洛克希德马丁+高空无人侦察机+机密资料+谨慎传阅.ppt

1、1,HARP-HighAltitudeReconnaissancePlatformDesignProposal,Dr.JamesD.Lang,ProjectAdvisorDr.LelandM.Nicolai,ProjectSponsorDr.PaulA.Wieselmann,ProjectSponsor,StevenH.ChristensonTeamLead,2,PresentationOverview,-DefineRequirements-DesignProcessandAssumptions-AircraftConfiguration/Sizing-WeightBreakdown-Mis

2、sionAnalysisandCompliance-Aerodynamics-Performance,-Propulsion-StabilityandControl-MaterialsandStructure-CostEstimations-FutureWork-ReferencesandAcknowledgements,3,Requirements,Provide24/7ISRCoveragewith2Aircraft2000nmRadiusforISRMission10500nmFerryFlight6963lbPayload(InstalledWeight)-(4)XBandRadarA

3、rrays3.3x6.1ft-(2)UHFRadarArrays4.9x40.6ftMinimizeTake-offWeightandLifeCycleCost,4,MissionEndurance2*(One-WayTransit)+TimeonStationTimeonStation2*(One-WayTransit)+TurnaroundTime,DerivedRequirementsfor24/7Coveragewith2Aircraft,5,ISRMission,DescendtoSeaLevel,ClimbtoCruiseAltitude,CruiseOut2000nm,Cruis

4、eBack2000nm,Loiter16Hours(TOS),SeaLevelLoiterfor30min,55000ft,Distance(nm),2000nm,6,MaxDistanceFerryMission,DescendtoSeaLevel,ClimbtoCruiseAltitude,Cruise10500nm,SeaLevelLoiterfor30min,55000ft,Distance(nm),10500nm,7,AssumeWtoandW/S,SizeWingCalculateComponentWeightsCalculateFuelFractions,Yes/No,Deter

5、mineFuelAvailable,Fuel)avalFuel)reqd,DetermineFuelRequiredforMission,AerodynamicsSizeEnginePerformance,AR,Taper,SweepFuselageSizingandShapeEstimateTailSize,StudyMissionRequirements,RefineWtoandW/SEstimates,RefineAerodynamicParametersSizeControlSurfaces/TailCalculateDragDeterminePerformanceCapabiliti

6、es,MissionRequirementsMet?,RefineWtoandW/SOptimizeDesign,-AssumptionsMade/Refined-,-ConfigurationAssumptionsMade/RefinedtoMeetMissionRequirements-,DesignProcess,Yes/No,8,AircraftConfiguration,-L/D)max,wing=35for0degSweep,20AR,60%LaminarFlowLockheedMartinAerodynamicData-2250lbThrust,.55TSFCfor2015Adv

7、ancedTechnologyTurbofanEngineatFullPowerand55000ft,DesignAnalysisBasedontheFollowingAssumptions:,9,AircraftConfiguration,Wto=50000lbW/S=60lb/ft2WingArea=833ft2WingSpan=129ftWingSweep=0degAspectRatio=20,10,RadarGeometry,XBandRadar(4)-3.3x6.1ft-AzimuthFieldofRegard(FOR)+/-70degrees-Locatedtogive360Deg

8、reeCoverageUHFRadar(2)-4.9x40.6ft-AzimuthFOR+/-70degrees-LocatedtoViewOutEachSide,11,HorizonDistance,DesignArrayAnglesforDesiredFootprint,12,AircraftConfiguration,WingArea=833ft2WingSpan=129ftWingSweep=0degAspectRatio=20,FuselageLength=62ftHeight=6ftWidth=10ft,13,AircraftConfiguration,14,AircraftCon

9、figuration,WingFuelTank,CenterofGravity&AerodynamicCenter,15,Startup/Take-Off.970ClimbtoCruiseAlt.950CruiseOut.902LoiteronStation.754LoiterFuel10219lbManeuveringFuel671lbCruiseBack.902DescendtoSL1.00Loiter20min.994,Take-OffWeight50000lbFuelWeight23874lbFuelFraction.48FuelVolume3511gal,WeightFraction

10、s-ISR,-Cruiseat.943*L/D)max-LoiteratL/D)max,(1)2015TechnologyTurbofanEngineSLSThrust=8000lbSLSTSFC=.40T/W=.16,16,-16HourTOS-Cl=.864L/D)max=31.52Mach.6and55000ft,ISRMissionCompliance,MissionEndurance2*(One-WayTransit)+TimeonStation=2*(5.52)+16.2hr=28.4hrTimeonStation2*(One-WayTransit)+TurnaroundTime=

11、12.2hr+4hr=16.2hr,-TwoAircraftCoverage-,-2000nmRange-Cl=.628L/D=29.72Mach.6and55000ft,TotalMissionFuelRequired:23874lb=3511gal,17,WeightFractions-Ferry,Startup/Take-Off.970ClimbtoCruiseAlt.950Cruise10500nm.567DescendtoSL1.00Loiter20min.994,Take-OffWeight50000lbFuelWeight24685lbFuelFraction.49FuelVol

12、ume3630gal,DesignPushedby10500nmFerryFlightApprox800lbAdditionalFuelRequired,18,Aerodynamics,AspectRatio=20Span=129ftWingSweep=0dege=.9t/c=.15K=.01768TaperRatio=.50MAC=6.7ftCroot=8.6ftCtip=4.3ftAirfoil:ModifiedLockheedMartinSensorcraftWing15%toProvide60%LaminarFlow,19,Aerodynamics,L/D)max,wing=35Loc

