lockheed martin challenge
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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. - PowerPoint PPT PresentationTRANSCRIPT
Lockheed Martin ChallengeVertical Launch UAV
Project Plan
∞ 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
Mission Statement
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
∞ Trade-off∞Gas ∞Electric
∞ Propulsion Related Requirements∞40-50 kt cruise∞2 hour endurance
∞ Possible Solutions∞Hacker∞AXI Gold 5330
∞ Propeller
Propulsion
Hacker A60 L Series
AXI Gold 5330
∞ XFLR5∞ Methods
∞ Vortex Lattice ∞ Lifting Line
∞ Output∞ Cl, Cd
∞ Very efficient for low Reynolds Numbers
∞ Structures Spreadsheet∞ Mike Garton
∞ MotoCalc 8∞ Engine Requirements
Current Design Process
∞ Launch System∞Attachment
∞ Avionics∞Autopilot
switchover
Systems Integration
∞ Endurance∞Weight∞Power
∞ Size – Humvee Capacity
∞ Launch Sequence∞Aircraft-Launch
System Attachment∞Control∞Structural Integrity
Technical Challenges
∞ Piston and Casing∞ Cradle and Carriage∞ Collapsible Legs∞ Pneumatic System
Pneumatic Launch System Components
∞ Encased piston tube∞ Magnetic piston∞ Rubber piston stop
Piston and Casing
∞ Magnetic carriage∞ Carriage slides along casing above piston∞ Cradle mounted on carriage∞ Slot for hook attachment on plane
Cradle and Carriage
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
Pneumatic System
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.
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
Avionics and Electrical Systems Components
Autopilot Video
Ground Station
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
Autopilot∞ Prime Concerns:
∞GPS, Inertial Measurement Unit, Compass, Gyroscope modules
∞Ability to interface with aircraft systems
∞Customization for launch and landing sequence
∞Cost
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
Camera∞ Industrial Box style camera
∞ Able to be customized based on lens
∞ Vari-focal Auto-Iris Lens
∞ Manual adjustable focal length
100 ft
83 ftX / 83 pixels per foot
45°
70°100 ft
140 ftX / 140 pixels per foot
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
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
Primary Concerns∞ Launch to cruise transition
∞ Data transmission and reception range
∞ Flight time
Launch to Cruise Transition∞ Vertical Launch
∞ How/When does main autopilot take over?
∞ Customize autopilot for launch
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: xPower Required: y
Radius: 2xPower Required: y2
Radius: 3xPower Required: y3
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
∞ 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
Deliverables for Fall 2008