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Fix issues in mass exporting

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This commit is contained in:
SiboVG 2023-04-01 12:23:02 +02:00
parent 153bd9ebf9
commit 27a77825be
1 changed files with 42 additions and 14 deletions
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56
core/src/net/sf/openrocket/file/rasaero/export/SimulationDTO.java
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@ -7,6 +7,7 @@ import net.sf.openrocket.file.rasaero.RASAeroCommonConstants;
import net.sf.openrocket.logging.ErrorSet;
import net.sf.openrocket.logging.WarningSet;
import net.sf.openrocket.masscalc.MassCalculator;
import net.sf.openrocket.masscalc.RigidBody;
import net.sf.openrocket.motor.Motor;
import net.sf.openrocket.motor.MotorConfiguration;
import net.sf.openrocket.motor.ThrustCurveMotor;
@ -124,6 +125,17 @@ public class SimulationDTO {
return;
}
if (mounts.isEmpty()) {
warnings.add(String.format("No motors found in simulation '%s', ignoring.", simulation.getName()));
return;
}
// Get sustainer motor mass
MotorMount sustainerMount = mounts.get((AxialStage) rocket.getChild(0));
MotorConfiguration sustainerConfig = sustainerMount.getMotorConfig(fcid);
Motor sustainerMotor = sustainerConfig.getMotor();
double sustainerMotorMass = sustainerMotor != null ? sustainerMotor.getLaunchMass() : 0;
for (Map.Entry<AxialStage, MotorMount> mountSet : mounts.entrySet()) {
AxialStage stage = mountSet.getKey();
MotorMount mount = mountSet.getValue();
@ -131,7 +143,10 @@ public class SimulationDTO {
continue;
}
// Get the motor info for this stage
MotorConfiguration motorConfig = mount.getMotorConfig(fcid);
Motor motor = motorConfig.getMotor();
double motorMass = motor != null ? motor.getLaunchMass() : 0;
StageSeparationConfiguration separationConfig = stage.getSeparationConfigurations().get(fcid);
int stageNr = rocket.getChildPosition(stage);
@ -139,8 +154,9 @@ public class SimulationDTO {
switch (stageNr) {
// Sustainer
case 0:
setSustainerEngine(RASAeroCommonConstants.OPENROCKET_TO_RASAERO_MOTOR(motors, motorConfig.getMotor(), motorConfig, warnings));
setSustainerLaunchWt(stage.getSectionMass() * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_WEIGHT);
setSustainerEngine(RASAeroCommonConstants.OPENROCKET_TO_RASAERO_MOTOR(motors, motor, motorConfig, warnings));
double sustainerMass = stage.getSectionMass() + motorMass;
setSustainerLaunchWt(sustainerMass * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_WEIGHT);
// Calculate CG of sustainer
CGCalcConfig.setOnlyStage(0);
@ -151,18 +167,21 @@ public class SimulationDTO {
break;
// Booster 1
case 1:
setBooster1Engine(RASAeroCommonConstants.OPENROCKET_TO_RASAERO_MOTOR(motors, motorConfig.getMotor(), motorConfig, warnings));
// Aggregate mass of sustainer and booster 1
setBooster1LaunchWt(rocket.getChild(0).getSectionMass() + stage.getSectionMass()
* RASAeroCommonConstants.OPENROCKET_TO_RASAERO_WEIGHT);
setBooster1Engine(RASAeroCommonConstants.OPENROCKET_TO_RASAERO_MOTOR(motors, motor, motorConfig, warnings));
// Aggregate CG of sustainer and booster 1
CGCalcConfig.setOnlyStage(0);
for (int i = 1; i <= stage.getStageNumber(); i++) {
CGCalcConfig._setStageActive(i, true);
}
double totalCG = MassCalculator.calculateStructure(CGCalcConfig).getCM().x;
RigidBody calc = MassCalculator.calculateStructure(CGCalcConfig);
// Aggregate mass of sustainer and booster 1
double booster1Mass = calc.getMass() + motorMass + sustainerMotorMass;
setBooster1LaunchWt(booster1Mass * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_WEIGHT);
// CG
double totalCG = calc.getCM().x;
setBooster1CG(totalCG * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_LENGTH);
setBooster1IgnitionDelay(motorConfig.getIgnitionDelay());
@ -171,18 +190,27 @@ public class SimulationDTO {
break;
// Booster 2
case 2:
setBooster2Engine(RASAeroCommonConstants.OPENROCKET_TO_RASAERO_MOTOR(motors, motorConfig.getMotor(), motorConfig, warnings));
// Aggregate mass of sustainer, booster 1 and booster 2
setBooster2LaunchWt(rocket.getChild(0).getSectionMass() + rocket.getChild(1).getSectionMass() +
stage.getSectionMass() * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_WEIGHT);
setBooster2Engine(RASAeroCommonConstants.OPENROCKET_TO_RASAERO_MOTOR(motors, motor, motorConfig, warnings));
// Calculate the aggregated CG of the sustainer, booster and booster 2
CGCalcConfig.setOnlyStage(0);
for (int i = 1; i <= stage.getStageNumber(); i++) {
CGCalcConfig._setStageActive(i, true);
}
totalCG = MassCalculator.calculateStructure(CGCalcConfig).getCM().x;
calc = MassCalculator.calculateStructure(CGCalcConfig);
// Get booster1 motor mass
MotorMount booster1Mount = mounts.get((AxialStage) rocket.getChild(1));
MotorConfiguration booster1Config = booster1Mount.getMotorConfig(fcid);
Motor booster1Motor = booster1Config.getMotor();
double booster1MotorMass = booster1Motor != null ? booster1Motor.getLaunchMass() : 0;
// Aggregate mass of sustainer, booster 1 and booster 2
double booster2Mass = calc.getMass() + motorMass + sustainerMotorMass + booster1MotorMass;
setBooster2LaunchWt(booster2Mass * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_WEIGHT);
// CG
totalCG = calc.getCM().x;
setBooster2CG(totalCG * RASAeroCommonConstants.OPENROCKET_TO_RASAERO_LENGTH);
setBooster2Delay(separationConfig.getSeparationDelay()); // TODO: this could be handled a bit better (look at separation delay, upper stage ignition event etc.)