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Merge remote-tracking branch 'upstream/master' into fw_autoland_att_tecs_navigator_termination_controlgroups

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Conflicts:
	src/drivers/px4io/px4io.cpp
This commit is contained in:
Thomas Gubler
2013-12-13 21:07:27 +01:00
parent 54e739926d 0b9b68f0d9
commit c3cbaf5deb
43 changed files with 1364 additions and 877 deletions
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src/modules/attitude_estimator_so3/README
+3
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@@ -0,0 +1,3 @@
Synopsis
nsh> attitude_estimator_so3_comp start
src/modules/attitude_estimator_so3_comp/attitude_estimator_so3_comp_main.cpp → src/modules/attitude_estimator_so3/attitude_estimator_so3_main.cpp
+171 -328
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@@ -1,16 +1,49 @@
/*
* Author: Hyon Lim <limhyon@gmail.com, hyonlim@snu.ac.kr>
/****************************************************************************
*
* @file attitude_estimator_so3_comp_main.c
* 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_main.cpp
*
* 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
@@ -46,94 +79,91 @@
#ifdef __cplusplus
extern "C" {
#endif
#include "attitude_estimator_so3_comp_params.h"
#include "attitude_estimator_so3_params.h"
#ifdef __cplusplus
}
#endif
extern "C" __EXPORT int attitude_estimator_so3_comp_main(int argc, char *argv[]);
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_comp_task; /**< Handle of deamon task / thread */
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 bool bFilterInit = false;
//! Auxiliary variables to reduce number of repeated operations
static float q0q0, q0q1, q0q2, q0q3;
static float q1q1, q1q2, q1q3;
static float q2q2, q2q3;
static float q3q3;
//! Serial packet related
static int uart;
static int baudrate;
static bool bFilterInit = false;
/**
* Mainloop of attitude_estimator_so3_comp.
* Mainloop of attitude_estimator_so3.
*/
int attitude_estimator_so3_comp_thread_main(int argc, char *argv[]);
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_comp {start|stop|status} [-d <devicename>] [-b <baud rate>]\n"
"-d and -b options are for separate visualization with raw data (quaternion packet) transfer\n"
"ex) attitude_estimator_so3_comp start -d /dev/ttyS1 -b 115200\n");
fprintf(stderr, "usage: attitude_estimator_so3 {start|stop|status}\n");
exit(1);
}
/**
* The attitude_estimator_so3_comp app only briefly exists to start
* 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 task_create().
*/
int attitude_estimator_so3_comp_main(int argc, char *argv[])
int attitude_estimator_so3_main(int argc, char *argv[])
{
if (argc < 1)
usage("missing command");
if (!strcmp(argv[1], "start")) {
if (thread_running) {
printf("attitude_estimator_so3_comp already running\n");
warnx("already running\n");
/* this is not an error */
exit(0);
}
thread_should_exit = false;
attitude_estimator_so3_comp_task = task_spawn_cmd("attitude_estimator_so3_comp",
attitude_estimator_so3_task = task_spawn_cmd("attitude_estimator_so3",
SCHED_DEFAULT,
SCHED_PRIORITY_MAX - 5,
12400,
attitude_estimator_so3_comp_thread_main,
(const char **)argv);
14000,
attitude_estimator_so3_thread_main,
(argv) ? (const char **)&argv[2] : (const char **)NULL);
exit(0);
}
if (!strcmp(argv[1], "stop")) {
thread_should_exit = true;
while(thread_running){
while (thread_running){
usleep(200000);
printf(".");
}
printf("terminated.");
warnx("stopped");
exit(0);
}
@@ -157,7 +187,8 @@ int attitude_estimator_so3_comp_main(int argc, char *argv[])
//---------------------------------------------------------------------------------------------------
// Fast inverse square-root
// See: http://en.wikipedia.org/wiki/Fast_inverse_square_root
float invSqrt(float number) {
float invSqrt(float number)
{
volatile long i;
volatile float x, y;
volatile const float f = 1.5F;
@@ -221,48 +252,47 @@ void NonlinearSO3AHRSinit(float ax, float ay, float az, float mx, float my, floa
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) {
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)
{
// 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)) {
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;
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 * mx * (q1q3 - q0q2) + 2 * my * (q2q3 + q0q1) + 2 * mz * (0.5 - q1q1 - q2q2);
bx = sqrt(hx * hx + hy * hy);
bz = hz;
// 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);
// 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);
// 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)
@@ -293,7 +323,9 @@ void NonlinearSO3AHRSupdate(float gx, float gy, float gz, float ax, float ay, fl
gyro_bias[0] += twoKi * halfex * dt; // integral error scaled by Ki
gyro_bias[1] += twoKi * halfey * dt;
gyro_bias[2] += twoKi * halfez * dt;
gx += gyro_bias[0]; // apply integral feedback
// apply integral feedback
gx += gyro_bias[0];
gy += gyro_bias[1];
gz += gyro_bias[2];
}
