Patent ID: 8033509
Filing Date: 2011-10-11
Classification: B64C,Y02T

Abstract:
1. An aircraft flight control surface actuation system, comprising: an electromechanical actuator assembly adapted to be selectively supplied with electrical current and, upon receipt of the electrical current, to supply a force to a flight control surface; a hydraulic actuator assembly adapted to selectively receive a supply of hydraulic fluid and, upon receipt of the hydraulic fluid, to supply a force to the flight control surface; a hydraulic actuator control adapted to receive a position command signal representative of a commanded flight control surface position and operable, in response thereto, to control the supply of hydraulic fluid to the hydraulic actuator assembly; and an electromechanical actuator control operable to control the electrical current supplied to, and thus the force supplied by, the electromechanical actuator assembly, the electromechanical actuator control including: