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317 lines
14 KiB
C
317 lines
14 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 AttitudeState "Attitude State"
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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 <pios_struct_helper.h>
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#include <pid.h>
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#include <manualcontrolcommand.h>
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#include <flightmodesettings.h>
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#include <stabilizationsettings.h>
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#include <stabilizationdesired.h>
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#include <stabilizationstatus.h>
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#include <stabilizationbank.h>
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#include <stabilizationsettingsbank1.h>
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#include <stabilizationsettingsbank2.h>
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#include <stabilizationsettingsbank3.h>
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#include <relaytuning.h>
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#include <relaytuningsettings.h>
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#include <ratedesired.h>
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#include <sin_lookup.h>
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#include <stabilization.h>
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#include <innerloop.h>
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#include <outerloop.h>
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#include <altitudeloop.h>
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// Public variables
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StabilizationData stabSettings;
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// Private variables
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static int cur_flight_mode = -1;
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// Private functions
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static void SettingsUpdatedCb(UAVObjEvent *ev);
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static void BankUpdatedCb(UAVObjEvent *ev);
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static void SettingsBankUpdatedCb(UAVObjEvent *ev);
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static void FlightModeSwitchUpdatedCb(UAVObjEvent *ev);
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static void StabilizationDesiredUpdatedCb(UAVObjEvent *ev);
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/**
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* Module initialization
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*/
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int32_t StabilizationStart()
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{
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StabilizationSettingsConnectCallback(SettingsUpdatedCb);
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ManualControlCommandConnectCallback(FlightModeSwitchUpdatedCb);
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StabilizationBankConnectCallback(BankUpdatedCb);
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StabilizationSettingsBank1ConnectCallback(SettingsBankUpdatedCb);
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StabilizationSettingsBank2ConnectCallback(SettingsBankUpdatedCb);
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StabilizationSettingsBank3ConnectCallback(SettingsBankUpdatedCb);
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StabilizationDesiredConnectCallback(StabilizationDesiredUpdatedCb);
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SettingsUpdatedCb(StabilizationSettingsHandle());
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StabilizationDesiredUpdatedCb(StabilizationDesiredHandle());
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FlightModeSwitchUpdatedCb(ManualControlCommandHandle());
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BankUpdatedCb(StabilizationBankHandle());
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#ifdef PIOS_INCLUDE_WDG
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PIOS_WDG_RegisterFlag(PIOS_WDG_STABILIZATION);
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#endif
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return 0;
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}
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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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StabilizationDesiredInitialize();
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StabilizationSettingsInitialize();
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StabilizationStatusInitialize();
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StabilizationBankInitialize();
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StabilizationSettingsBank1Initialize();
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StabilizationSettingsBank2Initialize();
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StabilizationSettingsBank3Initialize();
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RateDesiredInitialize();
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ManualControlCommandInitialize(); // only used for PID bank selection based on flight mode switch
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// Code required for relay tuning
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sin_lookup_initalize();
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RelayTuningSettingsInitialize();
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RelayTuningInitialize();
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stabilizationOuterloopInit();
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stabilizationInnerloopInit();
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#ifdef REVOLUTION
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stabilizationAltitudeloopInit();
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#endif
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pid_zero(&stabSettings.outerPids[0]);
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pid_zero(&stabSettings.outerPids[1]);
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pid_zero(&stabSettings.outerPids[2]);
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pid_zero(&stabSettings.innerPids[0]);
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pid_zero(&stabSettings.innerPids[1]);
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pid_zero(&stabSettings.innerPids[2]);
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return 0;
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}
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MODULE_INITCALL(StabilizationInitialize, StabilizationStart);
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static void StabilizationDesiredUpdatedCb(__attribute__((unused)) UAVObjEvent *ev)
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{
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StabilizationStatusData status;
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StabilizationDesiredStabilizationModeData mode;
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int t;
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StabilizationDesiredStabilizationModeGet(&mode);
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for (t = 0; t < AXES; t++) {
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switch (cast_struct_to_array(mode, mode.Roll)[t]) {
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case STABILIZATIONDESIRED_STABILIZATIONMODE_MANUAL:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_DIRECT;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_DIRECT;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_RATE:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_DIRECT;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_RATE;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_ATTITUDE;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_RATE;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_AXISLOCK:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_DIRECT;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_AXISLOCK;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_WEAKLEVELING:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_WEAKLEVELING;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_RATE;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_VIRTUALBAR:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_DIRECT;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_VIRTUALFLYBAR;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_RATTITUDE:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_RATTITUDE;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_RATE;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_RELAYRATE:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_DIRECT;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_RELAYTUNING;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_RELAYATTITUDE:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_ATTITUDE;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_RELAYTUNING;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_ALTITUDEHOLD:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_ALTITUDE;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_CRUISECONTROL;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_VERTICALVELOCITY:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_VERTICALVELOCITY;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_CRUISECONTROL;
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break;
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case STABILIZATIONDESIRED_STABILIZATIONMODE_CRUISECONTROL:
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cast_struct_to_array(status.OuterLoop, status.OuterLoop.Roll)[t] = STABILIZATIONSTATUS_OUTERLOOP_DIRECT;
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cast_struct_to_array(status.InnerLoop, status.InnerLoop.Roll)[t] = STABILIZATIONSTATUS_INNERLOOP_CRUISECONTROL;
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break;
