Electromechanical Actuation Feasibility Study

Abstract
An alternate to hydraulic actuation of primary flight control surfaces is desirable. Electromechanical actuation of primary flight controls is feasible and practical using the most recent advances in the state-of-the-art in magnetic materials for high-performance servomotors, high-current-capacity transistor switches for motor power control, and digital microprocessors for servo and redundancy management logic. Electromechanical actuation is consistent with current, proven, fly-by-wire technology and with the developing power-by- wire techniques. The control surface performance requirements and methods of analysis are presented for direct drive electromechanical power servos. Trade studies were conducted to evaluate the aircraft power source and distribution options; actuator motor and controller options; and geared rotary hinge actuator configuration options. A weight comparison is given between the hydraulic actuation system for the F-100 and the electromechanical system studied. Reliability assessments and redundancy management considerations also are included. A preliminary design of the electromechanical actuation system and test plan are presented. These data were developed using a selected baseline problem statement which was derived from existing hydraulic actuator specifications.

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