Request for Proposal: Joint Strike Fighter for Australian Air Force JLFANG Black Knight 170 Aerospace Engineering Design I University of California, San Diego Jacobs School of Engineering March 19, 2003 Dr. James Lang, Project Advisor Steven H. Christenson Andrew S. Fischer Ceazar C. Javellana III

Mission Requirements  Design an unmanned, all-weather multi-mission aircraft  Provide air defense, reconnaissance/surveillance and deliver precision-guided tactical weapons at long range  Capable of supersonic speeds for strike mission  Minimize life-cycle cost with 12,000 hours service life  Specific requirements: Strike Mission:  Long range strike capability at speeds up to Mach 1.6 at or above 25,000 ft.  Capable of performing a 3-hour patrol at 25,000 ft.  2,000 lb payload capacity.  Limit load factor n=+6 and –3 fully loaded. ISR/Attack Mission:  High endurance capability with range TBD.  Cruise for 8-hours at or above 25,000 ft at subsonic speeds.  2,000 lb payload capacity (ISR package or armament)  Unspecified limit load factor

JLFANG Black Knight 170

Black Knight view

Internal Components Avionics – Purple Flight & Propulsion Control System – Orange Fire Control System – Green Systems and Equipment – Blue Payload – Grey

Altitude Distance Phase 1. Take Off and Acc. Phase 2. Climb to Cruise Altitude Phase 3. Cruise Out Phase 4. Descend Phase 5. Strike Patrol Phase 6/8. Dash Out/Back Phase 7. Combat/Maneuvering Phase 9. Climb to Cruise Altitude Phase 10. Cruise Back Phase 12. Loiter 1000 nm Phase 11. Descend to Sea Level Strike Mission Profile

Strike Mission Segment Properties

Strike Mission Compliance Summary

Strike Mission Aerodynamic Performance

Strike Mission Specific Excess Power 1-g

Strike Mission Specific Excess Power 5-g

Strike Mission Turn Rate at Sea Level

Strike Mission Turn Rate at 25,000 ft

Strike Mission Sustained Load Factor

Strike Mission Aircraft Characteristics

Strike Mission Engine Data

Strike Mission Summary  Meets mission requirements (except one *) -550 nautical mile mission radius -Ps at prescribed alt, Mach and load factor -Take-off distance < 800 ft capable -Turn rate 12.6 deg/sec at 6-g’s *  38,500 lb take-off weight, 21,420 lb empty weight  Fuselage 37.8 ft long, 68.4 ft wing span, Sref 780 ft^2  130 x 20 x 20 inch payload bay – (8) 250 lb Mk-81 bombs or (1) 2,000 lb JDAM Mk-84 bomb  Scaled F-100 engine delivers lb static thrust

Altitude Distance Phase 1. Take Off and Acc. Phase 2. Climb to Cruise Altitude Phase 3. Cruise OutPhase 5. Cruise Back 5200 nm Phase 6. Descend to Sea Level Phase 4. Cruise ISR/Attack ISR/Attack Mission Profile

ISR/Attack Mission Segment Properties

ISR/Attack Mission Compliance Summary

ISR/Attack Mission Aerodynamic Performance

ISR/Attack Mission Aircraft Characteristics

ISR/Attack Mission Engine Data

ISR/Attack Mission Summary  Meets mission requirements nautical mile mission radius -Load limit n=1.5 for reduced modular wing weight -Take-off distance < 3200 ft capable  lb take-off weight, lb empty weight  Fuselage 37.8 ft long, 74.3 ft wing span, Sref 395 ft^2  130 x 20 x 20 inch payload bay – 2000 lb payload capacity  Scaled TF-39 engine delivers 9200 lb static thrust -Downscaled engine and module allows for fuel space

Other Mentionables Maintenance -Easy accessible avionics components -Quick engine and wing change through modular kits Uncertainty -Reduce uncertainty through refined estimates and analysis -Wto uncertainty ~15%, Thrust and TSFC at maneuver ~10% Materials -Use modern light-weight composite materials and stealth technology Future Work -Trade studies on long term cost savings for use of TF-39 engine from reduced TSFC -Wind tunnel testing of model to refine aerodynamic performance

References  L.M. Nicolai, Fundamentals of Aircraft Design, Revised 1984  D.P. Raymer, Aircraft Design: A Conceptual Approach, Third Edition, 1999