SAWE Report - Cal Poly San Luis Obispo

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Gravity ground refueling is provided via ports on the upper surface of the wing into tanks one and two. From there fuel can gravity feed into tanks three and four. This same gravity feed system can be utilized in flight given power feed system loss. All major thermal transfer within the aircraft is performed by the fuel system. The air cooled fuel cooler utilizing inlet duct boundary layer and flow control diversion air, placed ahead of the main gear bays dissipates all kinetic heating experienced by the airframe as well as systems heat generated. Dual heat exchangers are utilized for combat survivability. Fuel flow rate system 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. The Vendetta is fitted with an onboard fire suppression system, utilizing a halon suppressant in the engine bay and fuel cutoff valves at all fuel tanks. The system is designed so it can be retrofitted with a more environmentally friendly suppression chemical in the future. Table 14.II - Fuel System Sizing Requirements Fuel System Sizing Requirement Fuel Flow Rate GPM (LPM) CG Shift Requirement Between #3 and #4 Fuel Tanks 100 (379) KC-10 Probe Maximum Refueling Rate 1100 (4164) (2) F-119 Turbofan @ Max Thrust With Reheat 294 (1113) Air Cooled Fuel Cooler (ACFC) 400 (1514) 93
15 Manufacturing Several manufacturing considerations have been considered and planned for in the design of the Vendetta. One of these considerations is part commonality, which reduces the total number of separate parts that must be manufactured; thereby lowering manufacturing costs. The Vendetta is symmetrical in that both left and right wings, landing gear, horizontal and vertical stabilizers, etc. will be manufactured almost exactly the same. Furthermore, all flying surfaces are symmetrical and would provide an additional improvement in manufacturing costs. The design has also taken into consideration the routing of electrical lines, hydraulic lines, etc. These systems would be interconnected through a routing tunnel through the fuselage of the aircraft. This would reduce installation complexity and therefore reduce the amount of labor involved in the installation process. The routing tunnel as it passes beside the forward fuel tank, and aft past the weapons bay is shown below in Figure 15.1. Figure 15.1 - Routing Tunnel Manufacturing breaks include the wings, empennage, forward, center, and aft portions of the fuselage, as well as the landing gear itself. These breaks are shown in Figure 15.2. Figure 15.2 - Manufacturing Breaks 94
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SAWE Paper No. 3232 Category No. 10
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Table of Contents Abstract_________
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List of Figures Figure 1.1 - Design
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Figure 13.4 - Rectilinear Vision Pl
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Nomenclature AIAA American Institut
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α Angle of Attack, degrees, rad.
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Table 1.II - Summary of Design Requ
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Figure 1.3 - F-15 Strike Eagle F-11
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Table 1.III - Comparison of the F-1
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Many of the equations buried in the
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3 Configuration The current configu
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Another problem arises from the 20
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• Span = 54.7 ft • m.a.c. = 32
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4 Stealth Considerations As mention
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Table 4.I - Common Ground Radars Ra
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30 20 10 0 -10 -20 -30 -40 -50 1 GH
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5 Aerodynamics The major aerodynami
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1 GHz. 40º LE Sweep 10 GHz. 40º L
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5.3 Wing Thickness The effect of wi
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5.4 Airfoil The NACA 65A-003 airfoi
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1 Section Lift Coefficient 0.9 0.8
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90 80 Wing Cross Sectional Area (ft
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6 Propulsion In developing the prop
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Table 6.II - RFP Dimensions Compare
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38 Figure 6.1 - VAATE Goals
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TSFC 3.0 2.8 2.6 2.4 2.2 2.0 1.8 1.
Page 53 and 54: Deflection Angle Analysis for Mach
Page 55 and 56: Figure 6.8 - Cost Association with
Page 57 and 58: The inlet has a boundary layer dive
Page 59 and 60: 7 Materials and Structure The overa
Page 61 and 62: Vertical Attachment Points Horizont
Page 63 and 64: 8 Landing Gear Landing Gear design
Page 65 and 66: steel. This means that more braking
Page 67 and 68: Table 9.II - Final Component Weight
Page 69 and 70: throughout the 5-hour mission. Usin
Page 71 and 72: 10 Stability and Control To initial
Page 73 and 74: difference in neutral point and cen
Page 75 and 76: 40 30 20 10 0 -10 -20 -30 -40 -50 2
Page 77 and 78: The Vendetta configuration utilizes
Page 79 and 80: -0.6 -0.4 UNSTABLE NEUTRAL -0.2 Lif
Page 81 and 82: Validation of an aircraft design su
Page 83 and 84: consumption. The main aspects of th
Page 85 and 86: In addition to the performance requ
Page 87 and 88: 70,000 Altitude (ft) 60,000 50,000
Page 89 and 90: 11.4 Mission Requirements By comple
Page 91 and 92: Table 11.VIII - Landing Flight Prof
Page 93 and 94: 11.7 Alternate Missions In addition
Page 95 and 96: 12 Payload Weapon internal layout d
Page 97 and 98: 13 Cockpit Cockpit Design began wit
Page 99 and 100: that could be used in landing and t
Page 101 and 102: 14 Systems The systems of the Vende
Page 103: 14.3 Fuel System Initial fuel syste
Page 107 and 108: 16 Cost Analysis The final and perh
Page 109 and 110: Appendix Threats Chart Common Surfa
Page 111 and 112: Wing Break Point Fuel Aft Fuselage
Page 113 and 114: The Vendetta Design Team Chris Atki
Page 115 and 116: References 1. “Ejection Systems,
Page 117: 35. www.dfrc.nasa.gov/PAO/PAIS/HTML
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SAWE Report - Cal Poly San Luis Obispo

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