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https://bitbucket.org/librepilot/librepilot.git
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346 lines
9.2 KiB
C
346 lines
9.2 KiB
C
/**
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******************************************************************************
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* @addtogroup OpenPilotModules OpenPilot Modules
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* @{
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* @addtogroup StabilizationModule Stabilization Module
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* @brief Stabilization PID loops in an airframe type independent manner
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* @note This object updates the @ref ActuatorDesired "Actuator Desired" based on the
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* PID loops on the @ref AttitudeDesired "Attitude Desired" and @ref AttitudeActual "Attitude Actual"
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* @{
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*
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* @file stabilization.c
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* @author The OpenPilot Team, http://www.openpilot.org Copyright (C) 2010.
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* @brief Attitude stabilization module.
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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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#include "openpilot.h"
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#include "stabilization.h"
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#include "stabilizationsettings.h"
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#include "actuatordesired.h"
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#include "ratedesired.h"
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#include "stabilizationdesired.h"
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#include "attitudeactual.h"
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#include "attituderaw.h"
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#include "flightstatus.h"
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#include "systemsettings.h"
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#include "ahrssettings.h"
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#include "manualcontrol.h" // Just to get a macro
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#include "CoordinateConversions.h"
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// Private constants
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#define MAX_QUEUE_SIZE 1
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#if defined(PIOS_STABILIZATION_STACK_SIZE)
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#define STACK_SIZE_BYTES PIOS_STABILIZATION_STACK_SIZE
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#else
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#define STACK_SIZE_BYTES 724
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#endif
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#define TASK_PRIORITY (tskIDLE_PRIORITY+4)
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#define FAILSAFE_TIMEOUT_MS 30
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enum {PID_RATE_ROLL, PID_RATE_PITCH, PID_RATE_YAW, PID_ROLL, PID_PITCH, PID_YAW, PID_MAX};
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enum {ROLL,PITCH,YAW,MAX_AXES};
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// Private types
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typedef struct {
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float p;
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float i;
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float d;
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float iLim;
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float iAccumulator;
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float lastErr;
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} pid_type;
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// Private variables
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static xTaskHandle taskHandle;
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static StabilizationSettingsData settings;
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static xQueueHandle queue;
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float dT = 1;
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pid_type pids[PID_MAX];
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// Private functions
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static void stabilizationTask(void* parameters);
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static float ApplyPid(pid_type * pid, const float err);
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static float bound(float val);
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static void ZeroPids(void);
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static void SettingsUpdatedCb(UAVObjEvent * ev);
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/**
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* Module initialization
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*/
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int32_t StabilizationInitialize()
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{
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// Initialize variables
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// Create object queue
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queue = xQueueCreate(MAX_QUEUE_SIZE, sizeof(UAVObjEvent));
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// Listen for updates.
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// AttitudeActualConnectQueue(queue);
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AttitudeRawConnectQueue(queue);
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StabilizationSettingsConnectCallback(SettingsUpdatedCb);
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SettingsUpdatedCb(StabilizationSettingsHandle());
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// Start main task
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xTaskCreate(stabilizationTask, (signed char*)"Stabilization", STACK_SIZE_BYTES/4, NULL, TASK_PRIORITY, &taskHandle);
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TaskMonitorAdd(TASKINFO_RUNNING_STABILIZATION, taskHandle);
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PIOS_WDG_RegisterFlag(PIOS_WDG_STABILIZATION);
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return 0;
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}
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/**
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* Module task
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*/
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static void stabilizationTask(void* parameters)
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{
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portTickType lastSysTime;
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portTickType thisSysTime;
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UAVObjEvent ev;
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ActuatorDesiredData actuatorDesired;
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StabilizationDesiredData stabDesired;
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RateDesiredData rateDesired;
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AttitudeActualData attitudeActual;
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AttitudeRawData attitudeRaw;
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SystemSettingsData systemSettings;
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FlightStatusData flightStatus;
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SettingsUpdatedCb((UAVObjEvent *) NULL);
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// Main task loop
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lastSysTime = xTaskGetTickCount();
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ZeroPids();
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while(1) {
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PIOS_WDG_UpdateFlag(PIOS_WDG_STABILIZATION);
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// Wait until the AttitudeRaw object is updated, if a timeout then go to failsafe
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if ( xQueueReceive(queue, &ev, FAILSAFE_TIMEOUT_MS / portTICK_RATE_MS) != pdTRUE )
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{
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AlarmsSet(SYSTEMALARMS_ALARM_STABILIZATION,SYSTEMALARMS_ALARM_WARNING);
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continue;
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}
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// Check how long since last update
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thisSysTime = xTaskGetTickCount();
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if(thisSysTime > lastSysTime) // reuse dt in case of wraparound
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dT = (thisSysTime - lastSysTime) / portTICK_RATE_MS / 1000.0f;
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lastSysTime = thisSysTime;
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FlightStatusGet(&flightStatus);
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StabilizationDesiredGet(&stabDesired);
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AttitudeActualGet(&attitudeActual);
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AttitudeRawGet(&attitudeRaw);
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RateDesiredGet(&rateDesired);
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SystemSettingsGet(&systemSettings);
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#if defined(PIOS_QUATERNION_STABILIZATION)
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// Quaternion calculation of error in each axis. Uses more memory.
