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ACS Ptg Ctrl Fixes #643

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muellerr merged 35 commits from acs-ptg-ctrl-fixes-2 into v3.0.0-dev 2023-06-07 11:49:10 +02:00
Conversation 0 Commits 35 Files Changed 15 +315 -280
15 changed files with 315 additions and 280 deletions
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3
CHANGELOG.md
View File

@ -62,6 +62,7 @@ will consitute of a breaking change warranting a new major release:
- ACU dummy HK sets
- IMTQ HK sets
- IMTQ dummy now handles power switch
- Added some new ACS parameters
## Fixed
@ -96,6 +97,8 @@ will consitute of a breaking change warranting a new major release:
- STR datasets were not set to invalid on shutdown.
- Fixed usage of quaternion valid flag, which does not actually represent the validity of the
quaternion.
- Various fixes for the pointing modes of the `ACS Controller`. All modes should work now as
intended.
# [v2.0.5] 2023-05-11

112
mission/controller/AcsController.cpp
View File

@ -169,7 +169,7 @@ void AcsController::performSafe() {
guidance.getTargetParamsSafe(sunTargetDir);
double magMomMtq[3] = {0, 0, 0}, errAng = 0.0;
uint8_t safeCtrlStrat = safeCtrl.safeCtrlStrategy(
acs::SafeModeStrategy safeCtrlStrat = safeCtrl.safeCtrlStrategy(
mgmDataProcessed.mgmVecTot.isValid(), not mekfInvalidFlag,
gyrDataProcessed.gyrVecTot.isValid(), susDataProcessed.susVecTot.isValid(),
acsParameters.safeModeControllerParameters.useMekf,
@ -205,11 +205,13 @@ void AcsController::performSafe() {
case (acs::SafeModeStrategy::SAFECTRL_NO_SENSORS_FOR_CONTROL):
safeCtrlFailure(0, 1);
break;
default:
sif::error << "AcsController: Invalid safe mode strategy for performSafe" << std::endl;
break;
}
actuatorCmd.cmdDipolMtq(magMomMtq, cmdDipolMtqs,
*acsParameters.magnetorquerParameter.inverseAlignment,
acsParameters.magnetorquerParameter.dipolMax);
actuatorCmd.cmdDipoleMtq(*acsParameters.magnetorquerParameter.inverseAlignment,
acsParameters.magnetorquerParameter.dipoleMax, magMomMtq, cmdDipoleMtqs);
// detumble check and switch
if (mekfData.satRotRateMekf.isValid() && acsParameters.safeModeControllerParameters.useMekf &&
@ -231,8 +233,8 @@ void AcsController::performSafe() {
}
updateCtrlValData(errAng, safeCtrlStrat);
updateActuatorCmdData(cmdDipolMtqs);
commandActuators(cmdDipolMtqs[0], cmdDipolMtqs[1], cmdDipolMtqs[2],
updateActuatorCmdData(cmdDipoleMtqs);
commandActuators(cmdDipoleMtqs[0], cmdDipoleMtqs[1], cmdDipoleMtqs[2],
acsParameters.magnetorquerParameter.torqueDuration);
}
@ -259,7 +261,7 @@ void AcsController::performDetumble() {
triggerEvent(acs::MEKF_RECOVERY);
mekfInvalidFlag = false;
}
uint8_t safeCtrlStrat = detumble.detumbleStrategy(
acs::SafeModeStrategy safeCtrlStrat = detumble.detumbleStrategy(
mgmDataProcessed.mgmVecTot.isValid(), gyrDataProcessed.gyrVecTot.isValid(),
mgmDataProcessed.mgmVecTotDerivative.isValid(),
acsParameters.detumbleParameter.useFullDetumbleLaw);
@ -279,11 +281,13 @@ void AcsController::performDetumble() {
case (acs::SafeModeStrategy::SAFECTRL_NO_SENSORS_FOR_CONTROL):
safeCtrlFailure(0, 1);
break;
default:
sif::error << "AcsController: Invalid safe mode strategy for performDetumble" << std::endl;
break;
}
actuatorCmd.cmdDipolMtq(magMomMtq, cmdDipolMtqs,
*acsParameters.magnetorquerParameter.inverseAlignment,
acsParameters.magnetorquerParameter.dipolMax);
actuatorCmd.cmdDipoleMtq(*acsParameters.magnetorquerParameter.inverseAlignment,
acsParameters.magnetorquerParameter.dipoleMax, magMomMtq, cmdDipoleMtqs);
if (mekfData.satRotRateMekf.isValid() &&
VectorOperations<double>::norm(mekfData.satRotRateMekf.value, 3) <
@ -304,8 +308,8 @@ void AcsController::performDetumble() {
}
disableCtrlValData();
updateActuatorCmdData(cmdDipolMtqs);
commandActuators(cmdDipolMtqs[0], cmdDipolMtqs[1], cmdDipolMtqs[2],
updateActuatorCmdData(cmdDipoleMtqs);
commandActuators(cmdDipoleMtqs[0], cmdDipoleMtqs[1], cmdDipoleMtqs[2],
acsParameters.magnetorquerParameter.torqueDuration);
}
@ -366,24 +370,26 @@ void AcsController::performPointingCtrl() {
// Variables required for setting actuators
double torquePtgRws[4] = {0, 0, 0, 0}, rwTrqNs[4] = {0, 0, 0, 0}, torqueRws[4] = {0, 0, 0, 0},
mgtDpDes[3] = {0, 0, 0};
switch (mode) {
case acs::PTG_IDLE:
guidance.targetQuatPtgSun(susDataProcessed.sunIjkModel.value, targetQuat, targetSatRotRate);
guidance.targetQuatPtgSun(now, susDataProcessed.sunIjkModel.value, targetQuat,
targetSatRotRate);
guidance.comparePtg(mekfData.quatMekf.value, mekfData.satRotRateMekf.value, targetQuat,
targetSatRotRate, errorQuat, errorSatRotRate, errorAngle);
ptgCtrl.ptgLaw(&acsParameters.idleModeControllerParameters, errorQuat, errorSatRotRate,
*rwPseudoInv, torquePtgRws);
ptgCtrl.ptgNullspace(
&acsParameters.idleModeControllerParameters, &(sensorValues.rw1Set.currSpeed.value),
&(sensorValues.rw2Set.currSpeed.value), &(sensorValues.rw3Set.currSpeed.value),
&(sensorValues.rw4Set.currSpeed.value), rwTrqNs);
ptgCtrl.ptgNullspace(&acsParameters.idleModeControllerParameters,
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value,
rwTrqNs);
VectorOperations<double>::add(torquePtgRws, rwTrqNs, torqueRws, 4);
actuatorCmd.scalingTorqueRws(torqueRws, acsParameters.rwHandlingParameters.maxTrq);
ptgCtrl.ptgDesaturation(
&acsParameters.idleModeControllerParameters, mgmDataProcessed.mgmVecTot.value,
mgmDataProcessed.mgmVecTot.isValid(), mekfData.satRotRateMekf.value,
&(sensorValues.rw1Set.currSpeed.value), &(sensorValues.rw2Set.currSpeed.value),
&(sensorValues.rw3Set.currSpeed.value), &(sensorValues.rw4Set.currSpeed.value), mgtDpDes);
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value, mgtDpDes);
enableAntiStiction = acsParameters.idleModeControllerParameters.enableAntiStiction;
break;
@ -397,17 +403,17 @@ void AcsController::performPointingCtrl() {
errorSatRotRate, errorAngle);
ptgCtrl.ptgLaw(&acsParameters.targetModeControllerParameters, errorQuat, errorSatRotRate,
*rwPseudoInv, torquePtgRws);
ptgCtrl.ptgNullspace(
&acsParameters.targetModeControllerParameters, &(sensorValues.rw1Set.currSpeed.value),
&(sensorValues.rw2Set.currSpeed.value), &(sensorValues.rw3Set.currSpeed.value),
&(sensorValues.rw4Set.currSpeed.value), rwTrqNs);
ptgCtrl.ptgNullspace(&acsParameters.targetModeControllerParameters,
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value,
rwTrqNs);