@@ -337,208 +369,43 @@ void NonlinearSO3AHRSupdate(float gx, float gy, float gz, float ax, float ay, fl
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;
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 send_uart_byte(char c)
{
write(uart,&c,1);
}
void send_uart_bytes(uint8_t *data, int length)
{
write(uart,data,(size_t)(sizeof(uint8_t)*length));
}
void send_uart_float(float f) {
uint8_t * b = (uint8_t *) &f;
//! Assume float is 4-bytes
for(int i=0; i<4; i++) {
uint8_t b1 = (b[i] >> 4) & 0x0f;
uint8_t b2 = (b[i] & 0x0f);
uint8_t c1 = (b1 < 10) ? ('0' + b1) : 'A' + b1 - 10;
uint8_t c2 = (b2 < 10) ? ('0' + b2) : 'A' + b2 - 10;
send_uart_bytes(&c1,1);
send_uart_bytes(&c2,1);
}
}
void send_uart_float_arr(float *arr, int length)
{
for(int i=0;i<length;++i)
{
send_uart_float(arr[i]);
send_uart_byte(',');
}
}
int open_uart(int baud, const char *uart_name, struct termios *uart_config_original, bool *is_usb)
{
int speed;
switch (baud) {
case 0: speed = B0; break;
case 50: speed = B50; break;
case 75: speed = B75; break;
case 110: speed = B110; break;
case 134: speed = B134; break;
case 150: speed = B150; break;
case 200: speed = B200; break;
case 300: speed = B300; break;
case 600: speed = B600; break;
case 1200: speed = B1200; break;
case 1800: speed = B1800; break;
case 2400: speed = B2400; break;
case 4800: speed = B4800; break;
case 9600: speed = B9600; break;
case 19200: speed = B19200; break;
case 38400: speed = B38400; break;
case 57600: speed = B57600; break;
case 115200: speed = B115200; break;
case 230400: speed = B230400; break;
case 460800: speed = B460800; break;
case 921600: speed = B921600; break;
default:
printf("ERROR: Unsupported baudrate: %d\n\tsupported examples:\n\n\t9600\n19200\n38400\n57600\n115200\n230400\n460800\n921600\n\n", baud);
return -EINVAL;
}
printf("[so3_comp_filt] UART is %s, baudrate is %d\n", uart_name, baud);
uart = open(uart_name, O_RDWR | O_NOCTTY);
/* Try to set baud rate */
struct termios uart_config;
int termios_state;
*is_usb = false;
/* make some wild guesses including that USB serial is indicated by either /dev/ttyACM0 or /dev/console */
if (strcmp(uart_name, "/dev/ttyACM0") != OK && strcmp(uart_name, "/dev/console") != OK) {
/* Back up the original uart configuration to restore it after exit */
if ((termios_state = tcgetattr(uart, uart_config_original)) < 0) {
printf("ERROR getting baudrate / termios config for %s: %d\n", uart_name, termios_state);
close(uart);
return -1;
}
/* Fill the struct for the new configuration */
tcgetattr(uart, &uart_config);
/* Clear ONLCR flag (which appends a CR for every LF) */
uart_config.c_oflag &= ~ONLCR;
/* Set baud rate */
if (cfsetispeed(&uart_config, speed) < 0 || cfsetospeed(&uart_config, speed) < 0) {
printf("ERROR setting baudrate / termios config for %s: %d (cfsetispeed, cfsetospeed)\n", uart_name, termios_state);
close(uart);
return -1;
}
if ((termios_state = tcsetattr(uart, TCSANOW, &uart_config)) < 0) {
printf("ERROR setting baudrate / termios config for %s (tcsetattr)\n", uart_name);
close(uart);
return -1;
}
} else {
*is_usb = true;
}
return uart;
q2q2 = q2 * q2;
q2q3 = q2 * q3;
q3q3 = q3 * q3;
}
/*
* [Rot_matrix,x_aposteriori,P_aposteriori] = attitudeKalmanfilter(dt,z_k,x_aposteriori_k,P_aposteriori_k,knownConst)
*/
/*
* EKF Attitude Estimator main function.
* Nonliner complementary filter on SO(3), attitude estimator main function.
*
* Estimates the attitude recursively once started.
* Estimates the attitude once started.
*
* @param argc number of commandline arguments (plus command name)
* @param argv strings containing the arguments
*/
int attitude_estimator_so3_comp_thread_main(int argc, char *argv[])
int attitude_estimator_so3_thread_main(int argc, char *argv[])
{
const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
//! Serial debug related
int ch;
struct termios uart_config_original;
bool usb_uart;
bool debug_mode = false;
char *device_name = "/dev/ttyS2";
baudrate = 115200;
const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
//! Time constant
float dt = 0.005f;
/* output euler angles */
float euler[3] = {0.0f, 0.0f, 0.0f};
float Rot_matrix[9] = {1.f, 0, 0,
0, 1.f, 0,
0, 0, 1.f
}; /**< init: identity matrix */
/* 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};
/* work around some stupidity in task_create's argv handling */
argc -= 2;
argv += 2;
//! -d <device_name>, default : /dev/ttyS2
//! -b <baud_rate>, default : 115200
while ((ch = getopt(argc,argv,"d:b:")) != EOF){
switch(ch){
case 'b':
baudrate = strtoul(optarg, NULL, 10);
if(baudrate == 0)
printf("invalid baud rate '%s'",optarg);
break;
case 'd':
device_name = optarg;
debug_mode = true;
break;
default:
usage("invalid argument");
}
}
if(debug_mode){
printf("Opening debugging port for 3D visualization\n");
uart = open_uart(baudrate, device_name, &uart_config_original, &usb_uart);
if (uart < 0)
printf("could not open %s", device_name);
else
printf("Open port success\n");
}
// print text
printf("Nonlinear SO3 Attitude Estimator initialized..\n\n");
fflush(stdout);
int overloadcounter = 19;
/* store start time to guard against too slow update rates */
uint64_t last_run = hrt_absolute_time();
warnx("main thread started");
struct sensor_combined_s raw;
memset(&raw, 0, sizeof(raw));
@@ -555,8 +422,8 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
/* subscribe to raw data */
int sub_raw = orb_subscribe(ORB_ID(sensor_combined));
/* rate-limit raw data updates to 200Hz */
orb_set_interval(sub_raw, 4);
/* 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));
@@ -565,17 +432,15 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
int sub_control_mode = orb_subscribe(ORB_ID(vehicle_control_mode));
/* advertise attitude */
orb_advert_t pub_att = orb_advertise(ORB_ID(vehicle_attitude), &att);
//orb_advert_t pub_att = orb_advertise(ORB_ID(vehicle_attitude), &att);
//orb_advert_t att_pub = -1;
orb_advert_t att_pub = orb_advertise(ORB_ID(vehicle_attitude), &att);
int loopcounter = 0;
int printcounter = 0;
thread_running = true;
/* advertise debug value */
// struct debug_key_value_s dbg = { .key = "", .value = 0.0f };
// orb_advert_t pub_dbg = -1;
float sensor_update_hz[3] = {0.0f, 0.0f, 0.0f};
// XXX write this out to perf regs
@@ -583,20 +448,22 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
uint32_t sensor_last_count[3] = {0, 0, 0};
uint64_t sensor_last_timestamp[3] = {0, 0, 0};
struct attitude_estimator_so3_comp_params so3_comp_params;
struct attitude_estimator_so3_comp_param_handles so3_comp_param_handles;
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_comp");
perf_counter_t so3_comp_loop_perf = perf_alloc(PC_ELAPSED, "attitude_estimator_so3");
/* Main loop*/
while (!thread_should_exit) {
@@ -615,12 +482,9 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
orb_copy(ORB_ID(vehicle_control_mode), sub_control_mode, &control_mode);
if (!control_mode.flag_system_hil_enabled) {
fprintf(stderr,
"[att so3_comp] WARNING: Not getting sensors - sensor app running?\n");
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 */
@@ -644,11 +508,12 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
gyro_offsets[2] += raw.gyro_rad_s[2];
offset_count++;
if (hrt_absolute_time() - start_time > 3000000LL) {
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", gyro_offsets[0], gyro_offsets[1], gyro_offsets[2]);
}
} else {
@@ -668,9 +533,9 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
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];
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_count[1] != raw.accelerometer_counter) {
@@ -696,31 +561,14 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
mag[1] = raw.magnetometer_ga[1];
mag[2] = raw.magnetometer_ga[2];
uint64_t now = hrt_absolute_time();
unsigned int time_elapsed = now - last_run;
last_run = now;
if (time_elapsed > loop_interval_alarm) {
//TODO: add warning, cpu overload here
// if (overloadcounter == 20) {
// printf("CPU OVERLOAD DETECTED IN ATTITUDE ESTIMATOR EKF (%lu > %lu)\n", time_elapsed, loop_interval_alarm);
// overloadcounter = 0;
// }
overloadcounter++;
}
static bool const_initialized = false;
/* initialize with good values once we have a reasonable dt estimate */
if (!const_initialized && dt < 0.05f && dt > 0.005f) {
dt = 0.005f;
parameters_update(&so3_comp_param_handles, &so3_comp_params);
const_initialized = true;
if (!state_initialized && dt < 0.05f && dt > 0.001f) {
state_initialized = true;
warnx("state initialized");
}
/* do not execute the filter if not initialized */
if (!const_initialized) {
if (!state_initialized) {
continue;
}
@@ -728,18 +576,23 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
// 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);
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] = 2.0 * (q1*q2 + q0*q3); // 12
Rot_matrix[2] = 2.0 * (q1*q3 - q0*q2); // 13
Rot_matrix[3] = 2.0 * (q1*q2 - q0*q3); // 21
Rot_matrix[4] = q0q0 - q1q1 + q2q2 - q3q3;// 22
Rot_matrix[5] = 2.0 * (q2*q3 + q0*q1); // 23
Rot_matrix[6] = 2.0 * (q1*q3 + q0*q2); // 31
Rot_matrix[7] = 2.0 * (q2*q3 - q0*q1); // 32
Rot_matrix[8] = q0q0 - q1q1 - q2q2 + q3q3;// 33
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)
@@ -747,29 +600,42 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
// 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
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])) {
/* Do something */
// 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", Rot_matrix[0], Rot_matrix[1], Rot_matrix[2]);
warnx("%.3f %.3f %.3f", Rot_matrix[3], Rot_matrix[4], Rot_matrix[5]);
warnx("%.3f %.3f %.3f", Rot_matrix[6], Rot_matrix[7], Rot_matrix[8]);
// Don't publish anything
continue;
}
if (last_data > 0 && raw.timestamp - last_data > 12000) printf("[attitude estimator so3_comp] sensor data missed! (%llu)\n", raw.timestamp - last_data);
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;
// XXX Apply the same transformation to the rotation matrix
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;
//! Euler angle rate. But it needs to be investigated again.
