Integration and power management of turbo-electric propulsion for multirotor UAV
Abstract
The rapidly growing and continually evolving unmanned aircraft system market demands performance innovations in aircraft versatility, maneuverability, payload, range and endurance. Standard, fully electric designs with vertical takeoff capabilities are extremely limited in endurance and payload capacity by large, heavy batteries. This novel turbo-electric solution uses a small gas turbine engine to drive a generator to supply power for lift and propulsion systems as well as fulfill other onboard power requirements. However, this proposed system requires, high electrical efficiency, as well active throttle control, generator load management, and power conditioning to accommodate the rapid electrical load fluctuations characteristic to multirotor aircraft. This poster outlines the physical integration of a turbo electric power system onto a dodecacopter platform, the development of an active turbine throttle controller, and the evaluation of a bi-directional DC-AC converter to control and condition the electrical power generated to allow the power system to meet the fluctuating power demand of a multirotor.
Citation
Thomas, R., & Rouser, K. (2021, April). Integration and power management of turbo-electric propulsion for multirotor UAV. Poster session presented at the Oklahoma State University Wentz Research Scholars Symposium, Stillwater, OK.