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https://bitbucket.org/librepilot/librepilot.git
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7d66a075de
1. Fix autoyaw to 0 attitude on takeoff post launch. 2. An error condition abort now properly disarms and continues to contrain thrust and stabi during disarmed state. 3. Increase thrustdown time from 2 to 5 seconds on an error condition (e.g. if 3 m deviation from takeoff position on NE).
268 lines
9.6 KiB
C++
268 lines
9.6 KiB
C++
/*
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******************************************************************************
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*
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* @file vtollandcontroller.cpp
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* @author The OpenPilot Team, http://www.openpilot.org Copyright (C) 2015.
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* @brief Vtol landing controller loop
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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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extern "C" {
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#include <openpilot.h>
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#include <callbackinfo.h>
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#include <math.h>
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#include <pid.h>
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#include <alarms.h>
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#include <CoordinateConversions.h>
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#include <sin_lookup.h>
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#include <pathdesired.h>
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#include <paths.h>
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#include "plans.h"
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#include <sanitycheck.h>
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#include <homelocation.h>
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#include <accelstate.h>
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#include <vtolpathfollowersettings.h>
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#include <flightstatus.h>
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#include <flightmodesettings.h>
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#include <pathstatus.h>
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#include <positionstate.h>
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#include <velocitystate.h>
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#include <velocitydesired.h>
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#include <stabilizationdesired.h>
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#include <airspeedstate.h>
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#include <attitudestate.h>
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#include <takeofflocation.h>
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#include <poilocation.h>
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#include <manualcontrolcommand.h>
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#include <systemsettings.h>
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#include <stabilizationbank.h>
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#include <stabilizationdesired.h>
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#include <vtolselftuningstats.h>
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#include <pathsummary.h>
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}
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// C++ includes
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#include "vtolautotakeoffcontroller.h"
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#include "pathfollowerfsm.h"
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#include "vtolautotakeofffsm.h"
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#include "pidcontroldown.h"
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// Private constants
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// pointer to a singleton instance
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VtolAutoTakeoffController *VtolAutoTakeoffController::p_inst = 0;
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VtolAutoTakeoffController::VtolAutoTakeoffController()
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: fsm(0), vtolPathFollowerSettings(0), mActive(false)
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{}
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// Called when mode first engaged
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void VtolAutoTakeoffController::Activate(void)
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{
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if (!mActive) {
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mActive = true;
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SettingsUpdated();
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fsm->Activate();
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controlDown.Activate();
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controlNE.Activate();
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}
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}
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uint8_t VtolAutoTakeoffController::IsActive(void)
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{
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return mActive;
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}
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uint8_t VtolAutoTakeoffController::Mode(void)
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{
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return PATHDESIRED_MODE_AUTOTAKEOFF;
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}
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// Objective updated in pathdesired, e.g. same flight mode but new target velocity
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void VtolAutoTakeoffController::ObjectiveUpdated(void)
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{
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// Set the objective's target velocity
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controlDown.UpdateVelocitySetpoint(pathDesired->ModeParameters[PATHDESIRED_MODEPARAMETER_AUTOTAKEOFF_DOWN]);
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controlNE.UpdateVelocitySetpoint(pathDesired->ModeParameters[PATHDESIRED_MODEPARAMETER_AUTOTAKEOFF_NORTH],
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pathDesired->ModeParameters[PATHDESIRED_MODEPARAMETER_AUTOTAKEOFF_EAST]);
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controlNE.UpdatePositionSetpoint(pathDesired->End.North, pathDesired->End.East);
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controlDown.UpdatePositionSetpoint(pathDesired->End.Down);
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fsm->setControlState((StatusVtolAutoTakeoffControlStateOptions)pathDesired->ModeParameters[PATHDESIRED_MODEPARAMETER_AUTOTAKEOFF_CONTROLSTATE]);
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}
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void VtolAutoTakeoffController::Deactivate(void)
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{
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if (mActive) {
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mActive = false;
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fsm->Inactive();
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controlDown.Deactivate();
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controlNE.Deactivate();
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}
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}
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// AutoTakeoff Uses different vertical velocity PID.
