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632 lines
19 KiB
C
632 lines
19 KiB
C
/**
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******************************************************************************
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* @addtogroup OpenPilotModules OpenPilot Modules
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* @{
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* @addtogroup Attitude Copter Control Attitude Estimation
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* @brief Acquires sensor data and computes attitude estimate
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* Specifically updates the the @ref AttitudeActual "AttitudeActual" and @ref AttitudeRaw "AttitudeRaw" settings objects
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* @{
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*
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* @file attitude.c
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* @author The OpenPilot Team, http://www.openpilot.org Copyright (C) 2010.
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* @brief Module to handle all comms to the AHRS on a periodic basis.
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*
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* @see The GNU Public License (GPL) Version 3
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*
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******************************************************************************/
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/*
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* This program is free software; you can redistribute it and/or modify
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* it under the terms of the GNU General Public License as published by
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* the Free Software Foundation; either version 3 of the License, or
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* (at your option) any later version.
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*
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* This program is distributed in the hope that it will be useful, but
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* WITHOUT ANY WARRANTY; without even the implied warranty of MERCHANTABILITY
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* or FITNESS FOR A PARTICULAR PURPOSE. See the GNU General Public License
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* for more details.
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*
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* You should have received a copy of the GNU General Public License along
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* with this program; if not, write to the Free Software Foundation, Inc.,
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* 59 Temple Place, Suite 330, Boston, MA 02111-1307 USA
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*/
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/**
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* Input objects: None, takes sensor data via pios
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* Output objects: @ref AttitudeRaw @ref AttitudeActual
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*
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* This module computes an attitude estimate from the sensor data
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*
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* The module executes in its own thread.
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*
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* UAVObjects are automatically generated by the UAVObjectGenerator from
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* the object definition XML file.
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*
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* Modules have no API, all communication to other modules is done through UAVObjects.
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* However modules may use the API exposed by shared libraries.
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* See the OpenPilot wiki for more details.
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* http://www.openpilot.org/OpenPilot_Application_Architecture
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*
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*/
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#include "pios.h"
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#include "attitude.h"
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#include "gyros.h"
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#include "accels.h"
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#include "attitudeactual.h"
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#include "attitudesettings.h"
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#include "flightstatus.h"
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#include "manualcontrolcommand.h"
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#include "CoordinateConversions.h"
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#include <pios_board_info.h>
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// Private constants
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#define STACK_SIZE_BYTES 540
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#define TASK_PRIORITY (tskIDLE_PRIORITY+3)
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#define SENSOR_PERIOD 4
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#define UPDATE_RATE 25.0f
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#define GYRO_NEUTRAL 1665
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#define PI_MOD(x) (fmod(x + M_PI, M_PI * 2) - M_PI)
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// Private types
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// Private variables
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static xTaskHandle taskHandle;
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// Private functions
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static void AttitudeTask(void *parameters);
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static float gyro_correct_int[3] = {0,0,0};
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static xQueueHandle gyro_queue;
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static int32_t updateSensors(AccelsData *, GyrosData *);
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static int32_t updateSensorsCC3D(AccelsData * accelsData, GyrosData * gyrosData);
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static void updateAttitude(AccelsData *, GyrosData *);
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static void settingsUpdatedCb(UAVObjEvent * objEv);
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static float accelKi = 0;
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static float accelKp = 0;
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static float accel_alpha = 0;
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static bool accel_filter_enabled = false;
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static float accels_filtered[3];
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static float grot_filtered[3];
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static float yawBiasRate = 0;
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static float gyroGain = 0.42;
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static int16_t accelbias[3];
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static float q[4] = {1,0,0,0};
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static float R[3][3];
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static int8_t rotate = 0;
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static bool zero_during_arming = false;
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static bool bias_correct_gyro = true;
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// For running trim flights
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static volatile bool trim_requested = false;
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static volatile int32_t trim_accels[3];
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static volatile int32_t trim_samples;
