raw));
//! Initialize attitude vehicle uORB message.
struct vehicle_attitude_s att;
memset(&att, 0, sizeof(att));
struct vehicle_control_mode_s control_mode;
memset(&control_mode, 0, sizeof(control_mode));
uint64_t last_data = 0;
uint64_t last_measurement = 0;
/* subscribe to raw data */
int sub_raw = orb_subscribe(ORB_ID(sensor_combined));
/* rate-limit raw data updates to 333 Hz (sensors app publishes at 200, so this is just paranoid) */
orb_set_interval(sub_raw, 3);
/* subscribe to param changes */
int sub_params = orb_subscribe(ORB_ID(parameter_update));
/* subscribe to control mode */
int sub_control_mode = orb_subscribe(ORB_ID(vehicle_control_mode));
/* advertise attitude */
orb_advert_t att_pub = orb_advertise(ORB_ID(vehicle_attitude), &att);
int loopcounter = 0;
thread_running = true;
// XXX write this out to perf regs
/* keep track of sensor updates */
uint64_t sensor_last_timestamp[3] = {0, 0, 0};
struct attitude_estimator_so3_params so3_comp_params;
struct attitude_estimator_so3_param_handles so3_comp_param_handles;
/* initialize parameter handles */
parameters_init(&so3_comp_param_handles);
parameters_update(&so3_comp_param_handles, &so3_comp_params);
uint64_t start_time = hrt_absolute_time();
bool initialized = false;
bool state_initialized = false;
float gyro_offsets[3] = { 0.0f, 0.0f, 0.0f };
unsigned offset_count = 0;
/* register the perf counter */
perf_counter_t so3_comp_loop_perf = perf_alloc(PC_ELAPSED, "attitude_estimator_so3");
/* Main loop*/
while (!thread_should_exit) {
struct pollfd fds[2];
fds[0].fd = sub_raw;
fds[0].events = POLLIN;
fds[1].fd = sub_params;
fds[1].events = POLLIN;
int ret = poll(fds, 2, 1000);
if (ret < 0) {
/* XXX this is seriously bad - should be an emergency */
} else if (ret == 0) {
/* check if we're in HIL - not getting sensor data is fine then */
orb_copy(ORB_ID(vehicle_control_mode), sub_control_mode, &control_mode);
if (!control_mode.flag_system_hil_enabled) {
warnx("WARNING: Not getting sensors - sensor app running?");
}
} else {
/* only update parameters if they changed */
if (fds[1].revents & POLLIN) {
/* read from param to clear updated flag */
struct parameter_update_s update;
orb_copy(ORB_ID(parameter_update), sub_params, &update);
/* update parameters */
parameters_update(&so3_comp_param_handles, &so3_comp_params);
}
/* only run filter if sensor values changed */
if (fds[0].revents & POLLIN) {
/* get latest measurements */
orb_copy(ORB_ID(sensor_combined), sub_raw, &raw);
if (!initialized) {
gyro_offsets[0] += raw.gyro_rad_s[0];
gyro_offsets[1] += raw.gyro_rad_s[1];
gyro_offsets[2] += raw.gyro_rad_s[2];
offset_count++;
if (hrt_absolute_time() > start_time + 3000000l) {
initialized = true;
gyro_offsets[0] /= offset_count;
gyro_offsets[1] /= offset_count;
gyro_offsets[2] /= offset_count;
warnx("gyro initialized, offsets: %.5f %.5f %.5f", (double)gyro_offsets[0], (double)gyro_offsets[1], (double)gyro_offsets[2]);
}
} else {
perf_begin(so3_comp_loop_perf);
/* Calculate data time difference in seconds */
dt = (raw.timestamp - last_measurement) / 1000000.0f;
last_measurement = raw.timestamp;
/* Fill in gyro measurements */
if (sensor_last_timestamp[0] != raw.timestamp) {
sensor_last_timestamp[0] = raw.timestamp;
}
gyro[0] = raw.gyro_rad_s[0] - gyro_offsets[0];
gyro[1] = raw.gyro_rad_s[1] - gyro_offsets[1];
gyro[2] = raw.gyro_rad_s[2] - gyro_offsets[2];
/* update accelerometer measurements */
if (sensor_last_timestamp[1] != raw.accelerometer_timestamp) {
sensor_last_timestamp[1] = raw.accelerometer_timestamp;
}
acc[0] = raw.accelerometer_m_s2[0];
acc[1] = raw.accelerometer_m_s2[1];
