SIMULATION OF A PROTOTYPE ELECTRICALLY POWERED INTEGRATED ACTUATOR FOR CIVIL AIRCRAFT

Developments in the design and proposed operation of large civil aircr aft have resulted in aircraft manufacturers and equipment suppliers de veloping new system concepts, one of which is the all or more electric aircraft. In the all or more electric aircraft the distribution of po wer for flight actuation will be through the electrical system, as opp osed to the currently used bulk hydraulic system. In order to implemen t power-by-wire, high-performance electrically powered actuators will be required. The paper discusses the design details, and the simulatio n of an electrohydrostatic actuator suitable for use in primary flight control systems of a civil aircraft. The paper presents experimental and simulation results, and identifies the parameters that will critic ally affect the performance of an actuator.