VectorOperations<double>::add(torquePtgRws, rwTrqNs, torqueRws, 4);
actuatorCmd.scalingTorqueRws(torqueRws, acsParameters.rwHandlingParameters.maxTrq);
ptgCtrl.ptgDesaturation(
&acsParameters.targetModeControllerParameters, mgmDataProcessed.mgmVecTot.value,
mgmDataProcessed.mgmVecTot.isValid(), mekfData.satRotRateMekf.value,
&(sensorValues.rw1Set.currSpeed.value), &(sensorValues.rw2Set.currSpeed.value),
&(sensorValues.rw3Set.currSpeed.value), &(sensorValues.rw4Set.currSpeed.value), mgtDpDes);
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value, mgtDpDes);
enableAntiStiction = acsParameters.targetModeControllerParameters.enableAntiStiction;
break;
@ -418,17 +424,17 @@ void AcsController::performPointingCtrl() {
targetSatRotRate, errorQuat, errorSatRotRate, errorAngle);
ptgCtrl.ptgLaw(&acsParameters.gsTargetModeControllerParameters, errorQuat, errorSatRotRate,
*rwPseudoInv, torquePtgRws);
ptgCtrl.ptgNullspace(
&acsParameters.gsTargetModeControllerParameters, &(sensorValues.rw1Set.currSpeed.value),
&(sensorValues.rw2Set.currSpeed.value), &(sensorValues.rw3Set.currSpeed.value),
&(sensorValues.rw4Set.currSpeed.value), rwTrqNs);
ptgCtrl.ptgNullspace(&acsParameters.gsTargetModeControllerParameters,
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value,
rwTrqNs);
VectorOperations<double>::add(torquePtgRws, rwTrqNs, torqueRws, 4);
actuatorCmd.scalingTorqueRws(torqueRws, acsParameters.rwHandlingParameters.maxTrq);
ptgCtrl.ptgDesaturation(
&acsParameters.gsTargetModeControllerParameters, mgmDataProcessed.mgmVecTot.value,
mgmDataProcessed.mgmVecTot.isValid(), mekfData.satRotRateMekf.value,
&(sensorValues.rw1Set.currSpeed.value), &(sensorValues.rw2Set.currSpeed.value),
&(sensorValues.rw3Set.currSpeed.value), &(sensorValues.rw4Set.currSpeed.value), mgtDpDes);
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value, mgtDpDes);
enableAntiStiction = acsParameters.gsTargetModeControllerParameters.enableAntiStiction;
break;
@ -442,63 +448,61 @@ void AcsController::performPointingCtrl() {
errorSatRotRate, errorAngle);
ptgCtrl.ptgLaw(&acsParameters.nadirModeControllerParameters, errorQuat, errorSatRotRate,
*rwPseudoInv, torquePtgRws);
ptgCtrl.ptgNullspace(
&acsParameters.nadirModeControllerParameters, &(sensorValues.rw1Set.currSpeed.value),
&(sensorValues.rw2Set.currSpeed.value), &(sensorValues.rw3Set.currSpeed.value),
&(sensorValues.rw4Set.currSpeed.value), rwTrqNs);
ptgCtrl.ptgNullspace(&acsParameters.nadirModeControllerParameters,
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value,
rwTrqNs);
VectorOperations<double>::add(torquePtgRws, rwTrqNs, torqueRws, 4);
actuatorCmd.scalingTorqueRws(torqueRws, acsParameters.rwHandlingParameters.maxTrq);
ptgCtrl.ptgDesaturation(
&acsParameters.nadirModeControllerParameters, mgmDataProcessed.mgmVecTot.value,
mgmDataProcessed.mgmVecTot.isValid(), mekfData.satRotRateMekf.value,
&(sensorValues.rw1Set.currSpeed.value), &(sensorValues.rw2Set.currSpeed.value),
&(sensorValues.rw3Set.currSpeed.value), &(sensorValues.rw4Set.currSpeed.value), mgtDpDes);
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value, mgtDpDes);
enableAntiStiction = acsParameters.nadirModeControllerParameters.enableAntiStiction;
break;
case acs::PTG_INERTIAL:
std::memcpy(targetQuat, acsParameters.inertialModeControllerParameters.tgtQuat,
4 * sizeof(double));
sizeof(targetQuat));
guidance.comparePtg(mekfData.quatMekf.value, mekfData.satRotRateMekf.value, targetQuat,
targetSatRotRate, acsParameters.inertialModeControllerParameters.quatRef,
acsParameters.inertialModeControllerParameters.refRotRate, errorQuat,
errorSatRotRate, errorAngle);
ptgCtrl.ptgLaw(&acsParameters.inertialModeControllerParameters, errorQuat, errorSatRotRate,
*rwPseudoInv, torquePtgRws);
ptgCtrl.ptgNullspace(
&acsParameters.inertialModeControllerParameters, &(sensorValues.rw1Set.currSpeed.value),
&(sensorValues.rw2Set.currSpeed.value), &(sensorValues.rw3Set.currSpeed.value),
&(sensorValues.rw4Set.currSpeed.value), rwTrqNs);
ptgCtrl.ptgNullspace(&acsParameters.inertialModeControllerParameters,
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value,
rwTrqNs);
VectorOperations<double>::add(torquePtgRws, rwTrqNs, torqueRws, 4);
actuatorCmd.scalingTorqueRws(torqueRws, acsParameters.rwHandlingParameters.maxTrq);
ptgCtrl.ptgDesaturation(
&acsParameters.inertialModeControllerParameters, mgmDataProcessed.mgmVecTot.value,
mgmDataProcessed.mgmVecTot.isValid(), mekfData.satRotRateMekf.value,
&(sensorValues.rw1Set.currSpeed.value), &(sensorValues.rw2Set.currSpeed.value),
&(sensorValues.rw3Set.currSpeed.value), &(sensorValues.rw4Set.currSpeed.value), mgtDpDes);
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value, mgtDpDes);
enableAntiStiction = acsParameters.inertialModeControllerParameters.enableAntiStiction;
break;
default:
sif::error << "AcsController: Invalid mode for performPointingCtrl";
sif::error << "AcsController: Invalid mode for performPointingCtrl" << std::endl;
break;
}
actuatorCmd.cmdSpeedToRws(
sensorValues.rw1Set.currSpeed.value, sensorValues.rw2Set.currSpeed.value,
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value, torqueRws,
cmdSpeedRws, acsParameters.onBoardParams.sampleTime,
acsParameters.rwHandlingParameters.maxRwSpeed,
acsParameters.rwHandlingParameters.inertiaWheel);
sensorValues.rw3Set.currSpeed.value, sensorValues.rw4Set.currSpeed.value,
acsParameters.onBoardParams.sampleTime, acsParameters.rwHandlingParameters.inertiaWheel,
acsParameters.rwHandlingParameters.maxRwSpeed, torqueRws, cmdSpeedRws);
if (enableAntiStiction) {
ptgCtrl.rwAntistiction(&sensorValues, cmdSpeedRws);
}
actuatorCmd.cmdDipolMtq(mgtDpDes, cmdDipolMtqs,
*acsParameters.magnetorquerParameter.inverseAlignment,
acsParameters.magnetorquerParameter.dipolMax);
actuatorCmd.cmdDipoleMtq(*acsParameters.magnetorquerParameter.inverseAlignment,
acsParameters.magnetorquerParameter.dipoleMax, mgtDpDes, cmdDipoleMtqs);
updateCtrlValData(targetQuat, errorQuat, errorAngle, targetSatRotRate);
updateActuatorCmdData(torqueRws, cmdSpeedRws, cmdDipolMtqs);
commandActuators(cmdDipolMtqs[0], cmdDipolMtqs[1], cmdDipolMtqs[2],
updateActuatorCmdData(torqueRws, cmdSpeedRws, cmdDipoleMtqs);
commandActuators(cmdDipoleMtqs[0], cmdDipoleMtqs[1], cmdDipoleMtqs[2],
acsParameters.magnetorquerParameter.torqueDuration, cmdSpeedRws[0],
cmdSpeedRws[1], cmdSpeedRws[2], cmdSpeedRws[3],
acsParameters.rwHandlingParameters.rampTime);

