Electric Control Surface Actuator Design Optimization and Allocation for the More Electric Aircraft

This work pertains to the optimization of electric actuators for the primary and secondary flight control surfaces of a More Electric Aircraft. Electrohydrostatic and electromechanical actuators are considered and optimized in accordance with the flight loads and actuator requirements identified in a separate work by the same authors. For the purposes of this work, the Boeing 737-800 aircraft is chosen as a test case. However the methodology is general and can be applied to any existing design or proposed design concept. Once the optimized actuator designs are obtained, the possibility of using both actuator types by allocating them to control surfaces on the basis of reliability requirements is considered.

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