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Lookup NU author(s): Dr Rafal Wrobel, Dr Tom WernerORCiD, Dr Xu DengORCiD
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This paper describes key aspects of the development process of an ultra-lightweight electrical motor for solar-powered high-altitude (20km) platform applications. A radial-flux permanent magnet (PM) machine topology with outer rotor and integrated air-cooling is considered here. The mission profile of the analysed solar-powered aircraft calls for a high-torque overload (×2.5) at take-off and a high-efficiency (>95%) at high altitude cruise operation. Consequently, a finebalance between both operating points needs to be seen when sizing the motor. Here, effective thermal management of the motor at take-off is critical for achieving a compact/lightweight motor design. Further to these, the motor design should enable a simple/cost-effective manufacturing and assembly process, which makes use of the lightweight composite materials for all structural subassemblies. In this work, a careful integration between both active and structural subassemblies of the motor resulted in a significant weight reduction, with contribution of all structural components less than 5% of the overall motor weight. The theoretical and initial experimental results discussed in the paper confirm that the developed motor meets the key design targets. Further evaluation will include the mission specific and aircraft integration aspects, i.e. highaltitude tests, aerodynamic tests and flight tests.
Author(s): Wrobel R, Werner TC, Deng X, Noal D
Publication type: Conference Proceedings (inc. Abstract)
Publication status: Published
Conference Name: 26th International Conference on Electrical Machines ICEM 2024
Year of Conference: 2024
Pages: 7
Acceptance date: 01/05/2024