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int32_t const MAX_TRIM_FLIGHT_SAMPLES = 65535;
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#define GRAV 9.81f
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#define ACCEL_SCALE (GRAV * 0.004f)
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/* 0.004f is gravity / LSB */
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/**
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* Initialise the module, called on startup
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* \returns 0 on success or -1 if initialisation failed
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*/
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int32_t AttitudeStart(void)
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{
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// Start main task
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xTaskCreate(AttitudeTask, (signed char *)"Attitude", STACK_SIZE_BYTES/4, NULL, TASK_PRIORITY, &taskHandle);
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TaskMonitorAdd(TASKINFO_RUNNING_ATTITUDE, taskHandle);
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PIOS_WDG_RegisterFlag(PIOS_WDG_ATTITUDE);
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return 0;
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}
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/**
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* Initialise the module, called on startup
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* \returns 0 on success or -1 if initialisation failed
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*/
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int32_t AttitudeInitialize(void)
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{
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AttitudeActualInitialize();
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AttitudeSettingsInitialize();
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AccelsInitialize();
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GyrosInitialize();
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// Initialize quaternion
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AttitudeActualData attitude;
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AttitudeActualGet(&attitude);
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attitude.q1 = 1;
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attitude.q2 = 0;
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attitude.q3 = 0;
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attitude.q4 = 0;
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AttitudeActualSet(&attitude);
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// Cannot trust the values to init right above if BL runs
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gyro_correct_int[0] = 0;
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gyro_correct_int[1] = 0;
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gyro_correct_int[2] = 0;
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q[0] = 1;
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q[1] = 0;
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q[2] = 0;
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q[3] = 0;
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for(uint8_t i = 0; i < 3; i++)
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for(uint8_t j = 0; j < 3; j++)
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R[i][j] = 0;
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trim_requested = false;
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AttitudeSettingsConnectCallback(&settingsUpdatedCb);
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return 0;
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}
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MODULE_INITCALL(AttitudeInitialize, AttitudeStart)
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/**
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* Module thread, should not return.
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*/
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int32_t accel_test;
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int32_t gyro_test;
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static void AttitudeTask(void *parameters)
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{
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uint8_t init = 0;
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AlarmsClear(SYSTEMALARMS_ALARM_ATTITUDE);
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// Set critical error and wait until the accel is producing data
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while(PIOS_ADXL345_FifoElements() == 0) {
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AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE, SYSTEMALARMS_ALARM_CRITICAL);
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PIOS_WDG_UpdateFlag(PIOS_WDG_ATTITUDE);
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}
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const struct pios_board_info * bdinfo = &pios_board_info_blob;
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bool cc3d = bdinfo->board_rev == 0x02;
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if(cc3d) {
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#if defined(PIOS_INCLUDE_MPU6000)
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gyro_test = PIOS_MPU6000_Test();
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#endif
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} else {
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#if defined(PIOS_INCLUDE_ADXL345)
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accel_test = PIOS_ADXL345_Test();
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#endif
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#if defined(PIOS_INCLUDE_ADC)
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// Create queue for passing gyro data, allow 2 back samples in case
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gyro_queue = xQueueCreate(1, sizeof(float) * 4);
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PIOS_Assert(gyro_queue != NULL);
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PIOS_ADC_SetQueue(gyro_queue);
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PIOS_ADC_Config((PIOS_ADC_RATE / 1000.0f) * UPDATE_RATE);
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#endif
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}
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// Force settings update to make sure rotation loaded
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settingsUpdatedCb(AttitudeSettingsHandle());
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// Main task loop
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while (1) {
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FlightStatusData flightStatus;
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FlightStatusGet(&flightStatus);
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if((xTaskGetTickCount() < 7000) && (xTaskGetTickCount() > 1000)) {
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// For first 7 seconds use accels to get gyro bias
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accelKp = 1;
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accelKi = 0.9;
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yawBiasRate = 0.23;
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accel_filter_enabled = false;
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init = 0;
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}
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else if (zero_during_arming && (flightStatus.Armed == FLIGHTSTATUS_ARMED_ARMING)) {
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accelKp = 1;
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accelKi = 0.9;
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yawBiasRate = 0.23;
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accel_filter_enabled = false;
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init = 0;
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} else if (init == 0) {
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// Reload settings (all the rates)
