1. Team Shane Stumvoll, Alex Willard, Robert Yarnell, Hubert Jayakumar, Tim Teal

2. Objectives Flapping wing micro-aerial vehicle 15 cm max diameter Stable hover/basic maneuvers Endurance necessary to demonstrate flight performance

3. Currently, there is a large push in technology for military and civilian air vehicles toward smaller, more maneuverable unmanned aerial vehicles. Flapping wing vehicles have potential advantages over fixed-wing and rotorcraft. Motivation

4. Flapping Vs. Fixed and Rotor Fixed-wing: Movement of the wings in relation to the aircraft are not used to generate lift. Rotorcraft uses lift generated by wings that revolve around a mast. Ornithopter Wings provide both lift and thrust from flapping motion Pros Superior Maneuverability and Performance Smaller Wings Needed for flight Lift greater than fixed wing Cons Less Stable Flight Directional controls are hard to map

5. Flapping mechanism Two options Four bar design Linear actuator Link Lengths determined analytically Output angle and velocity a function of input angle, velocity, and link lengths

6. Power System Control mechanism Flapping mechanism Control electronics Material Approach

7. Conclusion and Summary Design and build a flapping wing MAV The flapping wings provide more lift per unit span allowing for smaller wings that will be able to lift the same weight Decide on the best power supply to use Look at the different current designs Use resources on and off campus to help

8. Summer Work Additional resources gathered 4 bar length requirements for scaled model complete 4 bar system prototype complete

9. Next Step Build scaled up model Use scaled model to create pro E and simplified Ansys design