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MAE 155A Aerospace Engineering Design I

MAE 155A Aerospace Engineering Design I. Proposal #2 Dr. James D. Lang, Project Advisor. Team Firestorm Joshua T. Hu, Project Manager Brandan York, Chief Engineer Michael Basic, Project Engineer Aaron Pebley, Project Engineer. Outline of Presentation. Scope Design Timeline

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MAE 155A Aerospace Engineering Design I

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  1. MAE 155A Aerospace Engineering Design I Proposal #2 Dr. James D. Lang, Project Advisor Team Firestorm Joshua T. Hu, Project Manager Brandan York, Chief Engineer Michael Basic, Project Engineer Aaron Pebley, Project Engineer

  2. Outline of Presentation • Scope • Design Timeline • Design Factors • Mission Profile • Design Approach • Initial Designs • Decision Matrix • Final Design • Compliance Matrix • Aerodynamics, Structures, Stability, Subsystems, Supportability, Cost Analysis • Conclusion and Future Work Needed

  3. Scope • To develop and recommend an unmanned aerial vehicle (UAV) for the Royal Australian Air Force (RAAF). • Design must be viable and affordable compared to manned aircraft concepts. • UAV is to be similar to Joint Strike Fighter (JSF) in performance.

  4. Design Timeline

  5. Design Factors • Good Aerial Combat Performances for 2 Missions • Mission #1-Defensive Counter Air Mission • Mission #4-Offensive Counter Air Mission • Ease of Manufacturing • Low Cost • Modular Payload • Stealth • Variable Geometry Wings

  6. Mission Profile

  7. Design Approach • Jetfighter • Variable Geometry vs. Fixed Wings • V-Tail vs. Conventional • Fuselage Geometry • 2-D Vector Nozzles • Inlet Styles

  8. Initial Designs Design #1 – Michael Basic

  9. Initial Designs Design #2 – Joshua T. Hu

  10. Initial Designs Design #3 – Aaron Pebley

  11. Initial Designs Design #4 – Brandan York

  12. Initial Designs Design #5 – Joshua T. Hu

  13. Initial Designs Design #6 – Brandan York

  14. Decision Matrix

  15. 23 ft. 38 ft. 60 ft 7 ft. Final Design TOGW - 25125 lbs Fuel weight - 9170 lbs T/W - 1.19 (takeoff), .588(combat) L/D - 14(unswept), 12(swept), 7(dash) W/S - 70(takeoff), 35.8(combat) Max Mach 1.6 Wetted area/Wing area = 4.8

  16. Compliance Matrix

  17. Aerodynamics

  18. Aerodynamics

  19. Ps vs. Mach Chart

  20. C.G. Movement

  21. Materials and Structures -Main structural components made of either titanium or RTM composites -Wing skins made of carbon/epoxy thermoset composites (except the leading and trailing edges)

  22. Subsystem Avionics Fuel Tanks

  23. Subsystem Avionics C.G. Location Landing Gears 2-D Vector Nozzle Modular Payload Afterburning Low Bypass Turbofan

  24. Subsystem Variable Geometry Armpit Air Inlets w/ Channel-Type Boundary Layer Diverter

  25. Supportability • Off the shelf parts to save cost and training • Similar swing wing mechanism as F-14 Tomcat • Same avionics as JSF • Same powerplant as JSF • Same internal carriage as JSF • Same landing gear as JSF

  26. Cost Analysis • Required Life Cycle Cost (LCC) for 100 aircraft < $10 Billion • Firestorm UAV LCC for 100 aircraft = $6.3 Billion Requirement Met!

  27. Conclusion and Future Work Needed • Initial design phase over • Design factors achieved (low cost, stealth, etc…) • Further trade studies of T/W and W/S • Detailed study of vector nozzles • Aircraft mockup • Wind tunnel testings

  28. Conclusions and Further Work Needed (cont.)... • Perform FEA • Build and fly test vehicle

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