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This paper describes the design, construction and testing of a dual-output power converter concept where the large components, such as the DC link capacitor and heat-sink, are shared between two actuators which are used sequentially in the deployment of aircraft landing gear. This mutual component approach combines the advantages of dual-use power converters with the flexibility of one power converter per application. Practical results of the converter operating are presented for a range of test conditions in order to validate the simulation study.

One of the most recent trends in the aerospace industry is the increased use of electrical power in place of hydraulic, pneumatic and mechanical power. This paper presents an analytical and experimental feasibility study regarding the application of an electro-mechanical actuator (EMA) for the aileron of an aircraft using a real flight profile as a reference. The analysis is focused on the input power flow of the actuator converter, showing that the total amount of energy that would be regenerated into the aircraft power network is small and that the use of a bi-directional power flow converter has the advantage of reducing the size of the braking circuit. The investigation is carried out assuming a two stage matrix converter as the candidate power conversion topology. However many of the conclusions are equally applicable to other conversion topologies that are capable of bidirectional power flow.

This paper considers a wide range of options for the allowing regeneration onto the aircraft bus for possible inclusion in future aircraft power quality specifications. For many loads, such as actuators, the size and weight of power converters could be significantly reduced if the requirement to avoid regeneration was removed from the specifications.