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AttitudeSettingsAccelKiGet(&accelKi);
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AttitudeSettingsAccelKpGet(&accelKp);
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AttitudeSettingsYawBiasRateGet(&yawBiasRate);
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if (accel_alpha > 0.0f)
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accel_filter_enabled = true;
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init = 1;
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}
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PIOS_WDG_UpdateFlag(PIOS_WDG_ATTITUDE);
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AccelsData accels;
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GyrosData gyros;
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int32_t retval = 0;
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if (cc3d)
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retval = updateSensorsCC3D(&accels, &gyros);
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else
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retval = updateSensors(&accels, &gyros);
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// Only update attitude when sensor data is good
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if (retval != 0)
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AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE, SYSTEMALARMS_ALARM_ERROR);
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else {
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// Do not update attitude data in simulation mode
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if (!AttitudeActualReadOnly())
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updateAttitude(&accels, &gyros);
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AlarmsClear(SYSTEMALARMS_ALARM_ATTITUDE);
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}
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}
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}
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float gyros_passed[3];
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/**
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* Get an update from the sensors
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* @param[in] attitudeRaw Populate the UAVO instead of saving right here
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* @return 0 if successfull, -1 if not
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*/
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static int32_t updateSensors(AccelsData * accels, GyrosData * gyros)
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{
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struct pios_adxl345_data accel_data;
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float gyro[4];
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// Only wait the time for two nominal updates before setting an alarm
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if(xQueueReceive(gyro_queue, (void * const) gyro, UPDATE_RATE * 2) == errQUEUE_EMPTY) {
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AlarmsSet(SYSTEMALARMS_ALARM_ATTITUDE, SYSTEMALARMS_ALARM_ERROR);
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return -1;
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}
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// Do not read raw sensor data in simulation mode
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if (GyrosReadOnly() || AccelsReadOnly())
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return 0;
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// No accel data available
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if(PIOS_ADXL345_FifoElements() == 0)
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return -1;
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// First sample is temperature
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gyros->x = -(gyro[1] - GYRO_NEUTRAL) * gyroGain;
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gyros->y = (gyro[2] - GYRO_NEUTRAL) * gyroGain;
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gyros->z = -(gyro[3] - GYRO_NEUTRAL) * gyroGain;
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int32_t x = 0;
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int32_t y = 0;
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int32_t z = 0;
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uint8_t i = 0;
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uint8_t samples_remaining;
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do {
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i++;
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samples_remaining = PIOS_ADXL345_Read(&accel_data);
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x += accel_data.x;
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y += -accel_data.y;
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z += -accel_data.z;
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} while ( (i < 32) && (samples_remaining > 0) );
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gyros->temperature = samples_remaining;
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float accel[3] = {(float) x / i, (float) y / i, (float) z / i};
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if(rotate) {
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// TODO: rotate sensors too so stabilization is well behaved
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float vec_out[3];
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rot_mult(R, accel, vec_out);
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accels->x = vec_out[0];
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accels->y = vec_out[1];
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accels->z = vec_out[2];
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rot_mult(R, &gyros->x, vec_out);
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gyros->x = vec_out[0];
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gyros->y = vec_out[1];
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gyros->z = vec_out[2];
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} else {
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accels->x = accel[0];
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accels->y = accel[1];
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accels->z = accel[2];
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}
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if (trim_requested) {
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if (trim_samples >= MAX_TRIM_FLIGHT_SAMPLES) {
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trim_requested = false;
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} else {
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uint8_t armed;
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float throttle;
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FlightStatusArmedGet(&armed);
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ManualControlCommandThrottleGet(&throttle); // Until flight status indicates airborne
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if ((armed == FLIGHTSTATUS_ARMED_ARMED) && (throttle > 0)) {
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trim_samples++;
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// Store the digitally scaled version since that is what we use for bias
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trim_accels[0] += accels->x;
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trim_accels[1] += accels->y;
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trim_accels[2] += accels->z;
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}
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}
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}
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// Scale accels and correct bias
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accels->x = (accels->x - accelbias[0]) * ACCEL_SCALE;
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accels->y = (accels->y - accelbias[1]) * ACCEL_SCALE;
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accels->z = (accels->z - accelbias[2]) * ACCEL_SCALE;
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if(bias_correct_gyro) {