2
mission/controller/AcsController.h
View File

@ -69,7 +69,7 @@ class AcsController : public ExtendedControllerBase, public ReceivesParameterMes
bool mekfLost = false;
int32_t cmdSpeedRws[4] = {0, 0, 0, 0};
int16_t cmdDipolMtqs[3] = {0, 0, 0};
int16_t cmdDipoleMtqs[3] = {0, 0, 0};
#if OBSW_THREAD_TRACING == 1
uint32_t opCounter = 0;

93
mission/controller/acs/AcsParameters.cpp
View File

@ -318,7 +318,7 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->setMatrix(rwMatrices.without4);
break;
case 0x6:
parameterWrapper->setVector(rwMatrices.nullspace);
parameterWrapper->setVector(rwMatrices.nullspaceVector);
break;
default:
return INVALID_IDENTIFIER_ID;
@ -378,15 +378,18 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->set(idleModeControllerParameters.gainNullspace);
break;
case 0x5:
parameterWrapper->setVector(idleModeControllerParameters.desatMomentumRef);
parameterWrapper->set(idleModeControllerParameters.nullspaceSpeed);
muellerr commented 2023-06-06 11:19:50 +02:00
Review
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This looks like something which can break the MIB. Can it? If it does, I'd still be okay with this for v3.0.0 if the current MIB is not able to manipulate the parameter anyway.

This looks like something which can break the MIB. Can it? If it does, I'd still be okay with this for v3.0.0 if the current MIB is not able to manipulate the parameter anyway.
muellerr commented 2023-06-06 11:41:47 +02:00
Review
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after discussion: The operator manually specifies the parameter ID, so a release into v3.0.0 is okay.

after discussion: The operator manually specifies the parameter ID, so a release into v3.0.0 is okay.
break;
case 0x6:
parameterWrapper->set(idleModeControllerParameters.deSatGainFactor);
parameterWrapper->setVector(idleModeControllerParameters.desatMomentumRef);
break;
case 0x7:
parameterWrapper->set(idleModeControllerParameters.desatOn);
parameterWrapper->set(idleModeControllerParameters.deSatGainFactor);
break;
case 0x8:
parameterWrapper->set(idleModeControllerParameters.desatOn);
break;
case 0x9:
parameterWrapper->set(idleModeControllerParameters.enableAntiStiction);
break;
default:
@ -411,48 +414,51 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->set(targetModeControllerParameters.gainNullspace);
break;
case 0x5:
parameterWrapper->setVector(targetModeControllerParameters.desatMomentumRef);
parameterWrapper->set(targetModeControllerParameters.nullspaceSpeed);
break;
case 0x6:
parameterWrapper->set(targetModeControllerParameters.deSatGainFactor);
parameterWrapper->setVector(targetModeControllerParameters.desatMomentumRef);
break;
case 0x7:
parameterWrapper->set(targetModeControllerParameters.desatOn);
parameterWrapper->set(targetModeControllerParameters.deSatGainFactor);
break;
case 0x8:
parameterWrapper->set(targetModeControllerParameters.enableAntiStiction);
parameterWrapper->set(targetModeControllerParameters.desatOn);
break;
case 0x9:
parameterWrapper->setVector(targetModeControllerParameters.refDirection);
parameterWrapper->set(targetModeControllerParameters.enableAntiStiction);
break;
case 0xA:
parameterWrapper->setVector(targetModeControllerParameters.refRotRate);
parameterWrapper->setVector(targetModeControllerParameters.refDirection);
break;
case 0xB:
parameterWrapper->setVector(targetModeControllerParameters.quatRef);
parameterWrapper->setVector(targetModeControllerParameters.refRotRate);
break;
case 0xC:
parameterWrapper->set(targetModeControllerParameters.timeElapsedMax);
parameterWrapper->setVector(targetModeControllerParameters.quatRef);
break;
case 0xD:
parameterWrapper->set(targetModeControllerParameters.latitudeTgt);
parameterWrapper->set(targetModeControllerParameters.timeElapsedMax);
break;
case 0xE:
parameterWrapper->set(targetModeControllerParameters.longitudeTgt);
parameterWrapper->set(targetModeControllerParameters.latitudeTgt);
break;
case 0xF:
parameterWrapper->set(targetModeControllerParameters.altitudeTgt);
parameterWrapper->set(targetModeControllerParameters.longitudeTgt);
break;
case 0x10:
parameterWrapper->set(targetModeControllerParameters.avoidBlindStr);
parameterWrapper->set(targetModeControllerParameters.altitudeTgt);
break;
case 0x11:
parameterWrapper->set(targetModeControllerParameters.blindAvoidStart);
parameterWrapper->set(targetModeControllerParameters.avoidBlindStr);
break;
case 0x12:
parameterWrapper->set(targetModeControllerParameters.blindAvoidStop);
parameterWrapper->set(targetModeControllerParameters.blindAvoidStart);
break;
case 0x13:
parameterWrapper->set(targetModeControllerParameters.blindAvoidStop);
break;
case 0x14:
parameterWrapper->set(targetModeControllerParameters.blindRotRate);
break;
default:
@ -477,30 +483,33 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->set(gsTargetModeControllerParameters.gainNullspace);
break;
case 0x5:
parameterWrapper->setVector(gsTargetModeControllerParameters.desatMomentumRef);
parameterWrapper->set(gsTargetModeControllerParameters.nullspaceSpeed);
break;
case 0x6:
parameterWrapper->set(gsTargetModeControllerParameters.deSatGainFactor);
parameterWrapper->setVector(gsTargetModeControllerParameters.desatMomentumRef);
break;
case 0x7:
parameterWrapper->set(gsTargetModeControllerParameters.desatOn);
parameterWrapper->set(gsTargetModeControllerParameters.deSatGainFactor);
break;
case 0x8:
parameterWrapper->set(gsTargetModeControllerParameters.enableAntiStiction);
parameterWrapper->set(gsTargetModeControllerParameters.desatOn);
break;
case 0x9:
parameterWrapper->setVector(gsTargetModeControllerParameters.refDirection);
parameterWrapper->set(gsTargetModeControllerParameters.enableAntiStiction);
break;
case 0xA:
parameterWrapper->set(gsTargetModeControllerParameters.timeElapsedMax);
parameterWrapper->setVector(gsTargetModeControllerParameters.refDirection);
break;
case 0xB:
parameterWrapper->set(gsTargetModeControllerParameters.latitudeTgt);
parameterWrapper->set(gsTargetModeControllerParameters.timeElapsedMax);
break;
case 0xC:
parameterWrapper->set(gsTargetModeControllerParameters.longitudeTgt);
parameterWrapper->set(gsTargetModeControllerParameters.latitudeTgt);
break;
case 0xD:
parameterWrapper->set(gsTargetModeControllerParameters.longitudeTgt);
break;
case 0xE:
parameterWrapper->set(gsTargetModeControllerParameters.altitudeTgt);
break;
default:
@ -525,27 +534,30 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->set(nadirModeControllerParameters.gainNullspace);
break;
case 0x5:
parameterWrapper->setVector(nadirModeControllerParameters.desatMomentumRef);
parameterWrapper->set(nadirModeControllerParameters.nullspaceSpeed);
break;
case 0x6:
parameterWrapper->set(nadirModeControllerParameters.deSatGainFactor);
parameterWrapper->setVector(nadirModeControllerParameters.desatMomentumRef);
break;
case 0x7:
parameterWrapper->set(nadirModeControllerParameters.desatOn);
parameterWrapper->set(nadirModeControllerParameters.deSatGainFactor);
break;
case 0x8:
parameterWrapper->set(nadirModeControllerParameters.enableAntiStiction);
parameterWrapper->set(nadirModeControllerParameters.desatOn);
break;
case 0x9:
parameterWrapper->setVector(nadirModeControllerParameters.refDirection);
parameterWrapper->set(nadirModeControllerParameters.enableAntiStiction);
break;
case 0xA:
parameterWrapper->setVector(nadirModeControllerParameters.quatRef);
parameterWrapper->setVector(nadirModeControllerParameters.refDirection);
break;
case 0xB:
parameterWrapper->setVector(nadirModeControllerParameters.refRotRate);
parameterWrapper->setVector(nadirModeControllerParameters.quatRef);
break;
case 0xC:
parameterWrapper->setVector(nadirModeControllerParameters.refRotRate);
break;
case 0xD:
parameterWrapper->set(nadirModeControllerParameters.timeElapsedMax);
break;
default:
@ -570,21 +582,24 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->set(inertialModeControllerParameters.gainNullspace);
break;
case 0x5:
parameterWrapper->setVector(inertialModeControllerParameters.desatMomentumRef);
parameterWrapper->set(inertialModeControllerParameters.nullspaceSpeed);
break;
case 0x6:
parameterWrapper->set(inertialModeControllerParameters.deSatGainFactor);
parameterWrapper->setVector(inertialModeControllerParameters.desatMomentumRef);
break;
case 0x7:
parameterWrapper->set(inertialModeControllerParameters.desatOn);
parameterWrapper->set(inertialModeControllerParameters.deSatGainFactor);
break;
case 0x8:
parameterWrapper->set(inertialModeControllerParameters.enableAntiStiction);
parameterWrapper->set(inertialModeControllerParameters.desatOn);
break;
case 0x9:
parameterWrapper->setVector(inertialModeControllerParameters.tgtQuat);
parameterWrapper->set(inertialModeControllerParameters.enableAntiStiction);
break;
case 0xA:
parameterWrapper->setVector(inertialModeControllerParameters.tgtQuat);
break;
case 0xB:
parameterWrapper->setVector(inertialModeControllerParameters.refRotRate);
break;
case 0xC:
@ -696,7 +711,7 @@ ReturnValue_t AcsParameters::getParameter(uint8_t domainId, uint8_t parameterId,
parameterWrapper->setMatrix(magnetorquerParameter.inverseAlignment);
break;
case 0x5:
parameterWrapper->set(magnetorquerParameter.dipolMax);
parameterWrapper->set(magnetorquerParameter.dipoleMax);
break;
case 0x6:
parameterWrapper->set(magnetorquerParameter.torqueDuration);