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}
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}
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StabilizationStatusSet(&status);
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}
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static void FlightModeSwitchUpdatedCb(__attribute__((unused)) UAVObjEvent *ev)
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{
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uint8_t fm;
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ManualControlCommandFlightModeSwitchPositionGet(&fm);
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if (fm == cur_flight_mode) {
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return;
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}
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cur_flight_mode = fm;
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SettingsBankUpdatedCb(NULL);
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}
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static void SettingsBankUpdatedCb(__attribute__((unused)) UAVObjEvent *ev)
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{
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if (cur_flight_mode < 0 || cur_flight_mode >= FLIGHTMODESETTINGS_FLIGHTMODEPOSITION_NUMELEM) {
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return;
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}
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if ((ev) && ((stabSettings.settings.FlightModeMap[cur_flight_mode] == 0 && ev->obj != StabilizationSettingsBank1Handle()) ||
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(stabSettings.settings.FlightModeMap[cur_flight_mode] == 1 && ev->obj != StabilizationSettingsBank2Handle()) ||
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(stabSettings.settings.FlightModeMap[cur_flight_mode] == 2 && ev->obj != StabilizationSettingsBank3Handle()) ||
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stabSettings.settings.FlightModeMap[cur_flight_mode] > 2)) {
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return;
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}
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switch (stabSettings.settings.FlightModeMap[cur_flight_mode]) {
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case 0:
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StabilizationSettingsBank1Get((StabilizationSettingsBank1Data *)&stabSettings.stabBank);
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break;
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case 1:
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StabilizationSettingsBank2Get((StabilizationSettingsBank2Data *)&stabSettings.stabBank);
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break;
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case 2:
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StabilizationSettingsBank3Get((StabilizationSettingsBank3Data *)&stabSettings.stabBank);
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break;
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}
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StabilizationBankSet(&stabSettings.stabBank);
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}
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static void BankUpdatedCb(__attribute__((unused)) UAVObjEvent *ev)
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{
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StabilizationBankGet(&stabSettings.stabBank);
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// Set the roll rate PID constants
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pid_configure(&stabSettings.innerPids[0], stabSettings.stabBank.RollRatePID.Kp,
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stabSettings.stabBank.RollRatePID.Ki,
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stabSettings.stabBank.RollRatePID.Kd,
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stabSettings.stabBank.RollRatePID.ILimit);
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// Set the pitch rate PID constants
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pid_configure(&stabSettings.innerPids[1], stabSettings.stabBank.PitchRatePID.Kp,
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stabSettings.stabBank.PitchRatePID.Ki,
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stabSettings.stabBank.PitchRatePID.Kd,
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stabSettings.stabBank.PitchRatePID.ILimit);
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// Set the yaw rate PID constants
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pid_configure(&stabSettings.innerPids[2], stabSettings.stabBank.YawRatePID.Kp,
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stabSettings.stabBank.YawRatePID.Ki,
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stabSettings.stabBank.YawRatePID.Kd,
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stabSettings.stabBank.YawRatePID.ILimit);
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// Set the roll attitude PI constants
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pid_configure(&stabSettings.outerPids[0], stabSettings.stabBank.RollPI.Kp,
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stabSettings.stabBank.RollPI.Ki,
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0,
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stabSettings.stabBank.RollPI.ILimit);
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// Set the pitch attitude PI constants
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pid_configure(&stabSettings.outerPids[1], stabSettings.stabBank.PitchPI.Kp,
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stabSettings.stabBank.PitchPI.Ki,
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0,
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stabSettings.stabBank.PitchPI.ILimit);
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// Set the yaw attitude PI constants
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pid_configure(&stabSettings.outerPids[2], stabSettings.stabBank.YawPI.Kp,
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stabSettings.stabBank.YawPI.Ki,
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0,
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stabSettings.stabBank.YawPI.ILimit);
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}
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static void SettingsUpdatedCb(__attribute__((unused)) UAVObjEvent *ev)
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{
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// needs no mutex, as long as eventdispatcher and Stabilization are both TASK_PRIORITY_CRITICAL
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StabilizationSettingsGet(&stabSettings.settings);
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// Set up the derivative term
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pid_configure_derivative(stabSettings.settings.DerivativeCutoff, stabSettings.settings.DerivativeGamma);
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// The dT has some jitter iteration to iteration that we don't want to
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// make thie result unpredictable. Still, it's nicer to specify the constant
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// based on a time (in ms) rather than a fixed multiplier. The error between
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// update rates on OP (~300 Hz) and CC (~475 Hz) is negligible for this
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// calculation
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const float fakeDt = 0.0025f;
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if (stabSettings.settings.GyroTau < 0.0001f) {
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stabSettings.gyro_alpha = 0; // not trusting this to resolve to 0
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} else {
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stabSettings.gyro_alpha = expf(-fakeDt / stabSettings.settings.GyroTau);
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}
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// force flight mode update
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cur_flight_mode = -1;
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// Rattitude stick angle where the attitude to rate transition happens
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if (stabSettings.settings.RattitudeModeTransition < (uint8_t)10) {
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stabSettings.rattitude_mode_transition_stick_position = 10.0f / 100.0f;
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} else {
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stabSettings.rattitude_mode_transition_stick_position = (float)stabSettings.settings.RattitudeModeTransition / 100.0f;
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}
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stabSettings.cruiseControl.min_thrust = (float)stabSettings.settings.CruiseControlMinThrust / 100.0f;
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stabSettings.cruiseControl.max_thrust = (float)stabSettings.settings.CruiseControlMaxThrust / 100.0f;
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stabSettings.cruiseControl.thrust_difference = stabSettings.cruiseControl.max_thrust - stabSettings.cruiseControl.min_thrust;
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stabSettings.cruiseControl.power_trim = stabSettings.settings.CruiseControlPowerTrim / 100.0f;
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stabSettings.cruiseControl.half_power_delay = stabSettings.settings.CruiseControlPowerDelayComp / 2.0f;
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stabSettings.cruiseControl.max_power_factor_angle = RAD2DEG(acosf(1.0f / stabSettings.settings.CruiseControlMaxPowerFactor));
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}
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/**
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* @}
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* @}
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*/
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