University of Colorado

1. Structures Mission Statement Aerodynamics Thrust Vectoring • "Design and construct a supersonic unmanned aerial vehicle that will break the world UAV speed record and utilize a fluid injection thrust vectoring control system." • Use fluidic injection to critically choke flow and provide thrust vectoring in nozzle • Create prediction models for secondary flow properties required to maintain critical throat area • Verify/augment models with physical test datacollected through modification on the SWIFT supersonic tunnel • Use as 1- D nozzle choking as proof of concept for later thrust skewing nozzle • Using almost all carbon fiber composite. • 3g limit and 100 kPa duct pressure with safety factor of 1.25 • Wings have a spar and rib structure • At end of inlet duct, max allowable stress of 2280 MPa, max predicted of 2000 MPa • Nose Inlet • Simplifies duct design • Requires less extensive wind tunnel testing / CFD modeling Project Requirements • Sears-Haack Fuselage • Minimizes shockwave drag • Aircraft shall achieve supersonic flight • Aircraft shall be under 50 kg • Aircraft shall meet all requirements for FAI speed record • Aircraft shall incorporate a fluidic thrust vectoring system for yaw control • Aircraft shall meet all requirements for testing at EAFB or similar facility • Cranked Arrow Planform • Better low-speed performance than standard delta • Easier to manufacture than • Ogee wing • Tail-less Design • Significant drag reduction • Yaw supplied by thrust vectoring • Roll and pitch both supplied by elevons (elevators + ailerons) Mission Profile Manufacturing • Carbon fiber wings and fuselage • High strength • Low weight • Composite molds • CNC’d female molds • Entire UAV out from two molds • Carbon fiber • Resuable Molds Flight Computer Propulsion Testing Aircraft parameters • Custom afterburning turbojet engine • Centrifugal compressor for good compression on small scale • Incorporating afterburner significantly increases thrust NI sbRIO Specifications 8.2''x5.6''-Size 110-3.3V Digital I/O 32-Analog Inputs 292 g-Mass 400 MHz-Processing Speed 256 MB-Internal Storage Fully Autonomous System • Integration of Controls and Sensors • Controls Every Aspect of Flight Programming in LabVIEW • GUI Based, Reusable Code Modify SWIFT supersonic wind tunnel Manual pressure control out of reservoir tank Secondary line pressure and mass flow controlled electronically Secondary line injected at throat of test nozzle Mass Breakdown Controls • Elevons • Length : 0.50 m • Width : 0.05 m • Take off speed : 54 m/s (105 knots) • Landing speed : 40 m/s (78 knots) • Pitching moment : 25 Nm @ CL0= 0.01 Wind Tunnel Testing at Air Force Academy in Summer 2011 Subsonic, Transonic and Supersonic Testing Mach 0.3 – 1.8 Total Weight = 50 kg University of Colorado Project Advisers : Dr. Ryan Starkey & Joseph Tanner Aerospace engineering Sciences