6
mission/controller/acs/AcsParameters.h
View File

@ -816,7 +816,7 @@ class AcsParameters : public HasParametersIF {
{1.0864, 0, 0}, {-0.5432, -0.5432, 1.2797}, {0, 0, 0}, {-0.5432, 0.5432, 1.2797}};
double without4[4][3] = {
{0.5432, 0.5432, 1.2797}, {0, -1.0864, 0}, {-0.5432, 0.5432, 1.2797}, {0, 0, 0}};
double nullspace[4] = {-0.5000, 0.5000, -0.5000, 0.5000};
double nullspaceVector[4] = {-1, 1, -1, 1};
} rwMatrices;
struct SafeModeControllerParameters {
@ -840,7 +840,9 @@ class AcsParameters : public HasParametersIF {
double om = 0.3;
double omMax = 1 * M_PI / 180;
double qiMin = 0.1;
double gainNullspace = 0.01;
double nullspaceSpeed = 32500; // 0.1 RPM
double desatMomentumRef[3] = {0, 0, 0};
double deSatGainFactor = 1000;
@ -933,7 +935,7 @@ class AcsParameters : public HasParametersIF {
double mtq2orientationMatrix[3][3] = {{0, 0, 1}, {0, 1, 0}, {-1, 0, 0}};
double alignmentMatrixMtq[3][3] = {{0, 0, -1}, {-1, 0, 0}, {0, 1, 0}};
double inverseAlignment[3][3] = {{0, -1, 0}, {0, 0, 1}, {-1, 0, 0}};
double dipolMax = 0.2; // [Am^2]
double dipoleMax = 0.2; // [Am^2]
uint16_t torqueDuration = 300; // [ms]
} magnetorquerParameter;

64
mission/controller/acs/ActuatorCmd.cpp
View File

@ -5,11 +5,6 @@
#include <fsfw/globalfunctions/math/QuaternionOperations.h>
#include <fsfw/globalfunctions/math/VectorOperations.h>
#include <cmath>
#include "util/CholeskyDecomposition.h"
#include "util/MathOperations.h"
ActuatorCmd::ActuatorCmd() {}
ActuatorCmd::~ActuatorCmd() {}
@ -25,24 +20,30 @@ void ActuatorCmd::scalingTorqueRws(double *rwTrq, double maxTorque) {
}
}
void ActuatorCmd::cmdSpeedToRws(int32_t speedRw0, int32_t speedRw1, int32_t speedRw2,
int32_t speedRw3, const double *rwTorque, int32_t *rwCmdSpeed,
double sampleTime, int32_t maxRwSpeed, double inertiaWheel) {
using namespace Math;
// Calculating the commanded speed in RPM for every reaction wheel
void ActuatorCmd::cmdSpeedToRws(const int32_t speedRw0, const int32_t speedRw1,
const int32_t speedRw2, const int32_t speedRw3,
const double sampleTime, const double inertiaWheel,
const int32_t maxRwSpeed, const double *rwTorque,
int32_t *rwCmdSpeed) {
// group RW speed values (in 0.1 [RPM]) in vector
int32_t speedRws[4] = {speedRw0, speedRw1, speedRw2, speedRw3};
// calculate required RW speed as sum of current RW speed and RW speed delta
// delta w_rw = delta t / I_RW * torque_RW [rad/s]
double deltaSpeed[4] = {0, 0, 0, 0};
double radToRpm = 60 / (2 * PI); // factor for conversion to RPM
// W_RW = Torque_RW / I_RW * delta t [rad/s]
double factor = sampleTime / inertiaWheel * radToRpm;
int32_t deltaSpeedInt[4] = {0, 0, 0, 0};
const double factor = sampleTime / inertiaWheel * RAD_PER_SEC_TO_RPM * 10;
VectorOperations<double>::mulScalar(rwTorque, factor, deltaSpeed, 4);
// convert double to int32
int32_t deltaSpeedInt[4] = {0, 0, 0, 0};
for (int i = 0; i < 4; i++) {
deltaSpeedInt[i] = std::round(deltaSpeed[i]);
}
// sum of current RW speed and RW speed delta
VectorOperations<int32_t>::add(speedRws, deltaSpeedInt, rwCmdSpeed, 4);
VectorOperations<int32_t>::mulScalar(rwCmdSpeed, 10, rwCmdSpeed, 4);
// crop values which would exceed the maximum possible RPM
for (uint8_t i = 0; i < 4; i++) {
if (rwCmdSpeed[i] > maxRwSpeed) {
rwCmdSpeed[i] = maxRwSpeed;
@ -52,24 +53,25 @@ void ActuatorCmd::cmdSpeedToRws(int32_t speedRw0, int32_t speedRw1, int32_t spee
}
}
void ActuatorCmd::cmdDipolMtq(const double *dipolMoment, int16_t *dipolMomentActuator,
const double *inverseAlignment, double maxDipol) {
// Convert to actuator frame
double dipolMomentActuatorDouble[3] = {0, 0, 0};
MatrixOperations<double>::multiply(inverseAlignment, dipolMoment, dipolMomentActuatorDouble, 3, 3,
1);
// Scaling along largest element if dipol exceeds maximum
void ActuatorCmd::cmdDipoleMtq(const double *inverseAlignment, const double maxDipole,
const double *dipoleMoment, int16_t *dipoleMomentActuator) {
// convert to actuator frame
double dipoleMomentActuatorDouble[3] = {0, 0, 0};
MatrixOperations<double>::multiply(inverseAlignment, dipoleMoment, dipoleMomentActuatorDouble, 3,
3, 1);
// scaling along largest element if dipole exceeds maximum
uint8_t maxIdx = 0;
VectorOperations<double>::maxAbsValue(dipolMomentActuatorDouble, 3, &maxIdx);
double maxAbsValue = std::abs(dipolMomentActuatorDouble[maxIdx]);
if (maxAbsValue > maxDipol) {
double scalingFactor = maxDipol / maxAbsValue;
VectorOperations<double>::mulScalar(dipolMomentActuatorDouble, scalingFactor,
dipolMomentActuatorDouble, 3);
VectorOperations<double>::maxAbsValue(dipoleMomentActuatorDouble, 3, &maxIdx);
double maxAbsValue = std::abs(dipoleMomentActuatorDouble[maxIdx]);
if (maxAbsValue > maxDipole) {
double scalingFactor = maxDipole / maxAbsValue;
VectorOperations<double>::mulScalar(dipoleMomentActuatorDouble, scalingFactor,
dipoleMomentActuatorDouble, 3);
}
// scale dipole from 1 Am^2 to 1e^-4 Am^2
VectorOperations<double>::mulScalar(dipolMomentActuatorDouble, 1e4, dipolMomentActuatorDouble, 3);
VectorOperations<double>::mulScalar(dipoleMomentActuatorDouble, 1e4, dipoleMomentActuatorDouble,
3);
for (int i = 0; i < 3; i++) {
dipolMomentActuator[i] = std::round(dipolMomentActuatorDouble[i]);
dipoleMomentActuator[i] = std::round(dipoleMomentActuatorDouble[i]);
}
}

