Vendetta Final Proposal Part 2 - Cal Poly

Table 17.I - RFP Compliance Checklist
RFP Requirement Met Page# RFP Requirement Met Page#
Crew Performance Requirements
• Two pilot cockpit design 71 • 0 ft/sec specific excess power at 1-g mil. Thrust (1.6 M/50,000 ft) 59
Maintenance • 200 ft/sec specific excess power at 1-g max. thrust (1.6 M/50,000 ft) 60
• Easy access to and removal of major systems 78,79 • 0 ft/sec specific excess power at 2-g max. Thrust (1.6 M/50,000 ft) 60
Structure • 8.0 deg/sec instantaneous turn rate (0.9 M/15,000 ft) 62
• +7, -3 vertical g’s (clean, 50% fuel) 38 Weapons Carriage
• 2,133 psf max. dynamic pressure (Mach 0.2, sea-level) 38 • (4) Mk-84 LDGB 67,FO5
• 1.5 factor of safety on all design ultimate loads 36 • (4) GBU-27 + (2) AIM-120 67,FO5
• 12,000 hour service life 80-81 • (4) 2,000 lb JDAM + (2) AIM-120 67,FO5
Fuel/Fuel Tanks • (4) AGM-154 JSOW + (2) AIM-120 67,FO5
• Design fuel is JP-8 (6.8 lb/gal) FO2,75 Measures of Merit
• All fuel tanks self-sealing and retained throughout mission 75 • Weight Summary (TOGW, W e , W f , W/S, T/W, W f /W) 7
Stability • Aircraft Geometry
• Closed loop static/dynamic stability meets MIL-F-8785B 47-57 ◦ Wing/control surface area 19
• Static margin within +10% and -30% limits 42-45 ◦ Fuselage size and volume FO1
• Digital control system for longitudinally unstable designs 47-57 ◦ Frontal cross sectional area distribution 24-25
Balanced Observables ◦ Wetted area 25
• Balanced radar, IR, visual, acoustical, and electromagnetic signatures 13, FO3 ◦ Inlet and diffuser 31-34
• Front aspect RCS less than 0.05 m 2 against 1-10 GHz radar 13, FO3 • Systems integration
• All stores carried internally 67,FO5 ◦ Landing gear 40-41
Operation ◦ Weapons carriage 67-69,FO5
• All weather operations and weapons delivery from NATO runways,
◦ Sensor and avionics locations FO1, FO2
65,72
shelters, facilities
◦ Cockpit 71-73
Cost • Mission duration, radius, fuel burn by mission segment 64
• Flyaway cost less than 150 million (200 unit buy) 80 • Takeoff and landing distance (standard and icy conditions) 65
• Minimize life cycle costs 80 • Performance at 50% internal fuel
Engine Deck ◦ Max. Mach at 36,000 ft 60
• Include an engine data package 26-35, 84 ◦ 1-g max. thrust specific excess power envelope 60
Mission Performance ◦ 2-g max. thrust specific excess power envelope 60
• Weapons Load – (2) AIM-120 + (4) 2,000 lb JDAM 67-69,FO5 ◦ 5-g max. thrust specific excess power envelope 61
• Takeoff fuel for warm-up and acceleration (sea level, 59°F) 64 ◦ Max. thrust sustained load factor envelope 61
• Climb from sea level to optimum supercruise altitude 64 ◦ Max. thrust maneuvering performance diagrams at sea-level 62
• Supercruise out 1,000 nm at M=1.6 and optimum altitude 64 ◦ Max. thrust maneuvering performance diagrams at 15,000 ft 62
• Climb and Dash out 750 nm above 50,000 ft at M=1.6 64 • Fly away and life cycle costs (cost trades 100 to 1,000 units) 80-81
• Drop (4) 2,000 lb JDAM’s, turn 180° at M=1.6 at 50,000 ft 64 • Design Drawings
• Dash back 750 nm above 50,000 ft at M=1.6 64 ◦ Detailed three view FO1
• Supercruise back 1000 nm at M=1.6 and optimum altitude 64 ◦ 3-D perspective FO1
• Descend to sea level (no distance or fuel credit) 64 ◦ Internal layouts FO2
• Reserve fuel for 30 min. at sea level and maximum endurance speed 64 ◦ Materials selection FO4
83