acc[2] = raw.accelerometer_m_s2[2];
/* update magnetometer measurements */
if (sensor_last_timestamp[2] != raw.magnetometer_timestamp) {
sensor_last_timestamp[2] = raw.magnetometer_timestamp;
}
mag[0] = raw.magnetometer_ga[0];
mag[1] = raw.magnetometer_ga[1];
mag[2] = raw.magnetometer_ga[2];
/* initialize with good values once we have a reasonable dt estimate */
if (!state_initialized && dt < 0.05f && dt > 0.001f) {
state_initialized = true;
warnx("state initialized");
}
/* do not execute the filter if not initialized */
if (!state_initialized) {
continue;
}
// NOTE : Accelerometer is reversed.
// Because proper mount of PX4 will give you a reversed accelerometer readings.
NonlinearSO3AHRSupdate(gyro[0], gyro[1], gyro[2],
-acc[0], -acc[1], -acc[2],
mag[0], mag[1], mag[2],
so3_comp_params.Kp,
so3_comp_params.Ki,
dt);
// Convert q->R, This R converts inertial frame to body frame.
Rot_matrix[0] = q0q0 + q1q1 - q2q2 - q3q3;// 11
Rot_matrix[1] = 2.f * (q1*q2 + q0*q3); // 12
Rot_matrix[2] = 2.f * (q1*q3 - q0*q2); // 13
Rot_matrix[3] = 2.f * (q1*q2 - q0*q3); // 21
Rot_matrix[4] = q0q0 - q1q1 + q2q2 - q3q3;// 22
Rot_matrix[5] = 2.f * (q2*q3 + q0*q1); // 23
Rot_matrix[6] = 2.f * (q1*q3 + q0*q2); // 31
Rot_matrix[7] = 2.f * (q2*q3 - q0*q1); // 32
Rot_matrix[8] = q0q0 - q1q1 - q2q2 + q3q3;// 33
//1-2-3 Representation.
//Equation (290)
//Representing Attitude: Euler Angles, Unit Quaternions, and Rotation Vectors, James Diebel.
// Existing PX4 EKF code was generated by MATLAB which uses coloum major order matrix.
euler[0] = atan2f(Rot_matrix[5], Rot_matrix[8]); //! Roll
euler[1] = -asinf(Rot_matrix[2]); //! Pitch
euler[2] = atan2f(Rot_matrix[1], Rot_matrix[0]); //! Yaw
/* swap values for next iteration, check for fatal inputs */
if (isfinite(euler[0]) && isfinite(euler[1]) && isfinite(euler[2])) {
// Publish only finite euler angles
att.roll = euler[0] - so3_comp_params.roll_off;
att.pitch = euler[1] - so3_comp_params.pitch_off;
att.yaw = euler[2] - so3_comp_params.yaw_off;
} else {
/* due to inputs or numerical failure the output is invalid, skip it */
// Due to inputs or numerical failure the output is invalid
warnx("infinite euler angles, rotation matrix:");
warnx("%.3f %.3f %.3f", (double)Rot_matrix[0], (double)Rot_matrix[1], (double)Rot_matrix[2]);
warnx("%.3f %.3f %.3f", (double)Rot_matrix[3], (double)Rot_matrix[4], (double)Rot_matrix[5]);
warnx("%.3f %.3f %.3f", (double)Rot_matrix[6], (double)Rot_matrix[7], (double)Rot_matrix[8]);
// Don't publish anything
continue;
}
if (last_data > 0 && raw.timestamp > last_data + 12000) {
warnx("sensor data missed");
}
last_data = raw.timestamp;
/* send out */
att.timestamp = raw.timestamp;
// Quaternion
att.q[0] = q0;
att.q[1] = q1;
att.q[2] = q2;
att.q[3] = q3;
att.q_valid = true;
// Euler angle rate. But it needs to be investigated again.
/*
att.rollspeed = 2.0f*(-q1*dq0 + q0*dq1 - q3*dq2 + q2*dq3);
att.pitchspeed = 2.0f*(-q2*dq0 + q3*dq1 + q0*dq2 - q1*dq3);
att.yawspeed = 2.0f*(-q3*dq0 -q2*dq1 + q1*dq2 + q0*dq3);
*/
att.rollspeed = gyro[0];
att.pitchspeed = gyro[1];
att.yawspeed = gyro[2];
att.rollacc = 0;
att.pitchacc = 0;
att.yawacc = 0;
/* TODO: Bias estimation required */
memcpy(&att.rate_offsets, &(gyro_bias), sizeof(att.rate_offsets));
/* copy rotation matrix */
memcpy(&att.R, Rot_matrix, sizeof(float)*9);
att.R_valid = true;
// Publish
if (att_pub != nullptr) {
orb_publish(ORB_ID(vehicle_attitude), att_pub, &att);
} else {
warnx("NaN in roll/pitch/yaw estimate!");
orb_advertise(ORB_ID(vehicle_attitude), &att);
}
perf_end(so3_comp_loop_perf);
}
}
}
loopcounter++;
}
thread_running = false;
return 0;
}

