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

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6.4 NozzleThe nozzle of the Vendetta incorporates an afterburner and thrustreversers. It utilizes a low signature axisymmetric advanced nozzle, developedunder the IHPTET program, similar to that inFigure 6.12. The advanced nozzle is being used because it has comparableFigure 6.12 - Low-SignatureAxisymmetric Advanced Nozzlesignature to that of a 2-D nozzle, however it weights 50% less, costs 60% less and requires 300 fewer parts. Thrustvectoring is will not be incorporated as the Vendetta is not required to maneuver like a fighter.The nozzle will have thrust reversing capabilities to enable the aircraft to land on an icy runway and stop withinthe required 8,000 ft specified by the RFP. Clam shell style thrust reversers, which reverse 25% of the thrust through a15 degree angle, will be used. The thrust reversers will depart from the upper and lower fuselage just prior to the nozzle,translate back and come together behind the nozzle.35
7 Structural Layout & Material SelectionThe overall layout of the Vendetta’s structure is shown in Figure 7.1 and Foldout 2. The wing structure is similarto that of an F-15 and the material selection is similar to an F-22. The main load path is in the form of a central keel thatruns from between the nozzles and engines to the nose gear attachment point. The weapons bay splits the keel in thecenter of the aircraft. The load is shifted from the keel to the aft weapons bay wall and back into the keel at the forwardend of the weapons bay. A close-up of the weapons bay is also shown in Figure 7.1.Main WingSparsWeapons BayStiffenersFigure 7.1 - Structure Buildup for VendettaThe layout of Vendetta’s inlets and landing gear allow for a continuous structural member, in the form of abulkhead, to carry the aerodynamic loads from each wing directly to the central keel. This approach changes as thebulkheads move away from the main wing load paths. The weapons bay splits the forward wing attachment bulkheads.This occurs well in front of the aerodynamic center of the wing. Just forward of the aerodynamic center is the mainforward load path for the wing. The aft load paths are a ring structure around the engines and inlets. The importantthing to note is that where the primary loads are being distributed, between 25 to 50 percent of the mean aerodynamicchord, the bulkheads are continuous. Because of the thin root selection for the Vendetta, care was taken to ensure thatthe wing could withstand the tremendous loads produced by the 7-g load requirement with a factor of safety of 1.5. It36
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: oundary layer diverter for high spe
Page 47 and 48: Vertical AttachmentPointsHorizontal
Page 49: 8 Landing GearLanding Gear design f

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

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