// 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);
@@ -783,53 +649,30 @@ const unsigned int loop_interval_alarm = 6500; // loop interval in microseconds
att.pitchacc = 0;
att.yawacc = 0;
//! Quaternion
att.q[0] = q0;
att.q[1] = q1;
att.q[2] = q2;
att.q[3] = q3;
att.q_valid = true;
/* 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;
if (isfinite(att.roll) && isfinite(att.pitch) && isfinite(att.yaw)) {
// Broadcast
orb_publish(ORB_ID(vehicle_attitude), pub_att, &att);
// Publish
if (att_pub > 0) {
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);
//! This will print out debug packet to visualization software
if(debug_mode)
{
float quat[4];
quat[0] = q0;
quat[1] = q1;
quat[2] = q2;
quat[3] = q3;
send_uart_float_arr(quat,4);
send_uart_byte('\n');
}
}
}
}
loopcounter++;
}// while
}
thread_running = false;
/* Reset the UART flags to original state */
if (!usb_uart)
tcsetattr(uart, TCSANOW, &uart_config_original);
return 0;
}
src/modules/attitude_estimator_so3/attitude_estimator_so3_params.c
Executable
+86
View File
@@ -0,0 +1,86 @@
/****************************************************************************
*
* 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;
}
src/modules/attitude_estimator_so3/attitude_estimator_so3_params.h
Executable
+67
View File
@@ -0,0 +1,67 @@
/****************************************************************************
*
* 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);
src/modules/attitude_estimator_so3/module.mk
+8
View File
@@ -0,0 +1,8 @@
#
# Attitude estimator (Nonlinear SO(3) complementary Filter)
#
MODULE_COMMAND = attitude_estimator_so3
SRCS = attitude_estimator_so3_main.cpp \
attitude_estimator_so3_params.c
src/modules/attitude_estimator_so3_comp/README
-5
View File
@@ -1,5 +0,0 @@
Synopsis
nsh> attitude_estimator_so3_comp start -d /dev/ttyS1 -b 115200
Option -d is for debugging packet. See code for detailed packet structure.
src/modules/attitude_estimator_so3_comp/attitude_estimator_so3_comp_params.c
-63
View File
@@ -1,63 +0,0 @@
/*
* Author: Hyon Lim <limhyon@gmail.com, hyonlim@snu.ac.kr>
*
* @file attitude_estimator_so3_comp_params.c
*
* 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 "attitude_estimator_so3_comp_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(ATT_ROLL_OFFS, 0.0f);
PARAM_DEFINE_FLOAT(ATT_PITCH_OFFS, 0.0f);
PARAM_DEFINE_FLOAT(ATT_YAW_OFFS, 0.0f);
int parameters_init(struct attitude_estimator_so3_comp_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("ATT_ROLL_OFFS");
h->pitch_off = param_find("ATT_PITCH_OFFS");
h->yaw_off = param_find("ATT_YAW_OFFS");
return OK;
}
int parameters_update(const struct attitude_estimator_so3_comp_param_handles *h, struct attitude_estimator_so3_comp_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;
}
src/modules/attitude_estimator_so3_comp/attitude_estimator_so3_comp_params.h
-44
View File
@@ -1,44 +0,0 @@
/*
* Author: Hyon Lim <limhyon@gmail.com, hyonlim@snu.ac.kr>
*
* @file attitude_estimator_so3_comp_params.h
*
* 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 <systemlib/param/param.h>
struct attitude_estimator_so3_comp_params {
float Kp;
float Ki;
float roll_off;
float pitch_off;
float yaw_off;
};
struct attitude_estimator_so3_comp_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_comp_param_handles *h);
/**
* Update all parameters
*
*/
int parameters_update(const struct attitude_estimator_so3_comp_param_handles *h, struct attitude_estimator_so3_comp_params *p);
src/modules/attitude_estimator_so3_comp/module.mk
-8
View File
@@ -1,8 +0,0 @@
#
# Attitude estimator (Nonlinear SO3 complementary Filter)
#
MODULE_COMMAND = attitude_estimator_so3_comp
SRCS = attitude_estimator_so3_comp_main.cpp \
attitude_estimator_so3_comp_params.c
src/modules/fw_att_control/fw_att_control_params.c
+2 -2
View File
@@ -33,9 +33,9 @@ f * Copyright (c) 2013 PX4 Development Team. All rights reserved.
****************************************************************************/
/**
* @file fw_pos_control_l1_params.c
* @file fw_att_control_params.c
*
* Parameters defined by the L1 position control task
* Parameters defined by the fixed-wing attitude control task
*
* @author Lorenz Meier <lm@inf.ethz.ch>
*/
src/modules/mavlink/mavlink_receiver.cpp
+4 -7
View File
@@ -382,16 +382,15 @@ handle_message(mavlink_message_t *msg)
/* hil gyro */
static const float mrad2rad = 1.0e-3f;
hil_sensors.gyro_counter = hil_counter;
hil_sensors.gyro_raw[0] = imu.xgyro / mrad2rad;
hil_sensors.gyro_raw[1] = imu.ygyro / mrad2rad;
hil_sensors.gyro_raw[2] = imu.zgyro / mrad2rad;
hil_sensors.gyro_rad_s[0] = imu.xgyro;
hil_sensors.gyro_rad_s[1] = imu.ygyro;
hil_sensors.gyro_rad_s[2] = imu.zgyro;
hil_sensors.gyro_counter = hil_counter;
/* accelerometer */
hil_sensors.accelerometer_counter = hil_counter;
static const float mg2ms2 = 9.8f / 1000.0f;
hil_sensors.accelerometer_raw[0] = imu.xacc / mg2ms2;
hil_sensors.accelerometer_raw[1] = imu.yacc / mg2ms2;
@@ -401,6 +400,7 @@ handle_message(mavlink_message_t *msg)
hil_sensors.accelerometer_m_s2[2] = imu.zacc;
hil_sensors.accelerometer_mode = 0; // TODO what is this?