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float rpy_desired[3];
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float q_desired[4];
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float q_error[4];
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float local_error[3];
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// Essentially zero errors for anything in rate or none
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if(stabDesired.StabilizationMode[STABILIZATIONDESIRED_STABILIZATIONMODE_ROLL] == STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE)
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rpy_desired[0] = stabDesired.Roll;
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else
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rpy_desired[0] = attitudeActual.Roll;
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if(stabDesired.StabilizationMode[STABILIZATIONDESIRED_STABILIZATIONMODE_PITCH] == STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE)
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rpy_desired[1] = stabDesired.Pitch;
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else
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rpy_desired[1] = attitudeActual.Pitch;
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if(stabDesired.StabilizationMode[STABILIZATIONDESIRED_STABILIZATIONMODE_YAW] == STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE)
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rpy_desired[2] = stabDesired.Yaw;
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else
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rpy_desired[2] = attitudeActual.Yaw;
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RPY2Quaternion(rpy_desired, q_desired);
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quat_inverse(q_desired);
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quat_mult(q_desired, &attitudeActual.q1, q_error);
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quat_inverse(q_error);
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Quaternion2RPY(q_error, local_error);
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#else
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// Simpler algorithm for CC, less memory
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float local_error[3] = {stabDesired.Roll - attitudeActual.Roll,
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stabDesired.Pitch - attitudeActual.Pitch,
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stabDesired.Yaw - attitudeActual.Yaw};
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local_error[2] = fmod(local_error[2] + 180, 360) - 180;
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#endif
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float *attitudeDesiredAxis = &stabDesired.Roll;
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float *actuatorDesiredAxis = &actuatorDesired.Roll;
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float *rateDesiredAxis = &rateDesired.Roll;
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//Calculate desired rate
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for(int8_t ct=0; ct< MAX_AXES; ct++)
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{
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switch(stabDesired.StabilizationMode[ct])
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{
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case STABILIZATIONDESIRED_STABILIZATIONMODE_RATE:
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rateDesiredAxis[ct] = attitudeDesiredAxis[ct];
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE:
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rateDesiredAxis[ct] = ApplyPid(&pids[PID_ROLL + ct], local_error[ct]);
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break;
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}
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}
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uint8_t shouldUpdate = 1;
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RateDesiredSet(&rateDesired);
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ActuatorDesiredGet(&actuatorDesired);
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//Calculate desired command
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for(int8_t ct=0; ct< MAX_AXES; ct++)
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{
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if(fabs(rateDesiredAxis[ct]) > settings.MaximumRate[ct])
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{
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if(rateDesiredAxis[ct] > 0)
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{
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rateDesiredAxis[ct] = settings.MaximumRate[ct];
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}else
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{
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rateDesiredAxis[ct] = -settings.MaximumRate[ct];
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}
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}
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switch(stabDesired.StabilizationMode[ct])
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{
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case STABILIZATIONDESIRED_STABILIZATIONMODE_RATE:
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case STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE:
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{
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float command = ApplyPid(&pids[PID_RATE_ROLL + ct], rateDesiredAxis[ct]-attitudeRaw.gyros[ct]);
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actuatorDesiredAxis[ct] = bound(command);
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break;
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}
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case STABILIZATIONDESIRED_STABILIZATIONMODE_NONE:
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switch (ct)
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{
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case ROLL:
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actuatorDesiredAxis[ct] = bound(attitudeDesiredAxis[ct]);
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shouldUpdate = 1;
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break;
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case PITCH:
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actuatorDesiredAxis[ct] = bound(attitudeDesiredAxis[ct]);
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shouldUpdate = 1;
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break;
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case YAW:
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actuatorDesiredAxis[ct] = bound(attitudeDesiredAxis[ct]);
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shouldUpdate = 1;
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break;
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}
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break;
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}
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}
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// Save dT
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actuatorDesired.UpdateTime = dT * 1000;
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if(PARSE_FLIGHT_MODE(flightStatus.FlightMode) == FLIGHTMODE_MANUAL)
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shouldUpdate = 0;
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if(shouldUpdate)
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{
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actuatorDesired.Throttle = stabDesired.Throttle;
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if(dT > 15)
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actuatorDesired.NumLongUpdates++;
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ActuatorDesiredSet(&actuatorDesired);
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}
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if(flightStatus.Armed != FLIGHTSTATUS_ARMED_ARMED ||
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!shouldUpdate || (stabDesired.Throttle < 0))
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{
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ZeroPids();
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}
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// Clear alarms
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AlarmsClear(SYSTEMALARMS_ALARM_STABILIZATION);
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}
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}
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float ApplyPid(pid_type * pid, const float err)
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{
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float diff = (err - pid->lastErr);
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pid->lastErr = err;
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pid->iAccumulator += err * pid->i * dT;
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if(fabs(pid->iAccumulator) > pid->iLim) {
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if(pid->iAccumulator >0) {
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pid->iAccumulator = pid->iLim;
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} else {
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pid->iAccumulator = -pid->iLim;
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}
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}
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return ((err * pid->p) + pid->iAccumulator + (diff * pid->d / dT));
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}
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static void ZeroPids(void)
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{
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for(int8_t ct = 0; ct < PID_MAX; ct++) {
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pids[ct].iAccumulator = 0;
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pids[ct].lastErr = 0;
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}
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}
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/**
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* Bound input value between limits
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*/
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static float bound(float val)
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{
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if(val < -1) {
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val = -1;
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} else if(val > 1) {
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val = 1;
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}
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return val;
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}
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static void SettingsUpdatedCb(UAVObjEvent * ev)
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{
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memset(pids,0,sizeof (pid_type) * PID_MAX);
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StabilizationSettingsGet(&settings);
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float * data = settings.RollRatePI;
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for(int8_t pid=0; pid < PID_MAX; pid++)
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{
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pids[pid].p = *data++;
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pids[pid].i = *data++;
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pids[pid].iLim = *data++;
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}
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}
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/**
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* @}
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* @}
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*/
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