86
src/modules/attitude_estimator_so3/attitude_estimator_so3_params.c
View File

@ -1,86 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2013 PX4 Development Team. All rights reserved.
* Author: Hyon Lim <limhyon@gmail.com>
* 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
* 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
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/*
* @file attitude_estimator_so3_params.c
*
* Parameters for nonlinear complementary filters on the SO(3).
*/
#include "attitude_estimator_so3_params.h"
/* This is filter gain for nonlinear SO3 complementary filter */
/* NOTE : How to tune the gain? First of all, stick with this default gain. And let the quad in stable place.
Log the steady state reponse of filter. If it is too slow, increase SO3_COMP_KP.
If you are flying from ground to high altitude in short amount of time, please increase SO3_COMP_KI which
will compensate gyro bias which depends on temperature and vibration of your vehicle */
PARAM_DEFINE_FLOAT(SO3_COMP_KP, 1.0f); //! This parameter will give you about 15 seconds convergence time.
//! You can set this gain higher if you want more fast response.
//! But note that higher gain will give you also higher overshoot.
PARAM_DEFINE_FLOAT(SO3_COMP_KI, 0.05f); //! This gain will incorporate slow time-varying bias (e.g., temperature change)
//! This gain is depend on your vehicle status.
/* offsets in roll, pitch and yaw of sensor plane and body */
PARAM_DEFINE_FLOAT(SO3_ROLL_OFFS, 0.0f);
PARAM_DEFINE_FLOAT(SO3_PITCH_OFFS, 0.0f);
PARAM_DEFINE_FLOAT(SO3_YAW_OFFS, 0.0f);
int parameters_init(struct attitude_estimator_so3_param_handles *h)
{
/* Filter gain parameters */
h->Kp = param_find("SO3_COMP_KP");
h->Ki = param_find("SO3_COMP_KI");
/* Attitude offset (WARNING: Do not change if you do not know what exactly this variable wil lchange) */
h->roll_off = param_find("SO3_ROLL_OFFS");
h->pitch_off = param_find("SO3_PITCH_OFFS");
h->yaw_off = param_find("SO3_YAW_OFFS");
return OK;
}
int parameters_update(const struct attitude_estimator_so3_param_handles *h, struct attitude_estimator_so3_params *p)
{
/* Update filter gain */
param_get(h->Kp, &(p->Kp));
param_get(h->Ki, &(p->Ki));
/* Update attitude offset */
param_get(h->roll_off, &(p->roll_off));
param_get(h->pitch_off, &(p->pitch_off));
param_get(h->yaw_off, &(p->yaw_off));
return OK;
}

67
src/modules/attitude_estimator_so3/attitude_estimator_so3_params.h
View File

@ -1,67 +0,0 @@
/****************************************************************************
*
* Copyright (C) 2013 PX4 Development Team. All rights reserved.
* Author: Hyon Lim <limhyon@gmail.com>
* 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
* 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
* FOR A PARTICULAR PURPOSE ARE DISCLAIMED. IN NO EVENT SHALL THE
* COPYRIGHT OWNER OR CONTRIBUTORS BE LIABLE FOR ANY DIRECT, INDIRECT,
* INCIDENTAL, SPECIAL, EXEMPLARY, OR CONSEQUENTIAL DAMAGES (INCLUDING,
* BUT NOT LIMITED TO, PROCUREMENT OF SUBSTITUTE GOODS OR SERVICES; LOSS
* OF USE, DATA, OR PROFITS; OR BUSINESS INTERRUPTION) HOWEVER CAUSED
* AND ON ANY THEORY OF LIABILITY, WHETHER IN CONTRACT, STRICT
* LIABILITY, OR TORT (INCLUDING NEGLIGENCE OR OTHERWISE) ARISING IN
* ANY WAY OUT OF THE USE OF THIS SOFTWARE, EVEN IF ADVISED OF THE
* POSSIBILITY OF SUCH DAMAGE.
*
****************************************************************************/
/*
* @file attitude_estimator_so3_params.h
*
* Parameters for nonlinear complementary filters on the SO(3).
*/
#include <systemlib/param/param.h>
struct attitude_estimator_so3_params {
float Kp;
float Ki;
float roll_off;
float pitch_off;
float yaw_off;
};
struct attitude_estimator_so3_param_handles {
param_t Kp, Ki;
param_t roll_off, pitch_off, yaw_off;
};
/**
* Initialize all parameter handles and values
*
*/
int parameters_init(struct attitude_estimator_so3_param_handles *h);
/**
* Update all parameters
*
*/
int parameters_update(const struct attitude_estimator_so3_param_handles *h, struct attitude_estimator_so3_params *p);

12
src/modules/attitude_estimator_so3/module.mk
View File

@ -1,12 +0,0 @@
#
# Attitude estimator (Nonlinear SO(3) complementary Filter)
#
MODULE_COMMAND = attitude_estimator_so3
SRCS = attitude_estimator_so3_main.cpp \
attitude_estimator_so3_params.c
MODULE_STACKSIZE = 1200
EXTRACXXFLAGS = -Wno-float-equal