32
mission/controller/acs/ActuatorCmd.h
View File

@ -1,9 +1,8 @@
#ifndef ACTUATORCMD_H_
#define ACTUATORCMD_H_
#include "MultiplicativeKalmanFilter.h"
#include "SensorProcessing.h"
#include "SensorValues.h"
#include <cmath>
class ActuatorCmd {
public:
@ -19,29 +18,30 @@ class ActuatorCmd {
void scalingTorqueRws(double *rwTrq, double maxTorque);
/*
* @brief: cmdSpeedToRws() will set the maximum possible torque for the reaction
* wheels, also will calculate the needed revolutions per minute for the RWs, which will be given
* as Input to the RWs
* @param: rwTrqIn given torque from pointing controller
* rwTrqNS Nullspace torque
* @brief: cmdSpeedToRws() Calculates the RPM for the reaction wheel configuration,
* given the required torque calculated by the controller. Will also scale down the RPM of the
* wheels if they exceed the maximum possible RPM
* @param: rwTrq given torque from pointing controller
* rwCmdSpeed output revolutions per minute for every
* reaction wheel
*/
void cmdSpeedToRws(int32_t speedRw0, int32_t speedRw1, int32_t speedRw2, int32_t speedRw3,
const double *rwTorque, int32_t *rwCmdSpeed, double sampleTime,
int32_t maxRwSpeed, double inertiaWheel);
void cmdSpeedToRws(const int32_t speedRw0, const int32_t speedRw1, const int32_t speedRw2,
const int32_t speedRw3, const double sampleTime, const double inertiaWheel,
const int32_t maxRwSpeed, const double *rwTorque, int32_t *rwCmdSpeed);
/*
* @brief: cmdDipolMtq() gives the commanded dipol moment for the magnetorques
* @brief: cmdDipoleMtq() gives the commanded dipole moment for the
* magnetorquer
*
* @param: dipolMoment given dipol moment in spacecraft frame
* dipolMomentActuator resulting dipol moment in actuator reference frame
* @param: dipoleMoment given dipole moment in spacecraft frame
* dipoleMomentActuator resulting dipole moment in actuator reference frame
*/
void cmdDipolMtq(const double *dipolMoment, int16_t *dipolMomentActuator,
const double *inverseAlignment, double maxDipol);
void cmdDipoleMtq(const double *inverseAlignment, const double maxDipole,
const double *dipoleMoment, int16_t *dipoleMomentActuator);
protected:
private:
static constexpr double RAD_PER_SEC_TO_RPM = 60 / (2 * M_PI);
};
#endif /* ACTUATORCMD_H_ */

