1. Management, systems integration and reporting

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

24. 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

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

26. 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.

27. Telemetry Display

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

31. Initial wing structure for first iteration structural analysis

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

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

34. Hermes 450 on left and RQ7 Shadow on right

35. Structural components of the Fuselage

36. Modification of fuselage for payload and wing

37. Forces acting on the Fuselage

38. Stresses on the fuselage

39. Total Deformation on Fuselage Structure

40. Forces and moments acting on the Motor Mount

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

42. The general shape of the inverted V-tail

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

44. The internal structure of the tail

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

47. Layout Drawing Wing

48. Layout Drawing Wing Mount

49. Layout Drawing Fuselage

50. Layout Drawing: Motor Mount