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// Applying integral component here so it can be seen on the gyros and correct bias
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gyros->x += gyro_correct_int[0];
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gyros->y += gyro_correct_int[1];
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gyros->z += gyro_correct_int[2];
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}
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// Because most crafts wont get enough information from gravity to zero yaw gyro, we try
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// and make it average zero (weakly)
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gyro_correct_int[2] += - gyros->z * yawBiasRate;
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GyrosSet(gyros);
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AccelsSet(accels);
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return 0;
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}
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/**
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* Get an update from the sensors
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* @param[in] attitudeRaw Populate the UAVO instead of saving right here
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* @return 0 if successfull, -1 if not
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*/
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struct pios_mpu6000_data mpu6000_data;
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static int32_t updateSensorsCC3D(AccelsData * accelsData, GyrosData * gyrosData)
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{
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float accels[3], gyros[3];
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#if defined(PIOS_INCLUDE_MPU6000)
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xQueueHandle queue = PIOS_MPU6000_GetQueue();
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if(xQueueReceive(queue, (void *) &mpu6000_data, SENSOR_PERIOD) == errQUEUE_EMPTY)
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return -1; // Error, no data
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// Do not read raw sensor data in simulation mode
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if (GyrosReadOnly() || AccelsReadOnly())
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return 0;
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gyros[0] = -mpu6000_data.gyro_y * PIOS_MPU6000_GetScale();
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gyros[1] = -mpu6000_data.gyro_x * PIOS_MPU6000_GetScale();
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gyros[2] = -mpu6000_data.gyro_z * PIOS_MPU6000_GetScale();
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accels[0] = -mpu6000_data.accel_y * PIOS_MPU6000_GetAccelScale();
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accels[1] = -mpu6000_data.accel_x * PIOS_MPU6000_GetAccelScale();
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accels[2] = -mpu6000_data.accel_z * PIOS_MPU6000_GetAccelScale();
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gyrosData->temperature = 35.0f + ((float) mpu6000_data.temperature + 512.0f) / 340.0f;
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accelsData->temperature = 35.0f + ((float) mpu6000_data.temperature + 512.0f) / 340.0f;
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#endif
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if(rotate) {
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// TODO: rotate sensors too so stabilization is well behaved
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float vec_out[3];
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rot_mult(R, accels, vec_out);
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accels[0] = vec_out[0];
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accels[1] = vec_out[1];
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accels[2] = vec_out[2];
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rot_mult(R, gyros, vec_out);
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gyros[0] = vec_out[0];
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gyros[1] = vec_out[1];
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gyros[2] = vec_out[2];
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}
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accelsData->x = accels[0] - accelbias[0] * ACCEL_SCALE; // Applying arbitrary scale here to match CC v1
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accelsData->y = accels[1] - accelbias[1] * ACCEL_SCALE;
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accelsData->z = accels[2] - accelbias[2] * ACCEL_SCALE;
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gyrosData->x = gyros[0];
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gyrosData->y = gyros[1];
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gyrosData->z = gyros[2];
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if(bias_correct_gyro) {
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// Applying integral component here so it can be seen on the gyros and correct bias
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gyrosData->x += gyro_correct_int[0];
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gyrosData->y += gyro_correct_int[1];
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gyrosData->z += gyro_correct_int[2];
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}
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// Because most crafts wont get enough information from gravity to zero yaw gyro, we try
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// and make it average zero (weakly)
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gyro_correct_int[2] += - gyrosData->z * yawBiasRate;
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GyrosSet(gyrosData);
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AccelsSet(accelsData);
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return 0;
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}
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static inline void apply_accel_filter(const float *raw, float *filtered)
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{
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if (accel_filter_enabled) {
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filtered[0] = filtered[0] * accel_alpha + raw[0] * (1 - accel_alpha);
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filtered[1] = filtered[1] * accel_alpha + raw[1] * (1 - accel_alpha);
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filtered[2] = filtered[2] * accel_alpha + raw[2] * (1 - accel_alpha);
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} else {
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filtered[0] = raw[0];
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filtered[1] = raw[1];
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filtered[2] = raw[2];
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}
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}
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static void updateAttitude(AccelsData * accelsData, GyrosData * gyrosData)
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{
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float dT;
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portTickType thisSysTime = xTaskGetTickCount();
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static portTickType lastSysTime = 0;
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dT = (thisSysTime == lastSysTime) ? 0.001 : (portMAX_DELAY & (thisSysTime - lastSysTime)) / portTICK_RATE_MS / 1000.0f;
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lastSysTime = thisSysTime;
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// Bad practice to assume structure order, but saves memory
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float * gyros = &gyrosData->x;
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float * accels = &accelsData->x;
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float grot[3];
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float accel_err[3];
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// Apply smoothing to accel values, to reduce vibration noise before main calculations.
