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X-IPITER

X-IPITER. 2005 AUVSI Undergraduate Student UAV Competition Mississippi State University November 19, 2004. Outline. Team Members Objective Mission Profile Competition Restrictions Design Schedule Budget Contingency Progress Update Closing Remarks. Team Members. Advisors

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X-IPITER

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  1. X-IPITER 2005 AUVSI Undergraduate Student UAV Competition Mississippi State University November 19, 2004

  2. Outline • Team Members • Objective • Mission Profile • Competition Restrictions • Design • Schedule • Budget • Contingency • Progress Update • Closing Remarks

  3. Team Members Advisors Dr. Randolph Follett (ECE) Mr. Calvin Walker (ASE)

  4. “Design and build an unmanned aerial vehicle (UAV) capable of performing realistic autonomous missions in an aviation environment.” Objective

  5. Mission Profile • Autonomous or manual takeoff • Autonomously navigate through specified waypoints (if manual takeoff, demonstrate transition to autonomous flight) • Dynamic re-tasking of aircraft during flight • Provide imagery, total number of targets, GPS coordinates, and target orientation • Autonomous or manual landing within a specified area

  6. Competition Restrictions • Ceiling: 500ft AGL • Floor: 50ft AGL • No-fly zones • Max Weight: 55lbs • Max Mission Time: 40min

  7. Map of Competition Area

  8. Overall Design

  9. Airplane Systems

  10. Flight Control

  11. Surveillance

  12. Onboard Power

  13. Ground Station

  14. Software

  15. The Airplane • Material Comparison • Fabrication • Dimensions • Weight • Components • Performance • Longitudinal Stability and Control

  16. Composites • Advantages • Strength • Durability • Ease of Fabrication • Disadvantages • Expensive • Can be heavy for small aircraft Material Comparison

  17. Balsa • Advantages • Light Weight • Relatively Inexpensive • Disadvantages • Complex Structural Design • Length of Fabrication Time Material Comparison, Cont.

  18. Method • Wet-layup • Hotwire Foam Materials • Materials • Fiberglass/epoxy • Carbon Tubes • Owens-Corning “Pink” Foam • Plywood Fabrication Technique

  19. Wing • Airfoil Section: SD7062 • Chord: 16in • Span: 106in • Area: 1696in2 • Aspect Ratio: 6.5 • Fuselage • Length: 40in • Length (Tip to Tail): 80in • Width: 8.5in • Height: 8.5in Airplane Dimensions

  20. Empennage • Horizontal • Airfoil: NACA 0009 • Span: 34in • Chord (Root): 11.3in • Chord (Tip): 5.6 • Area: 287.3 in2 • Aspect Ratio: 4.02 • Vertical • Airfoil: NACA 0009 • Height: 16in • Chord (Root): 15in • Chord (Tip): 7.5in • Area: 180 in2 Airplane Dimensions, Cont.

  21. Gross Weight: 35.73 Empty Weight: 34.6 • Airframe: 25 • Systems: 9.6 Fuel Weight: 1.13 Airplane & Systems Weight(All Weights in pounds)

  22. Engine • Fuji BT-64A Gasoline Engine • Fuel Tank • 24 oz • Propeller • 20in diameter X 10in pitch • Radio Control • Futaba 9-Channel Transmitter/Receiver Airplane Components

  23. Recovery Parachute • Drag Chute Airplane Components, Cont.

  24. Minimum Required Power: 0.37 hp • Velocity at PR,min: 28.9 mph • CDO: 0.047 • VSTALL: 27 mph • VCruise: 45 mph for PReq: 0.82 hp • Vmax: 97 mph Performance Analysis

  25. Longitudinal Stability and Control • C.G at 24 inches from Nose (1/4 Chord of Wing) • Distance from Neutral Point to Nose is 27.2 inches • Static Margin is 19.8% • Cm-alpha = -0.963 radians-1

  26. Schedule

  27. Total Cost

  28. Total Cost, Cont.

  29. Competition Cost

  30. Contingency Plan • Rugged Design • Chute System • Camera Transmission Failsafe Modes • COTS Parts for quick replacement

  31. Progress Update • Airframe Design 90% Complete Partial Construction Underway • Systems Hardware and Power Systems Complete Software Programming and Testing Underway

  32. Conclusion • Durable • Future Usability • Fulfils all Mission Specifications • Upgradeable

  33. Questions? If it KWAX, it must be a XAWK http://www.ece.msstate.edu/department/organizations/auav/

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