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PDR

D-SUAVE. PDR. Deployable Small UAV Explorer (D–SUAVE) Customer: Kamran Mohseni University of Colorado at Boulder Fall 2006. D-SUAVE. D-SUAVE Team. David Goluskin * Michael Lapp * Burhan Muzaffar * Jastesh Sud * Brandon Bobian Nathan Sheiko Yoshi Hasegawa Miranda Mesloh.

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PDR

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  1. D-SUAVE PDR Deployable Small UAV Explorer (D–SUAVE) Customer: Kamran Mohseni University of Colorado at Boulder Fall 2006

  2. D-SUAVE D-SUAVE Team • David Goluskin* • Michael Lapp* • Burhan Muzaffar* • Jastesh Sud* • Brandon Bobian • Nathan Sheiko • Yoshi Hasegawa • Miranda Mesloh * Presenting

  3. Overview • Objective • Mission Overview • Deployment • Aerodynamics • Structures • Propulsion • Electronics • Project Plan • Major Risk Assessments • Summary • References • Appendices

  4. Primary Objective “To design, fabricate, integrate and verify a RC controlled UAV capable of being remotely deployed from the ARES aircraft and flying a specific flight pattern.”

  5. D-SUAVE Feedback Primary Factors Requirement flow down Stability of airplane during deployment Deployment scenarios affect the configuration selected Where do we deploy from? Secondary Factors What is the expected data transfer or collection rate? Under what atmospheric conditions the system should be able to operate What supports the mass determination? Required deployment force and acceleration the aircraft must withstand Why a Micro aerial vehicle? What is the detail of the mission? Overestimating propeller efficiencies Sketches/pictures of the possible configurations Who will pilot the vehicle?

  6. Requirements Flow Diagram Mission Spatial Resolution Spatial Range Temporal Resolution Readings per Location Sensors Carrier Vehicle Lap Pattern Lap Distance Lap Time Number Of Laps Cruise Velocity Cruise Drag Empty Mass Vehicles per Carrier Stall Velocity Turn Radius Velocity Endurance Sensor Box Mass, Size and Placement Vehicle and Package Mass Deployment Velocity Data Collection Driving Factors Carrier Vehicle Driving Factors Requirements

  7. Mission Profile Carrier Vehicle ARES

  8. Mission Path 5 min/lap, 4 laps 100 m 600 m

  9. Requirements

  10. D-SUAVE Design Process Helicopter Lighter than Air Fixed Wing Rocket Glider Folded in Tube Unfolded Piggyback Folded Piggyback Flying Wing Low Aspect Ratio Conventional Canard Bi-Plane Vehicle Design Propulsion/Power Supply Electronics/Comm/Sensors Prop Motor Speed Control Launchable/Packageable Structure Configuration Folding or Non Folding Gear Box Outrunner Wing Folding Stability Controllability Material Membrane Dihedral Control Surfaces Ailerons Rudder and Elevator only Link

  11. D-SUAVE Design Alternatives Link

  12. Existing Packagable MAVS Good Acceptable Unacceptable *Payload data generally unavailable

  13. D-SUAVE Deployment

  14. D-SUAVE Packaging Methods

  15. D-SUAVE Vehicle Deployment Methods

  16. D-SUAVE Wing Deployment

  17. D-SUAVE Tube Drop Verification

  18. D-SUAVE Car/Pole Verification • Vcar = VUAV • Pole height dictated by drop distance

  19. D-SUAVE Package Configuration

  20. D-SUAVE Aerodynamics

  21. D-SUAVE Possible Configurations Low-Aspect Ratio Aircraft • Assumptions: • Small angle of attack • Thin airfoil • Estimated Parasite drag

  22. D-SUAVE Possible Configurations Flying Wing • Assumptions: • Small angle of attack • Thin airfoil • Estimated Parasite drag

  23. D-SUAVE Possible Configurations Conventional Aircraft • Assumptions: • Small angle of attack • Thin airfoil • Estimated Parasite drag

  24. D-SUAVE Possible Configurations Canard Aircraft • Assumptions: • Small angle of attack • Thin airfoil • Estimated Parasite drag

  25. D-SUAVE Possible Configurations Biplane • Assumptions: • Small angle of attack • Thin airfoil • Estimated Parasite drag

  26. D-SUAVE Configuration of Aircraft

  27. Wing Sizing Calculate span required to lift vehicle for a given chord: Guess b c CL Lifting Line S no yes L L=W ? b 8.6 cm 14.1 cm

  28. L/D Without Induced Drag Airfoil Data Lifting Line Approximation

  29. L/D With Induced Drag Airfoil Data Corrected for Di(e = 0.6, AR = 8) Lifting Line Approximation

  30. Required CL Link

  31. Tail Configurations

  32. D-SUAVE Control Surface Configuration

  33. D-SUAVE Structures

  34. D-SUAVE MS M S Spar Structure b/2 α = 12.6 rad/s2 ω average = 3.15 rad/s

  35. D-SUAVE Spar Materials

  36. D-SUAVE Wing Materials

  37. D-SUAVE Propulsion

  38. D-SUAVE Outrunner vs Gearbox

  39. D-SUAVE Propeller Location

  40. D-SUAVE Selected Motors Assume: ηesc = 95%

  41. D-SUAVE Battery Types

  42. D-SUAVE Electronic Speed Control

  43. D-SUAVE Risk Reduction Experiment • Verify Endurance Requirement • Test entire propulsion system in the ITLL wind tunnel • Test battery capacity • RC Watt Meter • Verify combined motor/prop and ESC efficiencies

  44. D-SUAVE Electronics

  45. D-SUAVE Electronics Flow Chart Electronics/Sensors Options Power Source Requirement Verification Radio Control One Source Two Sources On Board Sensors From Ground Direct to BEC/Servos Flight Dynamics Board Assistance Radar Gun Stop watch and Visual Real Time Data Transmission Recover Recorded Data

  46. Ground Station Setup

  47. Motor Battery ESC/BEC Servos Flight Dynamics Board Receiver GS D-SUAVE Communications Setup

  48. D-SUAVE Onboard Sensors

  49. D-SUAVE Flight Dynamics Board • Dimensions: 4” x 1.25” • Mass: 30 g • Power/Current: ~1.50 W /125 mA • Components • GPS Receiver • XB-Pro TX • Rate Gyro • Microchip • Pressure Gauge • Cost: ~$500

  50. D-SUAVE Servos

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