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apply_accel_filter(accels, accels_filtered);
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// Rotate gravity unit vector to body frame, filter and cross with accels
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grot[0] = -(2 * (q[1] * q[3] - q[0] * q[2]));
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grot[1] = -(2 * (q[2] * q[3] + q[0] * q[1]));
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grot[2] = -(q[0] * q[0] - q[1]*q[1] - q[2]*q[2] + q[3]*q[3]);
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apply_accel_filter(grot, grot_filtered);
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CrossProduct((const float *)accels_filtered, (const float *)grot_filtered, accel_err);
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// Account for accel magnitude
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float accel_mag = sqrtf(accels_filtered[0]*accels_filtered[0] + accels_filtered[1]*accels_filtered[1] + accels_filtered[2]*accels_filtered[2]);
|
|
if (accel_mag < 1.0e-3f)
|
|
return;
|
|
|
|
// Account for filtered gravity vector magnitude
|
|
float grot_mag;
|
|
|
|
if (accel_filter_enabled)
|
|
grot_mag = sqrtf(grot_filtered[0]*grot_filtered[0] + grot_filtered[1]*grot_filtered[1] + grot_filtered[2]*grot_filtered[2]);
|
|
else
|
|
grot_mag = 1.0f;
|
|
|
|
if (grot_mag < 1.0e-3f)
|
|
return;
|
|
|
|
accel_err[0] /= (accel_mag*grot_mag);
|
|
accel_err[1] /= (accel_mag*grot_mag);
|
|
accel_err[2] /= (accel_mag*grot_mag);
|
|
|
|
// Accumulate integral of error. Scale here so that units are (deg/s) but Ki has units of s
|
|
gyro_correct_int[0] += accel_err[0] * accelKi;
|
|
gyro_correct_int[1] += accel_err[1] * accelKi;
|
|
|
|
//gyro_correct_int[2] += accel_err[2] * accelKi;
|
|
|
|
// Correct rates based on error, integral component dealt with in updateSensors
|
|
gyros[0] += accel_err[0] * accelKp / dT;
|
|
gyros[1] += accel_err[1] * accelKp / dT;
|
|
gyros[2] += accel_err[2] * accelKp / dT;
|
|
|
|
{ // scoping variables to save memory
|
|
// Work out time derivative from INSAlgo writeup
|
|
// Also accounts for the fact that gyros are in deg/s
|
|
float qdot[4];
|
|
qdot[0] = (-q[1] * gyros[0] - q[2] * gyros[1] - q[3] * gyros[2]) * dT * M_PI / 180 / 2;
|
|
qdot[1] = (q[0] * gyros[0] - q[3] * gyros[1] + q[2] * gyros[2]) * dT * M_PI / 180 / 2;
|
|
qdot[2] = (q[3] * gyros[0] + q[0] * gyros[1] - q[1] * gyros[2]) * dT * M_PI / 180 / 2;
|
|
qdot[3] = (-q[2] * gyros[0] + q[1] * gyros[1] + q[0] * gyros[2]) * dT * M_PI / 180 / 2;
|
|
|
|
// Take a time step
|
|
q[0] = q[0] + qdot[0];
|
|
q[1] = q[1] + qdot[1];
|
|
q[2] = q[2] + qdot[2];
|
|
q[3] = q[3] + qdot[3];
|
|
|
|
if(q[0] < 0) {
|
|
q[0] = -q[0];
|
|
q[1] = -q[1];
|
|
q[2] = -q[2];
|
|
q[3] = -q[3];
|
|
}
|
|
}
|
|
|
|
// Renomalize
|
|
float qmag = sqrtf(q[0]*q[0] + q[1]*q[1] + q[2]*q[2] + q[3]*q[3]);
|
|
q[0] = q[0] / qmag;
|
|
q[1] = q[1] / qmag;
|
|
q[2] = q[2] / qmag;
|
|
q[3] = q[3] / qmag;
|
|
|
|
// If quaternion has become inappropriately short or is nan reinit.
|
|
// THIS SHOULD NEVER ACTUALLY HAPPEN
|
|
if((fabs(qmag) < 1e-3) || (qmag != qmag)) {
|
|
q[0] = 1;
|
|
q[1] = 0;
|
|
q[2] = 0;
|
|
q[3] = 0;
|
|
}
|
|
|
|
AttitudeActualData attitudeActual;
|
|
AttitudeActualGet(&attitudeActual);
|
|
|
|
quat_copy(q, &attitudeActual.q1);
|
|
|
|
// Convert into eueler degrees (makes assumptions about RPY order)
|
|
Quaternion2RPY(&attitudeActual.q1,&attitudeActual.Roll);
|
|
|
|
AttitudeActualSet(&attitudeActual);
|
|
}
|
|
|
|
static void settingsUpdatedCb(UAVObjEvent * objEv) {
|
|
AttitudeSettingsData attitudeSettings;
|
|
AttitudeSettingsGet(&attitudeSettings);
|
|
|
|
|
|
accelKp = attitudeSettings.AccelKp;
|
|
accelKi = attitudeSettings.AccelKi;
|
|
yawBiasRate = attitudeSettings.YawBiasRate;
|
|
gyroGain = attitudeSettings.GyroGain;
|
|
|
|
// Calculate accel filter alpha, in the same way as for gyro data in stabilization module.
