GPS Vehicle Tracking/Payload Release System For Small UAV

1. GPS Vehicle Tracking/Payload Release System For Small UAV Project Team 02009

2. Project Summary • Motivation for the Project • Objectives: • Accurate Tracking of a UAV • Wireless Data Transmission • Autonomous Function : Drop a Payload

3. Project Requirements • Incorporate GPS technology onto a UAV; RIT Heavy Lift Plane. • Utilize 2-way wireless data transfer. • Graphical position tracking program on base computer. • Coordinates for payload drop site selectable at base computer. • Design a reliable payload retaining/release system. • Confirm payload delivery, required target accuracy: 100ft. • Collect data remotely from the aircraft. • System range: 500 ft. • Weight and volume capacity on board: 17 lbs., 300cc. • Budget: $2000

4. Design Process • Brainstorming/Concept Development Phase • Example: retaining/releasing the payload • Concept 1 : Clamp • Concept 2 : Sliding Pin

5. Design Process • Feasibility Assessment • Questions test feasibility of each concept. • Example: Is the release system strong enough to reliably retain the payload during flight? • Rank the concepts relative to each other • Concept 1:Clasp – rank 2 • Concept 2 : Pin – rank 3 • Plot the rank for each idea with respect to each feasibility question on a radar chart. • The concept with the most area on the plot is the best.

6. Design Process • Concept 2 is the best choice.

7. Release System Components Payload Fin Payload Retainer System Housing / Mount

8. Features of Release Mechanism • Very simple, Few parts • Easy to manufacture • Will be easy to mount to the Heavy Lift Plane with minimal modifications to the plane • System requires little force from actuating mechanism

9. Payload Mold Construction FINISHED PAYLOAD SHELL POSITIVE MOLD

10. Payload • The payload will be made out of a carbon-fiber shell and filled with shock absorbing foam for electronics.

11. DRAG CALCULATIONS • Assume ideal flow for simplified calculations • The total incompressible drag coefficient:

12. Payload Analysis • FEA • The payload is modeled using properties of aluminum. • The force of impact is applied to a flat on the nose of the payload. • The areas of highest stress will be reinforced with extra carbon fiber.

13. Payload FEA

14. Payload Components • Camera electronics • Camera • Transmitter • Battery

15. Video transmission • Considerations for design • Light weight • Size • Minimize drag • Range of transmitter – 500 ft • Robust configuration • Power consumption • Cost • All parts donated by Dr. Arney, CIS

16. Parachute • Design parameters for the parachute • Minimize chute diameter and impact load. • Assumptions • Cd of 0.8 • Payload weight of 2lbs. • Design Choice • Chute Diameter • 31 in. • Descent Velocity • 21 ft/s • Resulting Loading • 5.2 lbs. • 2.5 G’s Optimization of Parachute Surface Area vs. Impact Load

17. Electronic Control System

20. Y VMAV Vlat a X Vlong

21. Conclusion • The Design meets the requirements of the project. • All components will be bought, borrowed, or built next quarter. • The design’s concepts achieve the goal of advancing MAV technology. • This system is a platform for further development.