Document Type

Restricted Campus Only

Publication Date

4-2012

Abstract

The scope of the design project FALCON (Free-ranging Airborne Lightweight Camera OperatioN) was to design an aerial photography system (APU) to capture high­definition photographs at multiple angles from altitudes up to 30 meters. The final design was split into four subsystems: the chassis or lifting mechanism, image capture and image retrieval, camera mounting system and the emergency velocity reduction device (EVRD). The image capture and retrieval and camera mounting system were prototyped to accommodate alternative chassis options in case the chassis solution did not effectively meet the design criteria and constraints. However, the quad-copter did uphold as a successful chassis design. The EVRD subsystem provides additional safety if the design is permitted to be used in populated areas. Finally, this report discusses the departmentalized construction and testing of each subsystem prototype.

The final proposal for the subsystem prototypes consists of a quad-copter for the chassis, GoPro HD Hero Naked model camera for point-and-shoot image capture, memory card and wireless transmission combination for image retrieval, camera mounting system rotated with digital servo, and four electrically triggered parachutes for the EVRD. Further details and current status of the components selected for each of these subsystems are provided in the Methods and Results sections of this report.

Construction and testing has been completed for all subsystems; however, integration of the subsystems and some of the secondary goals were not accomplished. The chassis requires new propellers for further fine-tuning and successful horizontal test results. The final testing of image capture and retrieval subsystem requires a triggering device for wireless transmission of snap-shot or burst fire image capture. The camera mount requires a separate radio control transmitter and receiver to achieve the secondary performance goals. The EVRD requires a trigger mechanism to remotely release the parachutes from the casing. A servo or solenoid mechanism is under development to complete this subsystem prototype. The current budget, WBS schedule, list of vendors and bill of materials for the overall prototype are included in the Appendices. The constructed prototype met most of the requirements as demonstrated by outcome of the selected tests associated with each of the subsystems.

Comments

Dr. Enright, Advisor

ENGR 4382 Design VIII

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