63
mission/controller/acs/Guidance.cpp
View File

@ -266,7 +266,8 @@ void Guidance::targetQuatPtgGs(timeval now, double posSatE[3], double sunDirI[3]
targetRotationRate(timeElapsedMax, now, targetQuat, targetSatRotRate);
}
void Guidance::targetQuatPtgSun(double sunDirI[3], double targetQuat[4], double refSatRate[3]) {
void Guidance::targetQuatPtgSun(timeval now, double sunDirI[3], double targetQuat[4],
double targetSatRotRate[3]) {
//-------------------------------------------------------------------------------------
// Calculation of target quaternion to sun
//-------------------------------------------------------------------------------------
@ -296,9 +297,8 @@ void Guidance::targetQuatPtgSun(double sunDirI[3], double targetQuat[4], double
//----------------------------------------------------------------------------
// Calculation of reference rotation rate
//----------------------------------------------------------------------------
refSatRate[0] = 0;
refSatRate[1] = 0;
refSatRate[2] = 0;
int8_t timeElapsedMax = acsParameters->gsTargetModeControllerParameters.timeElapsedMax;
targetRotationRate(timeElapsedMax, now, targetQuat, targetSatRotRate);
}
void Guidance::targetQuatPtgNadirSingleAxis(timeval now, double posSatE[3], double quatBI[4],
@ -412,7 +412,7 @@ void Guidance::targetQuatPtgNadirThreeAxes(timeval now, double posSatE[3], doubl
void Guidance::comparePtg(double currentQuat[4], double currentSatRotRate[3], double targetQuat[4],
double targetSatRotRate[3], double refQuat[4], double refSatRotRate[3],
double errorQuat[4], double errorSatRotRate[3], double errorAngle) {
double errorQuat[4], double errorSatRotRate[3], double &errorAngle) {
// First calculate error quaternion between current and target orientation
QuaternionOperations::multiply(currentQuat, targetQuat, errorQuat);
// Last calculate add rotation from reference quaternion
@ -424,26 +424,17 @@ void Guidance::comparePtg(double currentQuat[4], double currentSatRotRate[3], do
// Calculate error angle
errorAngle = QuaternionOperations::getAngle(errorQuat, true);
// Only give back error satellite rotational rate if orientation has already been aquired
if (errorAngle < 2. / 180. * M_PI) {
// Calculate error satellite rotational rate
// First combine the target and reference satellite rotational rates
double combinedRefSatRotRate[3] = {0, 0, 0};
VectorOperations<double>::add(targetSatRotRate, refSatRotRate, combinedRefSatRotRate, 3);
// Then substract the combined required satellite rotational rates from the actual rate
VectorOperations<double>::subtract(currentSatRotRate, combinedRefSatRotRate, errorSatRotRate,
3);
} else {
// If orientation has not been aquired yet set satellite rotational rate to zero
errorSatRotRate = 0;
}
// target flag in matlab, importance, does look like it only gives feedback if pointing control is
// under 150 arcsec ??
// Then subtract the combined required satellite rotational rates from the actual rate
VectorOperations<double>::subtract(currentSatRotRate, combinedRefSatRotRate, errorSatRotRate, 3);
}
void Guidance::comparePtg(double currentQuat[4], double currentSatRotRate[3], double targetQuat[4],
double targetSatRotRate[3], double errorQuat[4],
double errorSatRotRate[3], double errorAngle) {
double errorSatRotRate[3], double &errorAngle) {
// First calculate error quaternion between current and target orientation
QuaternionOperations::multiply(currentQuat, targetQuat, errorQuat);
// Keep scalar part of quaternion positive
@ -453,17 +444,8 @@ void Guidance::comparePtg(double currentQuat[4], double currentSatRotRate[3], do
// Calculate error angle
errorAngle = QuaternionOperations::getAngle(errorQuat, true);
// Only give back error satellite rotational rate if orientation has already been aquired
if (errorAngle < 2. / 180. * M_PI) {
// Then substract the combined required satellite rotational rates from the actual rate
// Calculate error satellite rotational rate
VectorOperations<double>::subtract(currentSatRotRate, targetSatRotRate, errorSatRotRate, 3);
} else {
// If orientation has not been aquired yet set satellite rotational rate to zero
errorSatRotRate = 0;
}
// target flag in matlab, importance, does look like it only gives feedback if pointing control is
// under 150 arcsec ??
}
void Guidance::targetRotationRate(int8_t timeElapsedMax, timeval now, double quatInertialTarget[4],
@ -471,20 +453,25 @@ void Guidance::targetRotationRate(int8_t timeElapsedMax, timeval now, double qua
//-------------------------------------------------------------------------------------
// Calculation of target rotation rate
//-------------------------------------------------------------------------------------
double timeElapsed = now.tv_sec + now.tv_usec * pow(10, -6) -
(timeSavedQuaternion.tv_sec +
timeSavedQuaternion.tv_usec * pow((double)timeSavedQuaternion.tv_usec, -6));
double timeElapsed = now.tv_sec + now.tv_usec * 1e-6 -
(timeSavedQuaternion.tv_sec + timeSavedQuaternion.tv_usec * 1e-6);
if (VectorOperations<double>::norm(savedQuaternion, 4) == 0) {
std::memcpy(savedQuaternion, quatInertialTarget, sizeof(savedQuaternion));
}
if (timeElapsed < timeElapsedMax) {
double q[4] = {0, 0, 0, 0}, qS[4] = {0, 0, 0, 0};
QuaternionOperations::inverse(quatInertialTarget, q);
QuaternionOperations::inverse(savedQuaternion, qS);
double qDiff[4] = {0, 0, 0, 0};
VectorOperations<double>::subtract(quatInertialTarget, savedQuaternion, qDiff, 4);
VectorOperations<double>::subtract(q, qS, qDiff, 4);
VectorOperations<double>::mulScalar(qDiff, 1 / timeElapsed, qDiff, 4);
double tgtQuatVec[3] = {quatInertialTarget[0], quatInertialTarget[1], quatInertialTarget[2]},
qDiffVec[3] = {qDiff[0], qDiff[1], qDiff[2]};
double tgtQuatVec[3] = {q[0], q[1], q[2]};
double qDiffVec[3] = {qDiff[0], qDiff[1], qDiff[2]};
double sum1[3] = {0, 0, 0}, sum2[3] = {0, 0, 0}, sum3[3] = {0, 0, 0}, sum[3] = {0, 0, 0};
VectorOperations<double>::cross(quatInertialTarget, qDiff, sum1);
VectorOperations<double>::cross(tgtQuatVec, qDiffVec, sum1);
VectorOperations<double>::mulScalar(tgtQuatVec, qDiff[3], sum2, 3);
VectorOperations<double>::mulScalar(qDiffVec, quatInertialTarget[3], sum3, 3);
VectorOperations<double>::mulScalar(qDiffVec, q[3], sum3, 3);
VectorOperations<double>::add(sum1, sum2, sum, 3);
VectorOperations<double>::subtract(sum, sum3, sum, 3);
double omegaRefNew[3] = {0, 0, 0};
@ -531,10 +518,6 @@ ReturnValue_t Guidance::getDistributionMatrixRw(ACS::SensorValues *sensorValues,
std::memcpy(rwPseudoInv, acsParameters->rwMatrices.without4, 12 * sizeof(double));
return returnvalue::OK;
} else {
// @note: This one takes the normal pseudoInverse of all four raction wheels valid.
// Does not make sense, but is implemented that way in MATLAB ?!
// Thought: It does not really play a role, because in case there are more then one
// reaction wheel invalid the pointing control is destined to fail.
return returnvalue::FAILED;
}
}

11
mission/controller/acs/Guidance.h
View File

@ -15,7 +15,7 @@ class Guidance {
void getTargetParamsSafe(double sunTargetSafe[3]);
ReturnValue_t solarArrayDeploymentComplete();
// Function to get the target quaternion and refence rotation rate from gps position and
// Function to get the target quaternion and reference rotation rate from gps position and
// position of the ground station
void targetQuatPtgSingleAxis(timeval now, double posSatE[3], double velSatE[3], double sunDirI[3],
double refDirB[3], double quatBI[4], double targetQuat[4],
@ -25,9 +25,10 @@ class Guidance {
void targetQuatPtgGs(timeval now, double posSatE[3], double sunDirI[3], double quatIX[4],
double targetSatRotRate[3]);
// Function to get the target quaternion and refence rotation rate for sun pointing after ground
// Function to get the target quaternion and reference rotation rate for sun pointing after ground
// station
void targetQuatPtgSun(double sunDirI[3], double targetQuat[4], double refSatRate[3]);
void targetQuatPtgSun(timeval now, double sunDirI[3], double targetQuat[4],
double targetSatRotRate[3]);
// Function to get the target quaternion and refence rotation rate from gps position for Nadir
// pointing
@ -42,10 +43,10 @@ class Guidance {
// rate. Lastly gives back the error angle of the error quaternion.
void comparePtg(double currentQuat[4], double currentSatRotRate[3], double targetQuat[4],
double targetSatRotRate[3], double refQuat[4], double refSatRotRate[3],
double errorQuat[4], double errorSatRotRate[3], double errorAngle);
double errorQuat[4], double errorSatRotRate[3], double &errorAngle);
void comparePtg(double currentQuat[4], double currentSatRotRate[3], double targetQuat[4],
double targetSatRotRate[3], double errorQuat[4], double errorSatRotRate[3],
double errorAngle);
double &errorAngle);
void targetRotationRate(int8_t timeElapsedMax, timeval now, double quatInertialTarget[4],
double *targetSatRotRate);

6
mission/controller/acs/control/Detumble.cpp
View File

@ -7,8 +7,10 @@ Detumble::Detumble() {}
Detumble::~Detumble() {}
uint8_t Detumble::detumbleStrategy(const bool magFieldValid, const bool satRotRateValid,
const bool magFieldRateValid, const bool useFullDetumbleLaw) {
acs::SafeModeStrategy Detumble::detumbleStrategy(const bool magFieldValid,
const bool satRotRateValid,
const bool magFieldRateValid,
const bool useFullDetumbleLaw) {
if (not magFieldValid) {
return acs::SafeModeStrategy::SAFECTRL_NO_MAG_FIELD_FOR_CONTROL;
} else if (satRotRateValid and useFullDetumbleLaw) {

5
mission/controller/acs/control/Detumble.h
View File

@ -11,8 +11,9 @@ class Detumble {
Detumble();
virtual ~Detumble();
uint8_t detumbleStrategy(const bool magFieldValid, const bool satRotRateValid,
const bool magFieldRateValid, const bool useFullDetumbleLaw);
acs::SafeModeStrategy detumbleStrategy(const bool magFieldValid, const bool satRotRateValid,
const bool magFieldRateValid,
const bool useFullDetumbleLaw);
void bDotLawFull(const double *satRotRateB, const double *magFieldB, double *magMomB,
double gain);

