1. UAV Research International “Providing integrated consultation to MAV project engineers at Eglin AFB” Chris McGrath Neil Graham Alex von Oetinger John Dascomb Sponsor : Dr. Gregg Abate December 6, 2005

2. OVERVIEW  Problem Statement  Design Specifications  Project Planning  Design Selection  Procedure for Design  Cost Analysis  Spring Proposal  Conclusion

3. Problem Statement  To design a means of testing MAV flight dynamics in an indoor facility

4. Project Specs  Weight  100 – 200 grams (g)  Flight Speed  0 – 25 meters per second (m/s)  Exterior Material  Carbon Fiber Composite  Wing Tip Length  15 – 30 centimeters (cm)  MAV Flight Control  Both 2 and 3 axis  Type of Thrust  Pusher, Puller, None

5. Design Selection: Free Flight Wind Tunnel  The free flight wind tunnel has been successfully created before  Design is basically a conventional wind tunnel modified to allow for actual free flight of the test subject  Force balance achieved around the center of gravity of the MAV, essentially canceling out the force from the incident wind tunnel flow with the thrust of the engine

6. Project Planning  Final design analysis divided into 3 section: –Tunnel geometry  Design of wind tunnel ducting  Selection of fan flow  Settling screen and honeycomb selection –Instrumentation  Onboard measurement  Data collection/display –MAV handling  Control and release of the MAV inside the tunnel

7. Project Planning: Flow Chart

8. Design Procedure  Design Procedure is broken down into five main sections: –Wind Tunnel Design –Flow Quality –Flow Fan –Instrumentation –MAV Handling

9. Wind Tunnel Design  In wind tunnel design Three properties are most important to consider: –Test section Dimensions –Flow quality –Tunnel geometry

10. Wind Tunnel Design: Test section Dimensions  At its maximum area, wind tunnel must be 6 times that of the test section  The test section should give ample area for the MAV to fly  For the minimum analysis of the flight, the MAV needs to move laterally or vertically twice its wingspan

11. Wind Tunnel Design: Test section Dimensions (continued)  For the largest MAV (12” wingspan) to be tested in tunnel we would need 2 feet of flying area in any given direction or roughly a 4ft x 4ft test section  When moving longitudinally against the flow we will allow for 10ft of movement for the MAV

12. Wind Tunnel Design: Flow Quality  The quality of the flow for our application is based on velocity fluctuations in the direction of the airflow  Need a flow quality that has velocity fluctuations of less than 1% of the free flow  Screens and a honeycomb are implemented to take out the rotational and velocity fluctuations of the flow that form when the air passes through the fan

13. Wind Tunnel Design: Flow Quality (Continued)  The most important factor to flow quality is the contraction ratio  The larger the contraction ratio, the slower the air flow is when it passes through the screens and honeycomb  For a contraction ratio of 6, combined with the screens and honeycomb, we can achieve a flow quality of less than 1%

14. Wind Tunnel Design: Tunnel Geometry  Two different tunnel Geometries are explored –Ideal wind tunnel –Constrained wind tunnel

15. Wind Tunnel Design: Tunnel Geometry – Ideal tunnel  Larger tunnel overall  Utilizes full test section and contraction ratio  Implements a 4.5*4.5 ft test section to compensate for Boundary phenomenon ( only 80% of area is usable)  Test section has length of 10 ft

16. Wind Tunnel Design: Tunnel Geometry – Ideal tunnel (continued)  *ADD ADDITIONAL INFO*

17. Wind Tunnel Design: Tunnel Geometry – Constrained tunnel  Designed to fit inside the space currently provided at Eglin AFB (room measuring 40x30x15 ft )  Only aspect of the ideal tunnel that is too large for the room is the tunnel length  Need to shorten the tunnel by 21.3 ft

18. Wind Tunnel Design: Tunnel Geometry – Constrained tunnel (Continued)  *ADD ADDITIONAL INFO*

19. Flow Quality  Flow quality will be of paramount importance in tunnel design

20. Free Flight Diagram

21. Wind Tunnel Geometry  Area required to fly 4 ft x 4 ft  Test section area is 4.5 ft x 4.5 ft  Test section length greater than 10 ft

22. Wind Tunnel Geometry  Fan Specifications –Mass flow rate: 60.8 kg/s –Ideal power needed: 50 hp –Diameter of fan: 7.1 ft

23. Wind Tunnel Geometry  Final Expansion –Final area is 8 times test section area

24. Wind Tunnel Geometry

25. Tether System  Tether Location  Tether Restraint and Release System  Tether Reel

26. Tether Location  Above and below MAV’s center of mass

27. Restraint and Release System  Tether Clamp

28. Tension Reel  Miyamae's Command X-1

29. Instrumentation  Onboard  Flow Measurement  Data Collection Software

30. Onboard Instrumentation  Kestrel Autopilot –16.65 grams (2” x 1.37” x.47”) –Three-axis rate gyros –Accelerometers –Air pressure sensors

31. Flow Measurement  Pitot-Static Tube  Hot-Wire Anemometer

32. Data Collection Software  Virtual Cockpit  Labview

33. On-Going Activities  Source the Fan  Find manufacturer to produce settling screens  Create Bill of Materials  Build Pro-E model of system