hil_sensors.accelerometer_range_m_s2 = 32.7f; // int16
hil_sensors.accelerometer_counter = hil_counter;
/* adc */
hil_sensors.adc_voltage_v[0] = 0.0f;
@@ -409,7 +409,6 @@ handle_message(mavlink_message_t *msg)
/* magnetometer */
float mga2ga = 1.0e-3f;
hil_sensors.magnetometer_counter = hil_counter;
hil_sensors.magnetometer_raw[0] = imu.xmag / mga2ga;
hil_sensors.magnetometer_raw[1] = imu.ymag / mga2ga;
hil_sensors.magnetometer_raw[2] = imu.zmag / mga2ga;
@@ -419,15 +418,13 @@ handle_message(mavlink_message_t *msg)
hil_sensors.magnetometer_range_ga = 32.7f; // int16
hil_sensors.magnetometer_mode = 0; // TODO what is this
hil_sensors.magnetometer_cuttoff_freq_hz = 50.0f;
hil_sensors.magnetometer_counter = hil_counter;
/* baro */
hil_sensors.baro_pres_mbar = imu.abs_pressure;
hil_sensors.baro_alt_meter = imu.pressure_alt;
hil_sensors.baro_temp_celcius = imu.temperature;
hil_sensors.gyro_counter = hil_counter;
hil_sensors.magnetometer_counter = hil_counter;
hil_sensors.accelerometer_counter = hil_counter;
hil_sensors.baro_counter = hil_counter;
/* differential pressure */
hil_sensors.differential_pressure_pa = imu.diff_pressure * 1e2f; //from hPa to Pa
src/modules/mavlink/orb_listener.c
+29 -65
View File
@@ -54,6 +54,7 @@
#include <sys/prctl.h>
#include <stdlib.h>
#include <poll.h>
#include <lib/geo/geo.h>
#include <mavlink/mavlink_log.h>
@@ -72,7 +73,6 @@ struct vehicle_status_s v_status;
struct rc_channels_s rc;
struct rc_input_values rc_raw;
struct actuator_armed_s armed;
struct actuator_controls_effective_s actuators_effective_0;
struct actuator_controls_s actuators_0;
struct vehicle_attitude_s att;
struct airspeed_s airspeed;
@@ -119,7 +119,6 @@ static void l_attitude_setpoint(const struct listener *l);
static void l_actuator_outputs(const struct listener *l);
static void l_actuator_armed(const struct listener *l);
static void l_manual_control_setpoint(const struct listener *l);
static void l_vehicle_attitude_controls_effective(const struct listener *l);
static void l_vehicle_attitude_controls(const struct listener *l);
static void l_debug_key_value(const struct listener *l);
static void l_optical_flow(const struct listener *l);
@@ -147,7 +146,6 @@ static const struct listener listeners[] = {
{l_actuator_armed, &mavlink_subs.armed_sub, 0},
{l_manual_control_setpoint, &mavlink_subs.man_control_sp_sub, 0},
{l_vehicle_attitude_controls, &mavlink_subs.actuators_sub, 0},
{l_vehicle_attitude_controls_effective, &mavlink_subs.actuators_effective_sub, 0},
{l_debug_key_value, &mavlink_subs.debug_key_value, 0},
{l_optical_flow, &mavlink_subs.optical_flow, 0},
{l_vehicle_rates_setpoint, &mavlink_subs.rates_setpoint_sub, 0},
@@ -242,16 +240,29 @@ l_vehicle_attitude(const struct listener *l)
att.rollspeed,
att.pitchspeed,
att.yawspeed);
/* limit VFR message rate to 10Hz */
hrt_abstime t = hrt_absolute_time();
if (t >= last_sent_vfr + 100000) {
last_sent_vfr = t;
float groundspeed = sqrtf(global_pos.vx * global_pos.vx + global_pos.vy * global_pos.vy);
uint16_t heading = (att.yaw + M_PI_F) / M_PI_F * 180.0f;
float throttle = actuators_effective_0.control_effective[3] * (UINT16_MAX - 1);
uint16_t heading = _wrap_2pi(att.yaw) * M_RAD_TO_DEG_F;
float throttle = armed.armed ? actuators_0.control[3] * 100.0f : 0.0f;
mavlink_msg_vfr_hud_send(MAVLINK_COMM_0, airspeed.true_airspeed_m_s, groundspeed, heading, throttle, global_pos.alt, -global_pos.vz);
}
/* send quaternion values if it exists */
if(att.q_valid) {
mavlink_msg_attitude_quaternion_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
att.q[0],
att.q[1],
att.q[2],
att.q[3],
att.rollspeed,
att.pitchspeed,
att.yawspeed);
}
}
attitude_counter++;
@@ -266,13 +277,7 @@ l_vehicle_gps_position(const struct listener *l)
orb_copy(ORB_ID(vehicle_gps_position), mavlink_subs.gps_sub, &gps);
/* GPS COG is 0..2PI in degrees * 1e2 */
float cog_deg = gps.cog_rad;
if (cog_deg > M_PI_F)
cog_deg -= 2.0f * M_PI_F;
cog_deg *= M_RAD_TO_DEG_F;