151
mission/controller/acs/control/PtgCtrl.cpp
View File

@ -5,9 +5,6 @@
#include <fsfw/globalfunctions/math/QuaternionOperations.h>
#include <fsfw/globalfunctions/math/VectorOperations.h>
#include <fsfw/globalfunctions/sign.h>
#include <math.h>
#include "../util/MathOperations.h"
PtgCtrl::PtgCtrl(AcsParameters *acsParameters_) { acsParameters = acsParameters_; }
@ -32,12 +29,13 @@ void PtgCtrl::ptgLaw(AcsParameters::PointingLawParameters *pointingLawParameters
double qErrorLaw[3] = {0, 0, 0};
for (int i = 0; i < 3; i++) {
if (abs(qError[i]) < qErrorMin) {
if (std::abs(qError[i]) < qErrorMin) {
qErrorLaw[i] = qErrorMin;
} else {
qErrorLaw[i] = abs(qError[i]);
qErrorLaw[i] = std::abs(qError[i]);
}
}
double qErrorLawNorm = VectorOperations<double>::norm(qErrorLaw, 3);
double gain1 = cInt * omMax / qErrorLawNorm;
@ -73,7 +71,7 @@ void PtgCtrl::ptgLaw(AcsParameters::PointingLawParameters *pointingLawParameters
double pErrorSign[3] = {0, 0, 0};
for (int i = 0; i < 3; i++) {
if (abs(pError[i]) > 1) {
if (std::abs(pError[i]) > 1) {
pErrorSign[i] = sign(pError[i]);
} else {
pErrorSign[i] = pError[i];
@ -98,61 +96,92 @@ void PtgCtrl::ptgLaw(AcsParameters::PointingLawParameters *pointingLawParameters
VectorOperations<double>::mulScalar(torqueRws, -1, torqueRws, 4);
}
void PtgCtrl::ptgNullspace(AcsParameters::PointingLawParameters *pointingLawParameters,
const int32_t speedRw0, const int32_t speedRw1, const int32_t speedRw2,
const int32_t speedRw3, double *rwTrqNs) {
// concentrate RW speeds as vector and convert to double
double speedRws[4] = {static_cast<double>(speedRw0), static_cast<double>(speedRw1),
static_cast<double>(speedRw2), static_cast<double>(speedRw3)};
VectorOperations<double>::mulScalar(speedRws, 1e-1, speedRws, 4);
VectorOperations<double>::mulScalar(speedRws, RPM_TO_RAD_PER_SEC, speedRws, 4);
// calculate RPM offset utilizing the nullspace
double rpmOffset[4] = {0, 0, 0, 0};
double rpmOffsetSpeed = pointingLawParameters->nullspaceSpeed / 10 * RPM_TO_RAD_PER_SEC;
VectorOperations<double>::mulScalar(acsParameters->rwMatrices.nullspaceVector, rpmOffsetSpeed,
rpmOffset, 4);
// calculate resulting angular momentum
double rwAngMomentum[4] = {0, 0, 0, 0}, diffRwSpeed[4] = {0, 0, 0, 0};
VectorOperations<double>::subtract(speedRws, rpmOffset, diffRwSpeed, 4);
VectorOperations<double>::mulScalar(diffRwSpeed, acsParameters->rwHandlingParameters.inertiaWheel,
rwAngMomentum, 4);
// calculate resulting torque
double nullspaceMatrix[4][4] = {{0, 0, 0}, {0, 0, 0}, {0, 0, 0}, {0, 0, 0}};
MatrixOperations<double>::multiply(acsParameters->rwMatrices.nullspaceVector,
acsParameters->rwMatrices.nullspaceVector, *nullspaceMatrix, 4,
1, 4);
MatrixOperations<double>::multiply(*nullspaceMatrix, rwAngMomentum, rwTrqNs, 4, 4, 1);
VectorOperations<double>::mulScalar(rwTrqNs, -1 * pointingLawParameters->gainNullspace, rwTrqNs,
4);
}
void PtgCtrl::ptgDesaturation(AcsParameters::PointingLawParameters *pointingLawParameters,
double *magFieldEst, bool magFieldEstValid, double *satRate,
int32_t *speedRw0, int32_t *speedRw1, int32_t *speedRw2,
int32_t *speedRw3, double *mgtDpDes) {
if (!(magFieldEstValid) || !(pointingLawParameters->desatOn)) {
mgtDpDes[0] = 0;
mgtDpDes[1] = 0;
mgtDpDes[2] = 0;
const double *magFieldB, const bool magFieldBValid,
const double *satRate, const int32_t speedRw0, const int32_t speedRw1,
const int32_t speedRw2, const int32_t speedRw3, double *mgtDpDes) {
if (not magFieldBValid or not pointingLawParameters->desatOn) {
return;
}
// calculating momentum of satellite and momentum of reaction wheels
double speedRws[4] = {(double)*speedRw0, (double)*speedRw1, (double)*speedRw2, (double)*speedRw3};
double momentumRwU[4] = {0, 0, 0, 0}, momentumRw[3] = {0, 0, 0};
VectorOperations<double>::mulScalar(speedRws, acsParameters->rwHandlingParameters.inertiaWheel,
momentumRwU, 4);
MatrixOperations<double>::multiply(*(acsParameters->rwMatrices.alignmentMatrix), momentumRwU,
momentumRw, 3, 4, 1);
double momentumSat[3] = {0, 0, 0}, momentumTotal[3] = {0, 0, 0};
MatrixOperations<double>::multiply(*(acsParameters->inertiaEIVE.inertiaMatrixDeployed), satRate,
momentumSat, 3, 3, 1);
VectorOperations<double>::add(momentumSat, momentumRw, momentumTotal, 3);
// calculating momentum error
double deltaMomentum[3] = {0, 0, 0};
VectorOperations<double>::subtract(momentumTotal, pointingLawParameters->desatMomentumRef,
deltaMomentum, 3);
// resulting magnetic dipole command
double crossMomentumMagField[3] = {0, 0, 0};
VectorOperations<double>::cross(deltaMomentum, magFieldEst, crossMomentumMagField);
double normMag = VectorOperations<double>::norm(magFieldEst, 3), factor = 0;
factor = (pointingLawParameters->deSatGainFactor) / normMag;
VectorOperations<double>::mulScalar(crossMomentumMagField, factor, mgtDpDes, 3);
}
// concentrate RW speeds as vector and convert to double
double speedRws[4] = {static_cast<double>(speedRw0), static_cast<double>(speedRw1),
static_cast<double>(speedRw2), static_cast<double>(speedRw3)};
void PtgCtrl::ptgNullspace(AcsParameters::PointingLawParameters *pointingLawParameters,
const int32_t *speedRw0, const int32_t *speedRw1,
const int32_t *speedRw2, const int32_t *speedRw3, double *rwTrqNs) {
double speedRws[4] = {(double)*speedRw0, (double)*speedRw1, (double)*speedRw2, (double)*speedRw3};
double wheelMomentum[4] = {0, 0, 0, 0};
double rpmOffset[4] = {1, 1, 1, -1}, factor = 350 * 2 * Math::PI / 60;
// conversion to [rad/s] for further calculations
VectorOperations<double>::mulScalar(rpmOffset, factor, rpmOffset, 4);
VectorOperations<double>::mulScalar(speedRws, 2 * Math::PI / 60, speedRws, 4);
double diffRwSpeed[4] = {0, 0, 0, 0};
VectorOperations<double>::subtract(speedRws, rpmOffset, diffRwSpeed, 4);
VectorOperations<double>::mulScalar(diffRwSpeed, acsParameters->rwHandlingParameters.inertiaWheel,
wheelMomentum, 4);
double gainNs = pointingLawParameters->gainNullspace;
double nullSpaceMatrix[4][4] = {{0, 0, 0}, {0, 0, 0}, {0, 0, 0}, {0, 0, 0}};
MathOperations<double>::vecTransposeVecMatrix(acsParameters->rwMatrices.nullspace,
acsParameters->rwMatrices.nullspace,
*nullSpaceMatrix, 4);
MatrixOperations<double>::multiply(*nullSpaceMatrix, wheelMomentum, rwTrqNs, 4, 4, 1);
VectorOperations<double>::mulScalar(rwTrqNs, gainNs, rwTrqNs, 4);
VectorOperations<double>::mulScalar(rwTrqNs, -1, rwTrqNs, 4);
// convert magFieldB from uT to T
double magFieldBT[3] = {0, 0, 0};
VectorOperations<double>::mulScalar(magFieldB, 1e-6, magFieldBT, 3);
// calculate angular momentum of the satellite
double angMomentumSat[3] = {0, 0, 0};
MatrixOperations<double>::multiply(*(acsParameters->inertiaEIVE.inertiaMatrixDeployed), satRate,
angMomentumSat, 3, 3, 1);
// calculate angular momentum of the reaction wheels with respect to the nullspace RW speed
// relocate RW speed zero to nullspace RW speed
double refSpeedRws[4] = {0, 0, 0, 0};
VectorOperations<double>::mulScalar(acsParameters->rwMatrices.nullspaceVector,
pointingLawParameters->nullspaceSpeed, refSpeedRws, 4);
VectorOperations<double>::subtract(speedRws, refSpeedRws, speedRws, 4);
// convert speed from 10 RPM to 1 RPM
VectorOperations<double>::mulScalar(speedRws, 1e-1, speedRws, 4);
// convert to rad/s
VectorOperations<double>::mulScalar(speedRws, RPM_TO_RAD_PER_SEC, speedRws, 4);
// calculate angular momentum of each RW
double angMomentumRwU[4] = {0, 0, 0, 0};
VectorOperations<double>::mulScalar(speedRws, acsParameters->rwHandlingParameters.inertiaWheel,
angMomentumRwU, 4);
// convert RW angular momentum to body RF
double angMomentumRw[3] = {0, 0, 0};
MatrixOperations<double>::multiply(*(acsParameters->rwMatrices.alignmentMatrix), angMomentumRwU,
angMomentumRw, 3, 4, 1);
// calculate total angular momentum
double angMomentumTotal[3] = {0, 0, 0};
VectorOperations<double>::add(angMomentumSat, angMomentumRw, angMomentumTotal, 3);
// calculating momentum error
double deltaAngMomentum[3] = {0, 0, 0};
VectorOperations<double>::subtract(angMomentumTotal, pointingLawParameters->desatMomentumRef,
deltaAngMomentum, 3);
// resulting magnetic dipole command
double crossAngMomentumMagField[3] = {0, 0, 0};
VectorOperations<double>::cross(deltaAngMomentum, magFieldBT, crossAngMomentumMagField);
double factor =
pointingLawParameters->deSatGainFactor / VectorOperations<double>::norm(magFieldBT, 3);
VectorOperations<double>::mulScalar(crossAngMomentumMagField, factor, mgtDpDes, 3);
}
void PtgCtrl::rwAntistiction(ACS::SensorValues *sensorValues, int32_t *rwCmdSpeeds) {
@ -169,15 +198,9 @@ void PtgCtrl::rwAntistiction(ACS::SensorValues *sensorValues, int32_t *rwCmdSpee
if (rwCmdSpeeds[i] != 0) {
if (rwCmdSpeeds[i] > -acsParameters->rwHandlingParameters.stictionSpeed &&
rwCmdSpeeds[i] < acsParameters->rwHandlingParameters.stictionSpeed) {
if (currRwSpeed[i] == 0) {
if (rwCmdSpeeds[i] > 0) {
if (rwCmdSpeeds[i] > currRwSpeed[i]) {
rwCmdSpeeds[i] = acsParameters->rwHandlingParameters.stictionSpeed;
} else if (rwCmdSpeeds[i] < 0) {
rwCmdSpeeds[i] = -acsParameters->rwHandlingParameters.stictionSpeed;
}
} else if (currRwSpeed[i] < -acsParameters->rwHandlingParameters.stictionSpeed) {
rwCmdSpeeds[i] = acsParameters->rwHandlingParameters.stictionSpeed;
} else if (currRwSpeed[i] > acsParameters->rwHandlingParameters.stictionSpeed) {
} else if (rwCmdSpeeds[i] < currRwSpeed[i]) {
rwCmdSpeeds[i] = -acsParameters->rwHandlingParameters.stictionSpeed;
}
}

