1. 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

2. 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

3. JLFANG Black Knight 170

4. Black Knight 170 3-view

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

6. 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

7. Strike Mission Segment Properties

8. Strike Mission Compliance Summary

9. Strike Mission Aerodynamic Performance

11. Strike Mission Specific Excess Power 1-g

12. Strike Mission Specific Excess Power 5-g

13. Strike Mission Turn Rate at Sea Level

14. Strike Mission Turn Rate at 25,000 ft

15. Strike Mission Sustained Load Factor

16. Strike Mission Aircraft Characteristics

17. Strike Mission Engine Data

18. 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 28800 lb static thrust

19. 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

20. ISR/Attack Mission Segment Properties

21. ISR/Attack Mission Compliance Summary

22. ISR/Attack Mission Aerodynamic Performance

24. ISR/Attack Mission Aircraft Characteristics

25. ISR/Attack Mission Engine Data

26. ISR/Attack Mission Summary  Meets mission requirements -2600 nautical mile mission radius -Load limit n=1.5 for reduced modular wing weight -Take-off distance < 3200 ft capable  38500 lb take-off weight, 21425 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

27. 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

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