float cog_deg = _wrap_2pi(gps.cog_rad) * M_RAD_TO_DEG_F;
/* GPS position */
mavlink_msg_gps_raw_int_send(MAVLINK_COMM_0,
@@ -365,28 +370,16 @@ l_global_position(const struct listener *l)
/* copy global position data into local buffer */
orb_copy(ORB_ID(vehicle_global_position), mavlink_subs.global_pos_sub, &global_pos);
uint64_t timestamp = global_pos.timestamp;
int32_t lat = global_pos.lat;
int32_t lon = global_pos.lon;
int32_t alt = (int32_t)(global_pos.alt * 1000);
int32_t relative_alt = (int32_t)(global_pos.relative_alt * 1000.0f);
int16_t vx = (int16_t)(global_pos.vx * 100.0f);
int16_t vy = (int16_t)(global_pos.vy * 100.0f);
int16_t vz = (int16_t)(global_pos.vz * 100.0f);
/* heading in degrees * 10, from 0 to 36.000) */
uint16_t hdg = (global_pos.yaw / M_PI_F) * (180.0f * 10.0f) + (180.0f * 10.0f);
mavlink_msg_global_position_int_send(MAVLINK_COMM_0,
timestamp / 1000,
lat,
lon,
alt,
relative_alt,
vx,
vy,
vz,
hdg);
global_pos.timestamp / 1000,
global_pos.lat,
global_pos.lon,
global_pos.alt * 1000.0f,
global_pos.relative_alt * 1000.0f,
global_pos.vx * 100.0f,
global_pos.vy * 100.0f,
global_pos.vz * 100.0f,
_wrap_2pi(global_pos.yaw) * M_RAD_TO_DEG_F * 100.0f);
}
void
@@ -424,8 +417,8 @@ l_global_position_setpoint(const struct listener *l)
coordinate_frame,
global_sp.lat,
global_sp.lon,
global_sp.altitude,
global_sp.yaw);
global_sp.altitude * 1000.0f,
global_sp.yaw * M_RAD_TO_DEG_F * 100.0f);
}
void
@@ -603,32 +596,6 @@ l_manual_control_setpoint(const struct listener *l)
0);
}
void
l_vehicle_attitude_controls_effective(const struct listener *l)
{
orb_copy(ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE, mavlink_subs.actuators_effective_sub, &actuators_effective_0);
if (gcs_link) {
/* send, add spaces so that string buffer is at least 10 chars long */
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"eff ctrl0 ",
actuators_effective_0.control_effective[0]);
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"eff ctrl1 ",
actuators_effective_0.control_effective[1]);
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"eff ctrl2 ",
actuators_effective_0.control_effective[2]);
mavlink_msg_named_value_float_send(MAVLINK_COMM_0,
last_sensor_timestamp / 1000,
"eff ctrl3 ",
actuators_effective_0.control_effective[3]);
}
}
void
l_vehicle_attitude_controls(const struct listener *l)
{
@@ -839,9 +806,6 @@ uorb_receive_start(void)
orb_set_interval(mavlink_subs.man_control_sp_sub, 100); /* 10Hz updates */
/* --- ACTUATOR CONTROL VALUE --- */
mavlink_subs.actuators_effective_sub = orb_subscribe(ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE);
orb_set_interval(mavlink_subs.actuators_effective_sub, 100); /* 10Hz updates */
mavlink_subs.actuators_sub = orb_subscribe(ORB_ID_VEHICLE_ATTITUDE_CONTROLS);
orb_set_interval(mavlink_subs.actuators_sub, 100); /* 10Hz updates */
src/modules/position_estimator_inav/position_estimator_inav_main.c
+5 -6
View File
@@ -236,13 +236,13 @@ int position_estimator_inav_thread_main(int argc, char *argv[])
if (ret < 0) {
/* poll error */
errx(1, "subscriptions poll error on init.");
mavlink_log_info(mavlink_fd, "[inav] poll error on init");
} else if (ret > 0) {
if (fds_init[0].revents & POLLIN) {
orb_copy(ORB_ID(sensor_combined), sensor_combined_sub, &sensor);
if (wait_baro && sensor.baro_counter > baro_counter) {
if (wait_baro && sensor.baro_counter != baro_counter) {
baro_counter = sensor.baro_counter;
/* mean calculation over several measurements */
@@ -320,8 +320,7 @@ int position_estimator_inav_thread_main(int argc, char *argv[])
if (ret < 0) {
/* poll error */
warnx("subscriptions poll error.");
thread_should_exit = true;
mavlink_log_info(mavlink_fd, "[inav] poll error on init");
continue;
} else if (ret > 0) {
@@ -355,7 +354,7 @@ int position_estimator_inav_thread_main(int argc, char *argv[])
if (fds[4].revents & POLLIN) {
orb_copy(ORB_ID(sensor_combined), sensor_combined_sub, &sensor);
if (sensor.accelerometer_counter > accel_counter) {