13、kheedMartinAerodynamicsDataCdo)wing=.00817ReferencedtoSrefCdo)fuselage=.00369ReferencedtoSrefCdo)tail=.00121ReferencedtoSrefCdo)aircraft=.01393CalculatedwithInterferenceEffectsL/D)max,aircraft=31.52FromL/DvsClPlot,20,Aerodynamics,Cl=.864forL/D)maxandMinimumDragClalpha=6.9rad-1=.12deg-1atMach.6StallV

14、elocityBasedonCl)maxof2.0CandidateHighLiftDevices-MissionAdaptiveWing(MAW)-TrailingEdgeFlaps,21,Aerodynamics,FuselageSizedtoHoldRadarArrays,Length=62ftDepth=6ftWidth=10ftFinenessRatio=6.2,Volume=2922ft3WettedArea=1067ft2MaxCrossSectionalArea=47ft2,22,Aerodynamics,L/D)max=31.52,23,Aerodynamics,24,Aer

15、odynamics,-InsufficientDatainReferencestoAccuratelyCalculateMDD-ConcernthatatCruiseVelocityandAltitude(M.655000ft)AirfoilisNearMDD-SupercriticalWing,MDD,DragDivergentMachNumber,25,Performance,LimitLoadFactor1.25UltimateLoadFactor1.88TurnLoadFactor1.15ManeuveringTurnRate1.8deg/sDynamicPresLimit450lb/

16、ft2,StallVelocity159ft/sTake-OffVelocity191ft/sTake-OffDistance5000ftLandingDistance4000ftBrakingAcceleration7ft/s2,26,Performance,27,Performance,28,Performance,29,Propulsion,2015TechnologyTurbofanEngineModerateBypassRatio8000lbThrust(SeaLevelStatic).40TSFC(SeaLevelStatic)Dimensions:Length115in(9.6f

17、t)Diameter41in(3.4ft)EngineWeight:1600lbSystemWeight:3100lb,-PitotInlet,10ft2CaptureArea-FixedConvergentNozzle,6ft2ExitArea,30,Propulsion,31,Propulsion,32,Propulsion,33,AuxiliaryPower,RequiredPower128kWPowerAvailablefromEngine70kW=.061*TaltAdditionalPowerRequired58kW,TotalWeight1304lbAPUFuelWeight59

18、5lbTotalWeight1899lb,APUContinentalL/TSIO-360,34,AuxiliaryPower,EngineExcessPower,kW=.061*TaltAdditionalThrust957lbAdditionalFuel8562lb,(T-D)*V=PowerAdditionalThrust58lbAdditionalFuel523lb,AverageAdditionalFuel4542lb,35,Fuselage3415lbWing4928lbControlSurface(s)2508lbTail297lbLandingGear1677lbPropuls

19、ionSystem3100lbFlightSystems460lbFuelSystem/Tanks496lbHydraulicSystem172lbElectricalSystem849lbAirCond/Anti-iceSys794lbPayload(Installed)6963lb,Take-OffWeight50000lbEmptyWeight18697lbWeightwithPayload25660lbFuelWeightAvailable24340lbFuelFraction.49FuelVolume3579gal,WeightBuild-up,-FuselageandLanding

20、GearWeightReducedby15%and5%,respectively,for2015TechnologyTargetFactors,36,StabilityandControl,CenterofGravityandFuelSchedule,37,StabilityandControl,StaticMargin(SM)Summary,38,StabilityandControl,Cmo=.0681,39,StabilityandControl,AileronsArea=37.9ft2eachMAC=1.47ftSpan=25.8ft,FlapChord:25%WingChordatR

21、ootFlapSpan:27%ofWingSpan,FlapsArea=38.0ft2eachMAC=2.15ftSpan=17.7ft,TotalControlSurfaceArea:152ft2,AileronChord:22%ofWingMACAileronSpan:40%ofWingSpan,40,StabilityandControl,V-TailCvt=.0145Svt=55.7ft2Cht=.34Sht=67.7ft242degfromVerticalRudderArea=18.6ft2=(1/3)Svt,41,MaterialsandStructure,CarbonFiber-

22、Wings-ControlSurfaces-FuselageFiberglass-ArrayPanels,MaterialSelection,StructuralConcept,Semi-MonocoqueFuselageStructureCarbonFiberWingBox,SparsandLandingGearStruts,42,MaterialsandStructure,43,MaterialsandStructure,44,MaterialsandStructure,45,MaterialsandStructure,Ixx=2.89E3slug-ft2Iyy=1.93E5slug-ft

23、2Izz=6.86E5slug-ft2,MassMomentsofInertiaBasedonHistoricalData,46,CostEstimations,EngineeringHours,ToolingHours,ManufacturingHoursandManufacturingMaterialCostsBasedonHistoricalDataand:-NumberofAircraftProduced-AircraftTake-offGrossWeight-MaximumVelocityFlightTestCostsBasedonHistoricalDataand:-Numbero

24、fFlightTestAircraft-AircraftTake-offGrossWeight-MaximumVelocityQualityControlHoursBasedonHistoricalDataand:-ManufacturingHoursDevelopmentSupportCostBasedonHistoricalDataand:-AircraftTake-offGrossWeight-MaximumVelocityEngineandAvionicsCostProvidedBy:-LockheedMartin,47,CostEstimations,HoursEngineering

25、7,568,054Tooling4,483,622Manufacturing13,472,465QualityControl1,791,838,AircrafttobeProcured:100FlightTestAircraft:6,CostsDevelopmentSupport88,831,854FlightTest57,056,356ManufacturingMaterials260,106,607Engine206,700,000Avionics1,590,000,000,LaborRatesAdjustedto1999DollarsEngineering$85Tooling$88Manufacturing$73Qual