Date on Honors Thesis

Spring 4-29-2025

Major

Engineering Physics

Examining Committee Member

Dr. Theodore Thiede, Project Advisor

Examining Committee Member

Dr. Gheorghe Bunget, Committee Member

Examining Committee Member

Dr. Jake Hildebrant, Committee Member

Abstract/Description

Vertical Take-off and Landing (VTOL) airplanes provide a great degree of flexibility in mission type, as they combine the landing ability of a helicopter with the range of an airplane. This paper describes the design, implementation, and testing of the control system for just such a vehicle. Due to its non-typical motor configuration, there is an unbalanced torque on the frame. Two control methods are suggested and tested to balance this torque, and a PID controller with a high I gain is selected. Furthermore, the distance of the pods from the centerline is calculated and set at 14 inches. A number of tests are designed and performed to ensure functionality of all components, as well as to measure their capability. There is discussion and simulation of multiple transition styles from hover to horizontal flight, and an instantaneous-angle transition is implemented. The transition is tested through multiple flights and the simulation is verified. The transition from horizontal flight to hover is discussed and implemented, and shown to save the vehicle from crashing in its first use. Its rise time (that is, the time to reach 90% of final value) is measured to be 0.467 seconds, with the time to steady-state being 0.7 seconds. Finally, improvements to both the control system and the control circuitry are suggested.

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