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Diffstat (limited to 'src/modules/attitude_estimator_so3/attitude_estimator_so3_main.cpp')
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diff --git a/src/modules/attitude_estimator_so3/attitude_estimator_so3_main.cpp b/src/modules/attitude_estimator_so3/attitude_estimator_so3_main.cpp new file mode 100755 index 000000000..e79726613 --- /dev/null +++ b/src/modules/attitude_estimator_so3/attitude_estimator_so3_main.cpp @@ -0,0 +1,678 @@ +/**************************************************************************** + * + * 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 + */ + +#include <nuttx/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 task_create(). + */ +int attitude_estimator_so3_main(int argc, char *argv[]) +{ + if (argc < 1) + 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 = task_spawn_cmd("attitude_estimator_so3", + SCHED_DEFAULT, + SCHED_PRIORITY_MAX - 5, + 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){ + 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[]) +{ + 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}; + + /* 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 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; + + float sensor_update_hz[3] = {0.0f, 0.0f, 0.0f}; + // XXX write this out to perf regs + + /* keep track of sensor updates */ + uint32_t sensor_last_count[3] = {0, 0, 0}; + 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", gyro_offsets[0], gyro_offsets[1], 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; + uint8_t update_vect[3] = {0, 0, 0}; + + /* Fill in gyro measurements */ + if (sensor_last_count[0] != raw.gyro_counter) { + update_vect[0] = 1; + sensor_last_count[0] = raw.gyro_counter; + sensor_update_hz[0] = 1e6f / (raw.timestamp - sensor_last_timestamp[0]); + 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_count[1] != raw.accelerometer_counter) { + update_vect[1] = 1; + sensor_last_count[1] = raw.accelerometer_counter; + sensor_update_hz[1] = 1e6f / (raw.timestamp - sensor_last_timestamp[1]); + sensor_last_timestamp[1] = raw.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_count[2] != raw.magnetometer_counter) { + update_vect[2] = 1; + sensor_last_count[2] = raw.magnetometer_counter; + sensor_update_hz[2] = 1e6f / (raw.timestamp - sensor_last_timestamp[2]); + sensor_last_timestamp[2] = raw.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; + } + + uint64_t timing_start = hrt_absolute_time(); + + // 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", 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) { + 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 > 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); + } + } + } + + loopcounter++; + } + + thread_running = false; + + return 0; +} |