/**
* A first guess value of center of gravity location of the whole aircraft.
*
* @author Lorenzo Attanasio
* @param aircraft
*/
public void calculateBalance(Aircraft aircraft) {
_xCoGMeanAtOEM =
(aircraft.get_wing().get_X0().getEstimatedValue()
+ 0.25 * aircraft.get_wing().get_meanAerodChordActual().getEstimatedValue());
set_xCoGMaxAftAtOEM((_xCoGMeanAtOEM * (1 - 0.1)));
}
/**
* Evaluate center of gravity location of each component.
*
* @param aircraft
* @param conditions
* @param methodsMap
*/
public void calculateBalance(
Aircraft aircraft,
OperatingConditions conditions,
Map<ComponentEnum, List<MethodEnum>> methodsMap) {
aircraft.get_fuselage().calculateCG(aircraft, conditions);
aircraft.get_wing().calculateCG(aircraft, conditions);
aircraft.get_HTail().calculateCG(aircraft, conditions);
aircraft.get_VTail().calculateCG(aircraft, conditions);
aircraft.get_theNacelles().calculateCG();
aircraft.get_theFuelTank().calculateCG(aircraft, conditions);
aircraft.get_landingGear().calculateCG(aircraft, conditions);
// --- END OF STRUCTURE MASS-----------------------------------
aircraft.get_powerPlant().calculateCG();
calculateTotalCG(aircraft);
set_xCoGMeanAtOEM(
aircraft.get_wing().get_X0().getEstimatedValue()
+ 0.25 * aircraft.get_wing().get_meanAerodChordActual().getEstimatedValue());
set_xCoGMaxAftAtOEM(get_xCoGMeanAtOEM() * (1 - 0.1));
set_xCoGMaxForAtOEM(get_xCoGMeanAtOEM() * (1 + 0.1));
}
/**
* Evaluate overall CG
*
* @param aircraft
*/
public void calculateTotalCG(Aircraft aircraft) {
// Structural CG
_cgStructure = new CenterOfGravity();
_cgList.add(aircraft.get_fuselage().get_cg());
_cgList.add(aircraft.get_wing().get_cg());
_cgList.add(aircraft.get_HTail().get_cg());
_cgList.add(aircraft.get_VTail().get_cg());
_cgList.add(aircraft.get_landingGear().get_cg());
_cgList.addAll(aircraft.get_theNacelles().get_cgList());
System.out.println("\n \nCG COMPONENTS LOCATION IN BRF");
System.out.println("fuselage --> " + _cgList.get(0).get_xBRF());
System.out.println("wing --> " + _cgList.get(1).get_xBRF());
System.out.println("HTail --> " + _cgList.get(2).get_xBRF());
System.out.println("VTail --> " + _cgList.get(3).get_xBRF());
System.out.println("Landing gear --> " + _cgList.get(4).get_xBRF());
for (int i = 0; i < aircraft.get_theNacelles().get_cgList().size(); i++) {
System.out.println("Nacelle " + i + " --> " + _cgList.get(i + 5).get_xBRF());
}
// _cgList.forEach(p-> System.out.println(p.get_xBRF()));
double prod = 0., sum = 0.;
for (int i = 0; i < _cgList.size(); i++) {
prod +=
_cgList.get(i).get_xBRF().getEstimatedValue()
* aircraft.get_weights().get_massStructureList().get(i).getEstimatedValue();
sum += aircraft.get_weights().get_massStructureList().get(i).getEstimatedValue();
}
_cgStructure.set_xBRF(Amount.valueOf(prod / sum, SI.METER));
_cgStructure.calculateCGinMAC(
aircraft.get_wing().get_xLEMacActualBRF(),
aircraft.get_wing().get_xLEMacActualBRF(),
Amount.valueOf(0., SI.METER),
aircraft.get_wing().get_meanAerodChordActual());
// Structure + engines CG
_cgStructureAndPower = new CenterOfGravity();
System.out.println(
"fuel tank --> " + aircraft.get_theFuelTank().get_cg().get_xBRF().getEstimatedValue());
double cgPowerPlantContribute = 0.0;
for (int i = 0; i < aircraft.get_powerPlant().get_engineNumber(); i++) {
cgPowerPlantContribute =
cgPowerPlantContribute
+ (aircraft.get_powerPlant().get_cgList().get(i).get_xBRF().getEstimatedValue()
* aircraft
.get_powerPlant()
.get_engineList()
.get(i)
.get_totalMass()
.getEstimatedValue());
System.out.println(
"Engine " + i + " --> " + aircraft.get_powerPlant().get_cgList().get(i).get_xBRF());
}
_cgStructureAndPower.set_xBRF(
Amount.valueOf(
(cgPowerPlantContribute
+ aircraft.get_weights().get_structuralMass().getEstimatedValue()
* get_cgStructure().get_xBRF().getEstimatedValue())
/ (aircraft.get_weights().get_structuralMass().getEstimatedValue()
+ aircraft.get_powerPlant().get_totalMass().getEstimatedValue()),
SI.METER));
get_cgStructureAndPower()
.calculateCGinMAC(
aircraft.get_wing().get_xLEMacActualBRF(),
aircraft.get_wing().get_xLEMacActualBRF(),
Amount.valueOf(0., SI.METER),
aircraft.get_wing().get_meanAerodChordActual());
// MZFW CG location
_cgMZFM = new CenterOfGravity();
get_cgMZFM()
.set_xBRF(
Amount.valueOf(
(get_cgStructureAndPower().get_xBRF().getEstimatedValue()
* aircraft.get_weights().get_OEM().getEstimatedValue()
+ aircraft.get_configuration().get_seatsCoG().getEstimatedValue()
* aircraft.get_weights().get_paxMassMax().getEstimatedValue())
/ (aircraft.get_weights().get_paxMassMax().getEstimatedValue()
+ aircraft.get_weights().get_OEM().getEstimatedValue()),
SI.METER));
get_cgMZFM()
.calculateCGinMAC(
aircraft.get_wing().get_xLEMacActualBRF(),
aircraft.get_wing().get_xLEMacActualBRF(),
Amount.valueOf(0., SI.METER),
aircraft.get_wing().get_meanAerodChordActual());
// MTOM CG location
_cgMTOM = new CenterOfGravity();
_cgMTOM.set_xBRF(
Amount.valueOf(
(_cgMZFM.get_xBRF().getEstimatedValue()
* aircraft.get_weights().get_MZFM().getEstimatedValue()
+ aircraft.get_theFuelTank().get_fuelMass().getEstimatedValue()
* aircraft.get_theFuelTank().get_cg().get_xBRF().getEstimatedValue())
/ aircraft.get_weights().get_MTOM().getEstimatedValue(),
SI.METER));
_cgMTOM.calculateCGinMAC(
aircraft.get_wing().get_xLEMacActualBRF(),
aircraft.get_wing().get_xLEMacActualBRF(),
Amount.valueOf(0., SI.METER),
aircraft.get_wing().get_meanAerodChordActual());
}