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1. Management, systems integration and reporting

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  1. 1. Management, systems integration and reporting 2011 Daniel, Matt, Tony, Sam, Mayur

  2. Mission Task • Search and rescue UAV • Requirements

  3. Allocations of Groups & Members • 1. Management • 2. Mayur - Payload & Electrical Power • 3. Matt - Aerodynamics • 4. Daniel - Structures • 5. Sam - Propulsions • 6. Tony - Weights and Balance • 7. Matt - Launch & Retrieval

  4. Communications • Overall group meeting • Management meeting • Management attending sub group meetings

  5. Resolving conflict • Good vs bad • Optimal design vs realistic

  6. Payload and Electronics Payload Design

  7. Payload - Contents • One man life raft • EPIRB • Flares • Heliograph • Food Supplies • 1.2L water • Heat Packs • Torch • Circuitry for lights

  8. Payload - Final Design

  9. Payload - Final Design

  10. Payload - Final Design

  11. Payload - Layout

  12. Payload - Final Design

  13. Payload - Dropping and Retrieval • The payload is dropped to land upwind of the person • This means the wind will push it back towards the person • A rope follows the payload with a drogue, landing near the person for retrieval •  The person can then access everything that is stored in the payload,  which is attached with velcro

  14. Payload and Electronics Autopilot and Flight Control

  15. Mission Computer Decides where to fly Is responsible for communications Searches for person (via FPGA) Flight Computer  Controls the aircraft Gets info from sensors Continually monitors location/speed/attitude Autopilot System

  16. Search Pattern

  17. Search Pattern

  18. Electronic Connections

  19. Payload and Electronics Control and Comms

  20. Control Requires +-20 degree deflection 4 bar linkage chosen, directly driven by servo Servo mounted inside wing, linkage mount attached directly to the surface of the flap.  Battery Powered. Chosen for relatively light weight and small size compared to alternatives: hydraulic actuators, direct rotation For greater range of motion, or higher torque, gearing can be be implemented for relatively small weight gain.

  21. For wing servo PS-105, high torque servo 35Nm, +-45 degree range of motion, requires 18 W each For tail servo, K-2000 servo, 10 Nm torque, +-45 degrees of motion, requires 9 W each For throttle, Futaba Brushless servo, 3Nm torque, low power requirements.

  22. Flap Actuator

  23. Radio Broadcast Direct Line of sight impossible at search height Typical video surveillance (Ku, C and S) bands affected by rain Broadcast in L Band to avoid effects of Rain fade Satellite phone for telemetry broadcast 1.5" square Iridium Antenna for receiving signal RF unit to receive radio signal close to ship for direct control in case of emergency

  24. h =781m above search height of 200m L = 100km no change to range

  25. Telemetry Sent During normal flight Status(Cruise, Search, Loiter, Return)Location (from Gps) SpeedAltitude Distance to search area During search As above plus wind speed For positive identification, photo location Sends 50 by 50 pixel relevant section of photo to minimise bandwidth Termination protocol Ship sends confirmation signal every 10 seconds, if UAV loses contact for 10 minutes vehicle will terminate. If ship is not receiving telemetry, ie. satellite link down, will send instruction to UAV to re-establish uplink every 10 seconds, if UAV continues to receive this signal for 10 minutes will terminate.

  26. Telemetry Display

  27. Group 4 Structures Leo Pasukov Thomas Slee Amanda Neal NabilChowdhury NayeemChowdhury

  28. Initial wing structure for first iteration structural analysis

  29. A representation of the complete wing and fuselage attachment system

  30. Initial Fuselage Design to accommodate payload and air cannon launch with pusher propellers located under the wing facing the back of the vehicle

  31. Hermes 450 on left and RQ7 Shadow on right

  32. Structural components of the Fuselage

  33. Modification of fuselage for payload and wing

  34. Forces acting on the Fuselage

  35. Stresses on the fuselage

  36. Total Deformation on Fuselage Structure

  37. Forces and moments acting on the Motor Mount

  38. Determining the total deflection of the Motor Mount and equivalent Stress of Motor Mount

  39. The general shape of the inverted V-tail

  40. The ruddervators end before the apex of the inverted V, and provide the design with some aesthetics.

  41. The internal structure of the tail

  42. Screws hold the boom and tail structure together via these screw holes

  43. Layout Drawing Wing

  44. Layout Drawing Wing Mount

  45. Layout Drawing Fuselage

  46. Layout Drawing: Motor Mount