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

Project Summary ► Motivation for the Project ► Objectives:  Accurate Tracking of a UAV  Wireless Data Transmission  Autonomous Function : Drop a Payload

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

Design Process ► Brainstorming/Concept Development Phase  Example: retaining/releasing the payload ► Concept 1 : Clamp ► Concept 1 : Clamp ► Concept 2 : Sliding Pin

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.

Design Process ► Concept 2 is the best choice.

Payload Fin Payload Retainer System Housing / Mount Release System Components

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

Payload Mold Construction POSITIVE MOLDFINISHED PAYLOAD SHELL

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

DRAG CALCULATIONS ► Assume ideal flow for simplified calculations ► The total incompressible drag coefficient: Parameter Aero Team Senior Team CFD CLCLCLCL CDCDCDCD D 1.5 (lb) 1.69 (lb) (lb) L 27.7 (lb) (lb)

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.

Payload FEA

Payload Components ► Camera electronics  Camera  Transmitter  Battery

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

Parachute ► Design parameters for the parachute  Minimize chute diameter and impact load.  Assumptions ► C d 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

Electronic Control System

V MAV V long  X V lat Y

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.