if (sensor.accelerometer_counter != accel_counter) {
if (att.R_valid) {
/* correct accel bias, now only for Z */
sensor.accelerometer_m_s2[2] -= accel_bias[2];
@@ -381,7 +380,7 @@ int position_estimator_inav_thread_main(int argc, char *argv[])
accel_updates++;
}
if (sensor.baro_counter > baro_counter) {
if (sensor.baro_counter != baro_counter) {
baro_corr = - sensor.baro_alt_meter - z_est[0];
baro_counter = sensor.baro_counter;
baro_updates++;
src/modules/px4iofirmware/mixer.cpp
+5 -1
View File
@@ -195,7 +195,7 @@ mixer_tick(void)
r_page_servos[i] = r_page_servo_failsafe[i];
/* safe actuators for FMU feedback */
r_page_actuators[i] = (r_page_servos[i] - 1500) / 600.0f;
r_page_actuators[i] = FLOAT_TO_REG((r_page_servos[i] - 1500) / 600.0f);
}
@@ -211,6 +211,10 @@ mixer_tick(void)
for (unsigned i = mixed; i < PX4IO_SERVO_COUNT; i++)
r_page_servos[i] = 0;
for (unsigned i = 0; i < PX4IO_SERVO_COUNT; i++) {
r_page_actuators[i] = FLOAT_TO_REG(outputs[i]);
}
}
if ((should_arm || should_always_enable_pwm) && !mixer_servos_armed) {
src/modules/px4iofirmware/protocol.h
+5
View File
@@ -190,6 +190,11 @@ enum { /* DSM bind states */
/* 8 */
#define PX4IO_P_SETUP_SET_DEBUG 9 /* debug level for IO board */
#define PX4IO_P_SETUP_REBOOT_BL 10 /* reboot IO into bootloader */
#define PX4IO_REBOOT_BL_MAGIC 14662 /* required argument for reboot (random) */
#define PX4IO_P_SETUP_CRC 11 /* get CRC of IO firmware */
/* autopilot control values, -10000..10000 */
#define PX4IO_PAGE_CONTROLS 51 /**< actuator control groups, one after the other, 8 wide */
#define PX4IO_P_CONTROLS_GROUP_0 (PX4IO_PROTOCOL_MAX_CONTROL_COUNT * 0) /**< 0..PX4IO_PROTOCOL_MAX_CONTROL_COUNT - 1 */
src/modules/px4iofirmware/px4io.c
+20
View File
@@ -45,6 +45,7 @@
#include <string.h>
#include <poll.h>
#include <signal.h>
#include <crc32.h>
#include <drivers/drv_pwm_output.h>
#include <drivers/drv_hrt.h>
@@ -124,6 +125,22 @@ heartbeat_blink(void)
LED_BLUE(heartbeat = !heartbeat);
}
static void
calculate_fw_crc(void)
{
#define APP_SIZE_MAX 0xf000
#define APP_LOAD_ADDRESS 0x08001000
// compute CRC of the current firmware
uint32_t sum = 0;
for (unsigned p = 0; p < APP_SIZE_MAX; p += 4) {
uint32_t bytes = *(uint32_t *)(p + APP_LOAD_ADDRESS);
sum = crc32part((uint8_t *)&bytes, sizeof(bytes), sum);
}
r_page_setup[PX4IO_P_SETUP_CRC] = sum & 0xFFFF;
r_page_setup[PX4IO_P_SETUP_CRC+1] = sum >> 16;
}
int
user_start(int argc, char *argv[])
{
@@ -136,6 +153,9 @@ user_start(int argc, char *argv[])
/* configure the high-resolution time/callout interface */
hrt_init();
/* calculate our fw CRC so FMU can decide if we need to update */
calculate_fw_crc();
/*
* Poll at 1ms intervals for received bytes that have not triggered
* a DMA event.
src/modules/px4iofirmware/registers.c
+27
View File
@@ -45,6 +45,8 @@
#include <drivers/drv_hrt.h>
#include <drivers/drv_pwm_output.h>
#include <systemlib/systemlib.h>
#include <stm32_pwr.h>
#include "px4io.h"
#include "protocol.h"
@@ -154,6 +156,8 @@ volatile uint16_t r_page_setup[] =
[PX4IO_P_SETUP_VBATT_SCALE] = 10000,
#endif
[PX4IO_P_SETUP_SET_DEBUG] = 0,
[PX4IO_P_SETUP_REBOOT_BL] = 0,
[PX4IO_P_SETUP_CRC ... (PX4IO_P_SETUP_CRC+1)] = 0,
};
#define PX4IO_P_SETUP_FEATURES_VALID (0)
@@ -501,6 +505,29 @@ registers_set_one(uint8_t page, uint8_t offset, uint16_t value)
isr_debug(0, "set debug %u\n", (unsigned)r_page_setup[PX4IO_P_SETUP_SET_DEBUG]);
break;
case PX4IO_P_SETUP_REBOOT_BL:
if ((r_status_flags & PX4IO_P_STATUS_FLAGS_SAFETY_OFF) ||
(r_status_flags & PX4IO_P_STATUS_FLAGS_OVERRIDE) ||
(r_setup_arming & PX4IO_P_SETUP_ARMING_FMU_ARMED)) {
// don't allow reboot while armed
break;
}
// check the magic value
if (value != PX4IO_REBOOT_BL_MAGIC)
break;
// note that we don't set BL_WAIT_MAGIC in
// BKP_DR1 as that is not necessary given the
// timing of the forceupdate command. The
// bootloader on px4io waits for enough time
// anyway, and this method works with older
// bootloader versions (tested with both
// revision 3 and revision 4).
