Abstract
A new aircraft Electro-Hydrostatic Actuator (EHA) of a certain model fighter was designed to meet the braking system under the Aircraft Anti-skid Braking System development background. The paper describes the principle and features of the EHA, and gives the specific requirements of the EHA. In this paper the selection and performance of the motor, pump and hydraulic cylinder were optimized. It focuses on the motor structures and performances, with dual windings, which played a role as the power driver of EHA. The operation characteristics of the dual windings motor have investigated under different conditions. Finally, the paper provide modelling and analysis performance of EHA system and beyond a whole aircraft system.
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