|
|
const float fakeDt = 0.0025;
|
|
if (attitudeSettings.AccelTau < 0.0001) {
|
|
accel_alpha = 0; // not trusting this to resolve to 0
|
|
accel_filter_enabled = false;
|
|
} else {
|
|
accel_alpha = expf(-fakeDt / attitudeSettings.AccelTau);
|
|
accel_filter_enabled = true;
|
|
}
|
|
|
|
zero_during_arming = attitudeSettings.ZeroDuringArming == ATTITUDESETTINGS_ZERODURINGARMING_TRUE;
|
|
bias_correct_gyro = attitudeSettings.BiasCorrectGyro == ATTITUDESETTINGS_BIASCORRECTGYRO_TRUE;
|
|
|
|
accelbias[0] = attitudeSettings.AccelBias[ATTITUDESETTINGS_ACCELBIAS_X];
|
|
accelbias[1] = attitudeSettings.AccelBias[ATTITUDESETTINGS_ACCELBIAS_Y];
|
|
accelbias[2] = attitudeSettings.AccelBias[ATTITUDESETTINGS_ACCELBIAS_Z];
|
|
|
|
gyro_correct_int[0] = attitudeSettings.GyroBias[ATTITUDESETTINGS_GYROBIAS_X] / 100.0f;
|
|
gyro_correct_int[1] = attitudeSettings.GyroBias[ATTITUDESETTINGS_GYROBIAS_Y] / 100.0f;
|
|
gyro_correct_int[2] = attitudeSettings.GyroBias[ATTITUDESETTINGS_GYROBIAS_Z] / 100.0f;
|
|
|
|
// Indicates not to expend cycles on rotation
|
|
if(attitudeSettings.BoardRotation[0] == 0 && attitudeSettings.BoardRotation[1] == 0 &&
|
|
attitudeSettings.BoardRotation[2] == 0) {
|
|
rotate = 0;
|
|
|
|
// Shouldn't be used but to be safe
|
|
float rotationQuat[4] = {1,0,0,0};
|
|
Quaternion2R(rotationQuat, R);
|
|
} else {
|
|
float rotationQuat[4];
|
|
const float rpy[3] = {attitudeSettings.BoardRotation[ATTITUDESETTINGS_BOARDROTATION_ROLL],
|
|
attitudeSettings.BoardRotation[ATTITUDESETTINGS_BOARDROTATION_PITCH],
|
|
attitudeSettings.BoardRotation[ATTITUDESETTINGS_BOARDROTATION_YAW]};
|
|
RPY2Quaternion(rpy, rotationQuat);
|
|
Quaternion2R(rotationQuat, R);
|
|
rotate = 1;
|
|
}
|
|
|
|
if (attitudeSettings.TrimFlight == ATTITUDESETTINGS_TRIMFLIGHT_START) {
|
|
trim_accels[0] = 0;
|
|
trim_accels[1] = 0;
|
|
trim_accels[2] = 0;
|
|
trim_samples = 0;
|
|
trim_requested = true;
|
|
} else if (attitudeSettings.TrimFlight == ATTITUDESETTINGS_TRIMFLIGHT_LOAD) {
|
|
trim_requested = false;
|
|
attitudeSettings.AccelBias[ATTITUDESETTINGS_ACCELBIAS_X] = trim_accels[0] / trim_samples;
|
|
attitudeSettings.AccelBias[ATTITUDESETTINGS_ACCELBIAS_Y] = trim_accels[1] / trim_samples;
|
|
// Z should average -grav
|
|
attitudeSettings.AccelBias[ATTITUDESETTINGS_ACCELBIAS_Z] = trim_accels[2] / trim_samples + GRAV / ACCEL_SCALE;
|
|
attitudeSettings.TrimFlight = ATTITUDESETTINGS_TRIMFLIGHT_NORMAL;
|
|
AttitudeSettingsSet(&attitudeSettings);
|
|
} else
|
|
trim_requested = false;
|
|
}
|
|
/**
|
|
* @}
|
|
* @}
|
|
*/
|