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Lockheed Martin Challenge

Lockheed Martin Challenge. Vertical Launch UAV Project Plan. Mission Statement. Construct an unmanned aerial vehicle (UAV) with a camera payload UAV must autonomously navigate with real-time video feed to ground station UAV must utilize a pneumatic vertical launch system.

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Lockheed Martin Challenge

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  1. Lockheed Martin Challenge Vertical Launch UAV Project Plan

  2. Mission Statement • Construct an unmanned aerial vehicle (UAV) with a camera payload • UAV must autonomously navigate with real-time video feed to ground station • UAV must utilize a pneumatic vertical launch system

  3. UAV Physical Layout • Constraints • Wing Design • Airfoil Selection • 2 Piece Assembly • Materials Selection • Composite vs. Film Covering • Landing System • Belly Land (FR) • Tail • Fuselage • Camera Considerations Modified Byron’s Pipe Dream Design

  4. Propulsion • Trade-off • Gas • Electric • Propulsion Related Requirements • 40-50 kt cruise • 2 hour endurance • Possible Solutions • Hacker • AXI Gold 5330 • Propeller Hacker A60 L Series AXI Gold 5330

  5. Current Design Process • XFLR5 • Methods • Vortex Lattice • Lifting Line • Output • Cl, Cd • Very efficient for low Reynolds Numbers • Structures Spreadsheet • Mike Garton • MotoCalc 8 • Engine Requirements

  6. Systems Integration • Launch System • Attachment • Avionics • Autopilot switchover

  7. Technical Challenges • Endurance • Weight • Power • Size – Humvee Capacity • Launch Sequence • Aircraft-Launch System Attachment • Control • Structural Integrity

  8. Pneumatic Launch System Components • Piston and Casing • Cradle and Carriage • Collapsible Legs • Pneumatic System

  9. Piston and Casing • Encased piston tube • Magnetic piston • Rubber piston stop

  10. Cradle and Carriage • Magnetic carriage • Carriage slides along casing above piston • Cradle mounted on carriage • Slot for hook attachment on plane

  11. Transportation • Requirements: • To fit within the back cargo hold of a small Humvee • Assemble within ~5 min • Design Solution: • A compact rod-less pneumatic slide • Collapsible stabilizing legs • Launch from the ground

  12. Pneumatic System

  13. Force Requirements • Design Specifications: • Plane weight 20 lbs • 100 psi air pressure • Final launch height of 100 ft • Using an Excel sheet to predict forces • Determine: • Air tank size • Valve size • Piston stroke length • Etc.

  14. Testing and Integration • Testing • Pneumatics • Can we launch a 20 lb plane with a 100psi of air to a 100ft? • If not what can we do? • Actual field tests with a test plane • Integration • Plane cradle • Autopilot control

  15. Avionics and Electrical Systems Components Autopilot Video Ground Station

  16. Autopilot Requirements • Autopilot System must: • Be capable of autonomously navigating using waypoint navigation • Support a vertical pneumatic launch • Be capable of monitoring and controlling all systems necessary for flight • Support manual-override control • Be capable of transmitting real-time flight data to the ground control station

  17. Autopilot • Prime Concerns: • GPS, Inertial Measurement Unit, Compass, Gyroscope modules • Ability to interface with aircraft systems • Customization for launch and landing sequence • Cost

  18. Video Requirements • Video System must: • Return real-time video to a base station • Be able to distinguish a 6” target at 100’ • Be capable of a minimum 30 minutes of operation • Be designed in a “modular” fashion

  19. Camera 100 ft • Industrial Box style camera • Able to be customized based on lens • Vari-focal Auto-Iris Lens • Manual adjustable focal length 45° 83 ft X / 83 pixels per foot 70° 100 ft 140 ft X / 140 pixels per foot

  20. Ground Station Requirements • Ground Station must: • Display real-time video as transmitted from the onboard camera • Provide controls necessary for manual override • Be capable of transmitting and receiving flight data to the onboard autopilot system • Be mobile and have the ability to be transported in the back of a military humvee

  21. Ground Station • Separate displays for video and flight data • Components chosen based on onboard systems • Mobile power source based upon requirements of ground station components

  22. Primary Concerns • Launch to cruise transition • Data transmission and reception range • Flight time

  23. Launch to Cruise Transition • Vertical Launch • How/When does main autopilot take over? • Customize autopilot for launch

  24. Data Transmission/Reception • Range above 10 miles becomes problematic • Using a directional antenna presents problems • Omni-directional antenna – power consumption problems • Planning on approximately 5W transmitter for video system • Independent transmitter for video system Radius: x Power Required: y Radius: 2x Power Required: y2 Radius: 3x Power Required: y3

  25. Flight Time • Original flight time requested by Lockheed Martin: 2hrs • Power consumption for this length of time is problematic • More Batteries = More Weight • Control subsystem power consumption

  26. Deliverables for Fall 2008 • Project Plan – Sept 27, 2008 • Initial design of each component – Oct 15, 2008 • Physical system build complete – Nov 1, 2008 • Integration of rail launch and aircraft – Nov 30, 2008 • Begin testing of autopilot system – Nov 30, 2008 • Testing of airplane and launch system – Dec 1, 2008 • Final draft plan – Dec 15, 2008

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