SAWE Report - Cal Poly San Luis Obispo

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Table 13.I - Military Vision Specifications Forward Pilot 5.1.1 Vision azimuth (°) up (°) down (°) 0 10 11 20 20 30 25 90 40 135 20 11° 5° 5.1.2 Aft Pilot Position 0 5 Figure 13.3 - Virtual Cockpit Model Utilizing this information the virtual cockpit model shown in Figure 13.3 was generated. The solid model also took into account the use of an ejection seat, room for instrumentation, controls, switch placement as well as the above military vision specifications. Further vision refinement produced rectilinear vision plots as shown in Figure 13.4. Canopy reinforcing structure was removed from the areas between 25° and 40° up to aide in inflight refueling vision. Runway vision areas are defined and every effort was made to increase downward vision to aide in ground handling as well as takeoff and landing. Takeoff and Landing vision is inherently limited in supersonic aircraft. In an effort to reduce pilot workload and increase flight ability, multifunction displays (MFD) in modern aircraft can double as vision aid tools. MFD 1 incorporated into the glare shield and upper instrument panel Figure 13.4 – Rectilinear Vision Plot of Forward Cockpit Position 87
that could be used in landing and takeoff to increase downward vision, meshing seamlessly with the actual cockpit over nose view shown in Figure 13.5. MFD’s 2, 3, and 4 display moving map imagery, flight critical data, and mission critical information. The moving map display could also double in landings as another artifical vision aide. Perhaps utilizing infra-red or other electromagnetic spectrums for poor weather penetration and increased all weather capabilities. The standard dash mounted HUD was dropped in favor of a current helmet mounted HUD systems under development shown in Figure 13.6. The HUD allows far superior situational awareness as well as more aerodynamic canopy configuration. Figure 13.5 - Cockpit Display Arrangement Figure 13.6 - Helmet Mounted HUD Aircrew safety was a primary concern in the design of Vendetta. Due to RFP requirements the majority of the Vendetta’s mission will occur above the military specified ceiling for flight without a full pressure suit (50,000ft). Further research revealed the reasoning behind the specification. The NASA Bioastronautics study SP-3006 shows that animal and human life functions become critically affected by the lower oxygen content and lower pressure of the upper atmosphere. The study outlines how physiological effects such as the bends and hypoxia as well as the extremely low temperatures of high altitude within seconds render a human unconscious and dead in a mater of minutes. Also outlined is the Armstrong Line (63,000 ft), or the altitude at which water, at room temperature, will freely boil. In the study it shows how animals survived momentary exposure to altitudes higher than 63,000ft due to intravenous pressure keeping the blood within their veins liquid. Balancing this information against the economics and long prep and turn around time associated with full pressure suits the decision was made to opt for a partial pressure suit configuration. The advanced fighter crew protection system is shown in Figure 13.8. A partial pressure suit system was developed specifically for this altitude mission. It represents the next step beyond current systems and offers low unit cost in comparison to full pressure suits as well as low turn around time due to no necessity for a suiting procedure which involves lowering of blood nitrogen levels such as those used in the U-2. 88
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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
Page 47 and 48: Table 6.II - RFP Dimensions Compare
Page 49 and 50: 38 Figure 6.1 - VAATE Goals
Page 51 and 52: 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: 13 Cockpit Cockpit Design began wit
Page 101 and 102: 14 Systems The systems of the Vende
Page 103 and 104: 14.3 Fuel System Initial fuel syste
Page 105 and 106: 15 Manufacturing Several manufactur
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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