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. Final Design 23 ft. TOGW - 25125 lbs Fuel weight - 9170 lbs
T/W (takeoff), (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)

23. Subsystem
Avionics
Fuel Tanks

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

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

26. 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

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

28. 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

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