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void VtolAutoTakeoffController::SettingsUpdated(void)
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{
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const float dT = vtolPathFollowerSettings->UpdatePeriod / 1000.0f;
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controlNE.UpdateParameters(vtolPathFollowerSettings->HorizontalVelPID.Kp,
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vtolPathFollowerSettings->HorizontalVelPID.Ki,
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vtolPathFollowerSettings->HorizontalVelPID.Kd,
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vtolPathFollowerSettings->HorizontalVelPID.Beta,
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dT,
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vtolPathFollowerSettings->HorizontalVelMax);
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controlNE.UpdatePositionalParameters(vtolPathFollowerSettings->HorizontalPosP);
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controlNE.UpdateCommandParameters(-vtolPathFollowerSettings->MaxRollPitch, vtolPathFollowerSettings->MaxRollPitch, vtolPathFollowerSettings->VelocityFeedforward);
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controlDown.UpdateParameters(vtolPathFollowerSettings->AutoTakeoffVerticalVelPID.Kp,
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vtolPathFollowerSettings->AutoTakeoffVerticalVelPID.Ki,
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vtolPathFollowerSettings->AutoTakeoffVerticalVelPID.Kd,
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vtolPathFollowerSettings->AutoTakeoffVerticalVelPID.Beta,
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dT,
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vtolPathFollowerSettings->VerticalVelMax);
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controlDown.UpdatePositionalParameters(vtolPathFollowerSettings->VerticalPosP);
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VtolSelfTuningStatsData vtolSelfTuningStats;
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VtolSelfTuningStatsGet(&vtolSelfTuningStats);
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controlDown.UpdateNeutralThrust(vtolSelfTuningStats.NeutralThrustOffset + vtolPathFollowerSettings->ThrustLimits.Neutral);
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controlDown.SetThrustLimits(vtolPathFollowerSettings->ThrustLimits.Min, vtolPathFollowerSettings->ThrustLimits.Max);
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fsm->SettingsUpdated();
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}
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// AutoTakeoff Uses a different FSM to its parent
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int32_t VtolAutoTakeoffController::Initialize(VtolPathFollowerSettingsData *ptr_vtolPathFollowerSettings)
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{
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PIOS_Assert(ptr_vtolPathFollowerSettings);
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vtolPathFollowerSettings = ptr_vtolPathFollowerSettings;
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if (fsm == 0) {
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fsm = VtolAutoTakeoffFSM::instance();
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VtolAutoTakeoffFSM::instance()->Initialize(vtolPathFollowerSettings, pathDesired, flightStatus);
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controlDown.Initialize(fsm);
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}
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return 0;
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}
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void VtolAutoTakeoffController::UpdateVelocityDesired()
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{
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VelocityStateData velocityState;
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VelocityStateGet(&velocityState);
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VelocityDesiredData velocityDesired;
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PositionStateData positionState;
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PositionStateGet(&positionState);
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if (fsm->PositionHoldState()) {
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controlDown.UpdatePositionState(positionState.Down);
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controlDown.ControlPosition();
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}
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controlDown.UpdateVelocityState(velocityState.Down);
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controlNE.UpdateVelocityState(velocityState.North, velocityState.East);
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controlNE.UpdatePositionState(positionState.North, positionState.East);
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controlNE.ControlPosition();
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velocityDesired.Down = controlDown.GetVelocityDesired();
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float north, east;
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controlNE.GetVelocityDesired(&north, &east);
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velocityDesired.North = north;
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velocityDesired.East = east;
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// update pathstatus
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pathStatus->error = 0.0f;
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pathStatus->fractional_progress = 0.0f;
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if (fsm->PositionHoldState()) {
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pathStatus->fractional_progress = 1.0f;
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// note if the takeoff waypoint and the launch position are significantly different
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// the above check might need to expand to assessment of north and east.
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}
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pathStatus->path_direction_north = velocityDesired.North;
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pathStatus->path_direction_east = velocityDesired.East;
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pathStatus->path_direction_down = velocityDesired.Down;
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pathStatus->correction_direction_north = velocityDesired.North - velocityState.North;
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pathStatus->correction_direction_east = velocityDesired.East - velocityState.East;
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pathStatus->correction_direction_down = velocityDesired.Down - velocityState.Down;
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VelocityDesiredSet(&velocityDesired);
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}
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int8_t VtolAutoTakeoffController::UpdateStabilizationDesired()
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{
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uint8_t result = 1;
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StabilizationDesiredData stabDesired;
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AttitudeStateData attitudeState;
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StabilizationBankData stabSettings;
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float northCommand;
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float eastCommand;
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StabilizationDesiredGet(&stabDesired);
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AttitudeStateGet(&attitudeState);
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StabilizationBankGet(&stabSettings);
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controlNE.GetNECommand(&northCommand, &eastCommand);
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stabDesired.Thrust = controlDown.GetDownCommand();
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float angle_radians = DEG2RAD(attitudeState.Yaw);
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float cos_angle = cosf(angle_radians);
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float sine_angle = sinf(angle_radians);
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float maxPitch = vtolPathFollowerSettings->MaxRollPitch;
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stabDesired.StabilizationMode.Pitch = STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE;
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stabDesired.Pitch = boundf(-northCommand * cos_angle - eastCommand * sine_angle, -maxPitch, maxPitch);
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stabDesired.StabilizationMode.Roll = STABILIZATIONDESIRED_STABILIZATIONMODE_ATTITUDE;
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stabDesired.Roll = boundf(-northCommand * sine_angle + eastCommand * cos_angle, -maxPitch, maxPitch);
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ManualControlCommandData manualControl;
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ManualControlCommandGet(&manualControl);
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stabDesired.StabilizationMode.Yaw = STABILIZATIONDESIRED_STABILIZATIONMODE_AXISLOCK;
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stabDesired.Yaw = stabSettings.MaximumRate.Yaw * manualControl.Yaw;
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// default thrust mode to cruise control
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stabDesired.StabilizationMode.Thrust = STABILIZATIONDESIRED_STABILIZATIONMODE_CRUISECONTROL;
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fsm->ConstrainStabiDesired(&stabDesired); // excludes thrust
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StabilizationDesiredSet(&stabDesired);
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return result;
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}
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void VtolAutoTakeoffController::UpdateAutoPilot()
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{
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fsm->Update();
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UpdateVelocityDesired();
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int8_t result = UpdateStabilizationDesired();
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if (result) {
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AlarmsSet(SYSTEMALARMS_ALARM_GUIDANCE, SYSTEMALARMS_ALARM_OK);
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} else {
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pathStatus->Status = PATHSTATUS_STATUS_CRITICAL;
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AlarmsSet(SYSTEMALARMS_ALARM_GUIDANCE, SYSTEMALARMS_ALARM_WARNING);
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}
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PathStatusSet(pathStatus);
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}
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