Vendetta Final Proposal Part 1 (3.4 MB) - Cal Poly

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Hydraulic System (Orange)Electrical System (Blue)Fuel System (Red)Materials SelectionID1234567891011121314ActuatorNose RetractFlow Nose Deflector SteeringFlow DeflectorLE FlapMain RetractBrakesMPRL RotateTE FlapAileronEngine Driven PumpAPU Driven PumpHorizontalRudderThrust Reverser499Number1126242444224448151617345,67810 11 1,2ID151617181920ComponentRADARAvionicsSystemsDeIcing BootPTO driven GeneratorAPU driven Generator18ID212223242526Number11221Pneumatic System (Green)Pneumatic SystemAvionics CoolingOBIGGSFlow PressurizationDeflectorLAU-142APHXEngine BleedNumber1112122325212227292432332830ID272829303132333435Forward Fuselage Tank23,034 # JP-831ComponentAAR PortFlow Single Deflector Point RefuelingFlow Forward Deflector FuselageTank & PumpACFCWing Tank & PumpAft FuselageTank & PumpPrimary Fuel PumpEngineAPURight Wing Tank6,366 # JP-8Number111221221444440363738404340423945ID3637383940414243444546474849ComponentRadomeCanopyFlow Forward Deflector Skin & ChineBulkheads / FramesFuel TankWing RibsInlet DuctWeapons Bay DoorsControl Surface SkinLanding GearWing SparsHigh Temperature StructureHorizontal Pivot ShaftHorizontal Internal Structure4146MaterialCompositePolycarbonateFlow Composite Deflector & TitaniumResin transfer, Molded CompositeAluminum, TitaniumResin Transfer, Molded CompositeResin Transfer, Molded CompositeCompositeThermoplastic Skin, Resin TransferMolded Composite StiffnersCompositeTitanium, Steel AlloyTitanium, Resin TransferMolded CompositeTitaniumCarbon CompositeAluminum12132019263435Aft Fuselage Tank23,208 # JP-844474814Total Fuel59,000 # JP-84449Chris DroneyNate SchnaibleRev. 3VendettaScale 1:150Kolby KeiserChris MaglioHigh RollersFoldout 4Systems andMaterial SelectionChris AtkinsonDan Salluce5/23/02
8 Landing GearLanding Gear design for the Vendetta has eight significant design drivers.1) Tire selection to permit a high 150 knot takeoff and landing speed2) 120,000 lb gross weight3) Ease of loading and reloading weapons4) Tail Strike Angle5) Ground Handling Characteristics6) Structural Location7) Minimal Internal Volume Usage8) Low WeightSuitable structural attachment points dictated the main gear be positioned near the subsonic center of pressure onthe main wing (near the main spar) shown in Figure 7.2. This placement, as well as limited internal volume, goodground handling characteristics, minimal frontal area, and ease of unloading and loading weapons led to the adoption ofa tricycle landing gear configuration. The main gear configuration was then approximated as a 737 type main gear, (nearthe Vendetta’s TOGW) for volume purposes.Initial sizing began with tire selection. The main gear of the Vendetta should carry 92% of the TOGW and thenose gear should carry 8%. Starting with a database of tires and wheels the initial listing was narrowed to the choice of36in x 11in tires for the main gear and 24in x 7.7in for the nose gear. The tires selected allowed a 1.5 factor of safety(RFP imposed) over the dynamic landing load of the aircraf.Knowing the approximate volume of the 737 landing gear configuration with usable tires a solid model of thefuselage and internal components was produced todetermine the exact gear location. The initial designconsidered the smallest internal volume as well assmallest frontal area for a given load (Figure 8.1). Afteranalyzing both the internal position the gear would haveto fold into, behind and under the main inlet ducts, thetandem configuration was chosen. The main gear was thendesigned to fold into the allotted space; the retractionscheme can be seen in Figure 8.2The next challenge presented was obtaining theFigure 8.1 - Landing Gear Configuration Trade Studynecessary gear height for easy loading and unloading as40
Page 6 and 7: Figure 11.1 - 1-g Military Specific
Page 8 and 9: Nomenclature6DOF Six Degrees of Fre
Page 10: 1 IntroductionThe American Institut
Page 13 and 14: Table 1.III - Comparison of the F-1
Page 15 and 16: The weight fraction method provides
Page 17 and 18: 3 ConfigurationThe current configur
Page 19 and 20: • Span = 53 ft• m.a.c. = 32 ft
Page 21 and 22: VendettaChris DroneyNate SchnaibleK
Page 23 and 24: low signature axisymmetric advanced
Page 25 and 26: 0° Lookup77°50403020100-10-20-30-
Page 27 and 28: 5.2 Wing SweepThe next wing paramet
Page 29 and 30: 5.3 Wing ThicknessThe effect of win
Page 31 and 32: 0.10.050-0.05-0.1-0.150 0.1 0.2 0.3
Page 33 and 34: 5.6 DragDrag was divided into four
Page 35 and 36: 6 PropulsionIn developing the propu
Page 37 and 38: Turbine Engine Technology (IHPTET)
Page 39 and 40: 35,00030,000Sea Level 1.5K 5K10K20K
Page 41 and 42: 0.990.980.97Pressure Recovery0.960.
Page 43 and 44: oundary layer diverter for high spe
Page 45 and 46: 7 Structural Layout & Material Sele
Page 47: Vertical AttachmentPointsHorizontal

Vendetta Final Proposal Part 1 (3.4 MB) - Cal Poly

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