up_systemreset();
break;
case PX4IO_P_SETUP_DSM:
dsm_bind(value & 0x0f, (value >> 4) & 7);
break;
src/modules/sdlog2/sdlog2.c
+3 -18
View File
@@ -68,7 +68,6 @@
#include <uORB/topics/vehicle_rates_setpoint.h>
#include <uORB/topics/actuator_outputs.h>
#include <uORB/topics/actuator_controls.h>
#include <uORB/topics/actuator_controls_effective.h>
#include <uORB/topics/vehicle_command.h>
#include <uORB/topics/vehicle_local_position.h>
#include <uORB/topics/vehicle_local_position_setpoint.h>
@@ -691,7 +690,6 @@ int sdlog2_thread_main(int argc, char *argv[])
struct vehicle_rates_setpoint_s rates_sp;
struct actuator_outputs_s act_outputs;
struct actuator_controls_s act_controls;
struct actuator_controls_effective_s act_controls_effective;
struct vehicle_local_position_s local_pos;
struct vehicle_local_position_setpoint_s local_pos_sp;
struct vehicle_global_position_s global_pos;
@@ -717,7 +715,6 @@ int sdlog2_thread_main(int argc, char *argv[])
int rates_sp_sub;
int act_outputs_sub;
int act_controls_sub;
int act_controls_effective_sub;
int local_pos_sub;
int local_pos_sp_sub;
int global_pos_sub;
@@ -763,9 +760,9 @@ int sdlog2_thread_main(int argc, char *argv[])
memset(&log_msg.body, 0, sizeof(log_msg.body));
/* --- IMPORTANT: DEFINE NUMBER OF ORB STRUCTS TO WAIT FOR HERE --- */
/* number of messages */
const ssize_t fdsc = 20;
/* Sanity check variable and index */
/* number of subscriptions */
const ssize_t fdsc = 19;
/* sanity check variable and index */
ssize_t fdsc_count = 0;
/* file descriptors to wait for */
struct pollfd fds[fdsc];
@@ -824,12 +821,6 @@ int sdlog2_thread_main(int argc, char *argv[])
fds[fdsc_count].events = POLLIN;
fdsc_count++;
/* --- ACTUATOR CONTROL EFFECTIVE --- */
subs.act_controls_effective_sub = orb_subscribe(ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE);
fds[fdsc_count].fd = subs.act_controls_effective_sub;
fds[fdsc_count].events = POLLIN;
fdsc_count++;
/* --- LOCAL POSITION --- */
subs.local_pos_sub = orb_subscribe(ORB_ID(vehicle_local_position));
fds[fdsc_count].fd = subs.local_pos_sub;
@@ -1114,12 +1105,6 @@ int sdlog2_thread_main(int argc, char *argv[])
LOGBUFFER_WRITE_AND_COUNT(ATTC);
}
/* --- ACTUATOR CONTROL EFFECTIVE --- */
if (fds[ifds++].revents & POLLIN) {
orb_copy(ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE, subs.act_controls_effective_sub, &buf.act_controls_effective);
// TODO not implemented yet
}
/* --- LOCAL POSITION --- */
if (fds[ifds++].revents & POLLIN) {
orb_copy(ORB_ID(vehicle_local_position), subs.local_pos_sub, &buf.local_pos);
src/modules/uORB/objects_common.cpp
-7
View File
@@ -176,13 +176,6 @@ ORB_DEFINE(actuator_controls_3, struct actuator_controls_s);
#include "topics/actuator_armed.h"
ORB_DEFINE(actuator_armed, struct actuator_armed_s);
/* actuator controls, as set by actuators / mixers after limiting */
#include "topics/actuator_controls_effective.h"
ORB_DEFINE(actuator_controls_effective_0, struct actuator_controls_effective_s);
ORB_DEFINE(actuator_controls_effective_1, struct actuator_controls_effective_s);
ORB_DEFINE(actuator_controls_effective_2, struct actuator_controls_effective_s);
ORB_DEFINE(actuator_controls_effective_3, struct actuator_controls_effective_s);
#include "topics/actuator_outputs.h"
ORB_DEFINE(actuator_outputs_0, struct actuator_outputs_s);
ORB_DEFINE(actuator_outputs_1, struct actuator_outputs_s);
src/modules/uORB/topics/actuator_controls_effective.h
+30 -30
View File
@@ -46,34 +46,34 @@
#ifndef TOPIC_ACTUATOR_CONTROLS_EFFECTIVE_H
#define TOPIC_ACTUATOR_CONTROLS_EFFECTIVE_H
#include <stdint.h>
#include "../uORB.h"
#include "actuator_controls.h"
//#include <stdint.h>
//#include "../uORB.h"
//#include "actuator_controls.h"
//
//#define NUM_ACTUATOR_CONTROLS_EFFECTIVE NUM_ACTUATOR_CONTROLS
//#define NUM_ACTUATOR_CONTROL_GROUPS_EFFECTIVE NUM_ACTUATOR_CONTROL_GROUPS /**< for sanity checking */
//
///**
// * @addtogroup topics
// * @{
// */
//
//struct actuator_controls_effective_s {
// uint64_t timestamp;
// float control_effective[NUM_ACTUATOR_CONTROLS_EFFECTIVE];
//};
//
///**
// * @}
// */
//
///* actuator control sets; this list can be expanded as more controllers emerge */
//ORB_DECLARE(actuator_controls_effective_0);
//ORB_DECLARE(actuator_controls_effective_1);
//ORB_DECLARE(actuator_controls_effective_2);
//ORB_DECLARE(actuator_controls_effective_3);
//
///* control sets with pre-defined applications */
//#define ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE ORB_ID(actuator_controls_effective_0)
#define NUM_ACTUATOR_CONTROLS_EFFECTIVE NUM_ACTUATOR_CONTROLS
#define NUM_ACTUATOR_CONTROL_GROUPS_EFFECTIVE NUM_ACTUATOR_CONTROL_GROUPS /**< for sanity checking */
/**
* @addtogroup topics
* @{
*/
struct actuator_controls_effective_s {
uint64_t timestamp;
float control_effective[NUM_ACTUATOR_CONTROLS_EFFECTIVE];
};
/**
* @}
*/
/* actuator control sets; this list can be expanded as more controllers emerge */
ORB_DECLARE(actuator_controls_effective_0);
ORB_DECLARE(actuator_controls_effective_1);
ORB_DECLARE(actuator_controls_effective_2);
ORB_DECLARE(actuator_controls_effective_3);
/* control sets with pre-defined applications */
#define ORB_ID_VEHICLE_ATTITUDE_CONTROLS_EFFECTIVE ORB_ID(actuator_controls_effective_0)
#endif /* TOPIC_ACTUATOR_CONTROLS_EFFECTIVE_H */
#endif /* TOPIC_ACTUATOR_CONTROLS_EFFECTIVE_H */