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 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

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.

Design Timeline

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

Mission Profile

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

Initial Designs Design #1 – Michael Basic

Initial Designs Design #2 – Joshua T. Hu

Initial Designs Design #3 – Aaron Pebley

Initial Designs Design #4 – Brandan York

Initial Designs Design #5 – Joshua T. Hu

Initial Designs Design #6 – Brandan York

Decision Matrix

Final Design 23 ft. 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

Compliance Matrix

Aerodynamics

Aerodynamics

Ps vs. Mach Chart

C.G. Movement

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)

Subsystem Avionics Fuel Tanks

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

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

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

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

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

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