UAV Research International Providing integrated consultation to MAV
- Slides: 34
UAV Research International “Providing integrated consultation to MAV project engineers at Eglin AFB” Chris Mc. Grath Neil Graham Alex von Oetinger John Dascomb Sponsor : Dr. Gregg Abate December 6, 2005
OVERVIEW § § § § Problem Statement Design Specifications Project Planning Design Selection Procedure for Design Cost Analysis Spring Proposal Conclusion
Problem Statement § To design a means of testing MAV flight dynamics in an indoor facility
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
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
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
Project Planning: Flow Chart
Design Procedure § Design Procedure is broken down into five main sections: – Wind Tunnel Design – Flow Quality – Flow Fan – Instrumentation – MAV Handling
Wind Tunnel Design § In wind tunnel design Three properties are most important to consider: – Test section Dimensions – Flow quality – Tunnel geometry
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
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 4 ft x 4 ft test section § When moving longitudinally against the flow we will allow for 10 ft of movement for the MAV
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
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%
Wind Tunnel Design: Tunnel Geometry § Two different tunnel Geometries are explored – Ideal wind tunnel – Constrained wind tunnel
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
Wind Tunnel Design: Tunnel Geometry – Ideal tunnel (continued) § *ADD ADDITIONAL INFO*
Wind Tunnel Design: Tunnel Geometry – Constrained tunnel § Designed to fit inside the space currently provided at Eglin AFB (room measuring 40 x 30 x 15 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
Wind Tunnel Design: Tunnel Geometry – Constrained tunnel (Continued) § *ADD ADDITIONAL INFO*
Flow Quality § Flow quality will be of paramount importance in tunnel design
Free Flight Diagram
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
Wind Tunnel Geometry § Fan Specifications – Mass flow rate: 60. 8 kg/s – Ideal power needed: 50 hp – Diameter of fan: 7. 1 ft
Wind Tunnel Geometry § Final Expansion – Final area is 8 times test section area
Wind Tunnel Geometry
Tether System § Tether Location § Tether Restraint and Release System § Tether Reel
Tether Location § Above and below MAV’s center of mass
Restraint and Release System § Tether Clamp
Tension Reel § Miyamae's Command X-1
Instrumentation § Onboard § Flow Measurement § Data Collection Software
Onboard Instrumentation § Kestrel Autopilot – 16. 65 grams (2” x 1. 37” x. 47”) – Three-axis rate gyros – Accelerometers – Air pressure sensors
Flow Measurement § Pitot-Static Tube § Hot-Wire Anemometer
Data Collection Software § Virtual Cockpit § Labview
On-Going Activities § Source the Fan § Find manufacturer to produce settling screens § Create Bill of Materials § Build Pro-E model of system
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