Vendetta Final Proposal Part 2 - Cal Poly

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utilized for fuel capacity. The remaining fuel tank volume was left for self sealing linings, structure, and fuel expansion (See Foldout 2). All tanks in the aircraft are pressurized with nitrogen gas from the onboard inert gas generating system (OBIGGS). Pressurization is minimal due to structural constraints and the low vapor pressure of JP-8. Nitrogen reduces the concentration of fuel vapor and thus the chance of an explosion. All tanks on the aircraft are self sealing and feature flame resistant overflow and exhaust venting. Single point fueling and de-fueling can be performed from a port on the starboard side of the forward fuselage (Foldout 4). This fueling point shares common lines with the AAR retractable fueling boom port located on the upper portion of the forward fuselage. Both ports offer fueling rates as high as 1,100 gpm, which is the maximum KC-10 fuel probe refueling rate (Table 14.II). Fuel is directed to the forward fuselage tank and then power transferred to the remaining three tanks. A gravity feed system can be utilized in flight in case of a failure of the power feed system. All major thermal transfer within the aircraft is performed by the fuel system. The air cooled fuel cooler utilizes inlet duct boundary layer and flow control diversion air to dissipate all kinetic heating experienced by the airframe as well as heat generated by onboard systems. Dual heat exchangers are utilized for combat survivability. Fuel flow rate requirements (Table 14.II) will be used to size fuel lines and pumps. All fuel lines are redundant to provide for fuel circulation and system combat survivability. <strong>Vendetta</strong> is fitted with a halon fire suppression system. Table 14.II - Fuel System Sizing Requirements Fuel System Sizing Requirement Fuel Flow Rate GPM CG Shift Requirement Between #3 and #4 Fuel Tanks 100 KC-10 Probe Maximum Refueling Rate 1100 (2) F-119 Turbofan @ Max Thrust With Reheat 294 Air Cooled Fuel Cooler (ACFC) 400 76
14.4 Government Furnished Equipment Table 14.IIIprovides a list of GFE and identifies weither or not the equipment was utilized. Some GFE was not used because it was not applicable to the design. A brief description of the reasoning is also provided Table 14.III - List of Government Furnished Equipment Government Furnished Equipment Application Utilized ICNIA INS/GPS guidance and weapons targeting YES 3 x MFD Crew situation awareness enhancement YES Heads-Up Display Replaced by Helmet Mounted Display NO Data Bus New System Architecture Replaces Data Bus with VMS NO Vehicle Management System Manages Aircraft Systems YES IRSTS (Tessa Derivative) Low Speed and Altitude Targeting for GBU-27 YES Active Array Radar Use the AN/APG-77 LPI System Due to LO Requirement NO LANTIRN Navigation System Not a Low Altitude Night Aircraft NO LANTIRN Targeting System Not a Low Altitude Night Aircraft NO HARM Targeting System Does Not Carry HARM Missiles Because of LO Design NO Electrical System Engine Control YES Auxiliary Power Unit (APU) Description in RFP is of a Ram Air Turbine NO Ejection Seat Standard Seat Will Not Cover Flight Envelope. Use K-36D NO OBOGS Oxygen Generation for Pilot YES OBIGGS Nitrogen Generation for Fuel System YES AIM-120 AMRAAM Advanced Medium Range Air to Air Missile YES M61A1 20 mm Cannon Supercruise Mission Eliminates Viability of Cannon NO 14.5 Maintenance and Servicing Plan <strong>Vendetta</strong> is optimized for lowest possible integrated combat turnaround times focusing on open maintenance access for all major components and fast weapon, fuel, and crew refurbishment. Maintenance panels are located regularly across the bottom and top sides of main fuselage sections for easy open access to all serviceable equipment. RCS considerations are taken into account for placement and geometry of access paneling. Major component placement allows field servicing without major overhaul equipment jigs and specialized oversized tooling. Utilizing a hydrant pressurized fueling rate of 1100 gallons per minute fueling time is only 7.9 minutes. More common fueling rates of 100 gallons per minute drive fueling time to 87 minutes. Combat weapon refurbishment takes approximately 10 minutes per weapon or one hour for the RFP mission loading. Therefore with RFP weapons loadout, turnaround times between 60 and 87 minutes, depending upon the available refueling rate, are possible. Due to the choice of partial pressure suit, crew suiting and preparation is far below this time. 77
Page 1 and 2: well as a tip back angle which did
Page 3 and 4: Table 9.II - Final Component Weight
Page 5 and 6: the center-of-gravity location clos
Page 7 and 8: 10 Stability and Control To initial
Page 9 and 10: management system could then be use
Page 11 and 12: 40 30 20 10 0 -10 -20 -30 -40 -50 2
Page 13 and 14: flight. This would require a large
Page 15 and 16: Table 10.IV - Longitudinal and Late
Page 17 and 18: Additional components were integrat
Page 19 and 20: 11 Performance 11.1 Specific Excess
Page 21 and 22: 70,000 60,000 50,000 Altitude (ft)
Page 23 and 24: 11.3 Mission Requirements The RFP d
Page 25 and 26: 11.4 Takeoff & Landing The RFP requ
Page 27 and 28: 12 Payload Weapon internal layout w
Page 29 and 30: ange occurs due to the additional w
Page 31 and 32: 13 Cockpit Cockpit design began wit
Page 33 and 34: Due to RFP requirements the majorit
Page 35: fuelled systems offer high power to
Page 39 and 40: The assembly line would allow for m
Page 41 and 42: is a learning curve associated with
Page 43 and 44: Table 17.I - RFP Compliance Checkli
Page 45 and 46: 20,000 0.9 581 2,164 3,231 4,407 5,
Page 47 and 48: Appendix B - Design Tools Company S
Page 49: 25. Roskam, J. Airplane Flight Dyna

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