24
mission/controller/acs/control/PtgCtrl.h
View File

@ -1,13 +1,10 @@
#ifndef PTGCTRL_H_
#define PTGCTRL_H_
#include <math.h>
#include <mission/controller/acs/AcsParameters.h>
#include <mission/controller/acs/SensorValues.h>
#include <stdio.h>
#include <string.h>
#include <time.h>
#include "../AcsParameters.h"
#include "../SensorValues.h"
#include "eive/resultClassIds.h"
class PtgCtrl {
/*
@ -29,14 +26,14 @@ class PtgCtrl {
void ptgLaw(AcsParameters::PointingLawParameters *pointingLawParameters, const double *qError,
const double *deltaRate, const double *rwPseudoInv, double *torqueRws);
void ptgDesaturation(AcsParameters::PointingLawParameters *pointingLawParameters,
double *magFieldEst, bool magFieldEstValid, double *satRate,
int32_t *speedRw0, int32_t *speedRw1, int32_t *speedRw2, int32_t *speedRw3,
double *mgtDpDes);
void ptgNullspace(AcsParameters::PointingLawParameters *pointingLawParameters,
const int32_t *speedRw0, const int32_t *speedRw1, const int32_t *speedRw2,
const int32_t *speedRw3, double *rwTrqNs);
const int32_t speedRw0, const int32_t speedRw1, const int32_t speedRw2,
const int32_t speedRw3, double *rwTrqNs);
void ptgDesaturation(AcsParameters::PointingLawParameters *pointingLawParameters,
const double *magFieldB, const bool magFieldBValid, const double *satRate,
const int32_t speedRw0, const int32_t speedRw1, const int32_t speedRw2,
const int32_t speedRw3, double *mgtDpDes);
/* @brief: Commands the stiction torque in case wheel speed is to low
* torqueCommand modified torque after antistiction
@ -45,6 +42,7 @@ class PtgCtrl {
private:
const AcsParameters *acsParameters;
static constexpr double RPM_TO_RAD_PER_SEC = (2 * M_PI) / 60;
};
#endif /* ACS_CONTROL_PTGCTRL_H_ */

5
mission/controller/acs/control/SafeCtrl.cpp
View File

@ -9,9 +9,10 @@ SafeCtrl::SafeCtrl(AcsParameters *acsParameters_) { acsParameters = acsParameter
SafeCtrl::~SafeCtrl() {}
uint8_t SafeCtrl::safeCtrlStrategy(const bool magFieldValid, const bool mekfValid,
acs::SafeModeStrategy SafeCtrl::safeCtrlStrategy(const bool magFieldValid, const bool mekfValid,
const bool satRotRateValid, const bool sunDirValid,
const uint8_t mekfEnabled, const uint8_t dampingEnabled) {
const uint8_t mekfEnabled,
const uint8_t dampingEnabled) {
if (not magFieldValid) {
return acs::SafeModeStrategy::SAFECTRL_NO_MAG_FIELD_FOR_CONTROL;
} else if (mekfEnabled and mekfValid) {

2
mission/controller/acs/control/SafeCtrl.h
View File

@ -12,7 +12,7 @@ class SafeCtrl {
SafeCtrl(AcsParameters *acsParameters_);
virtual ~SafeCtrl();
uint8_t safeCtrlStrategy(const bool magFieldValid, const bool mekfValid,
acs::SafeModeStrategy safeCtrlStrategy(const bool magFieldValid, const bool mekfValid,
const bool satRotRateValid, const bool sunDirValid,
const uint8_t mekfEnabled, const uint8_t dampingEnabled);