Patent ID: 8678694
Filing Date: 2014-03-25
Classification: B64C,Y02T,Y10T

Abstract:
1. An aircraft reaction link as a constituent component of an actuator for driving a control surface of an aircraft is coupled to a hydraulically driven cylinder whose one end is attached pivotably to the control surface or to a horn arm member attached to the control surface, the aircraft reaction link comprising: a pair of linear portions disposed alongside each other and each extending linearly; a coupling portion connecting to one end of each of the pair of linear portions on the same side via a bent portion and extending so as to couple the one end of each of the pair of linear portions on the same side to each other; a fulcrum shaft attachment portion that is provided so as to protrude from a center portion of the coupling portion, the fulcrum shaft attachment portion is pivotably attachable to a fulcrum shaft for rotatably supporting the control surface; and a cylinder attachment portion that is provided as the other end of each of the pair of linear portions and pivotably attachable to the other end of the cylinder via a pivot shaft, wherein a metal frame that is made of a metallic material and is provided so as to extend across the coupling portion and the pair of linear portions and a composite frame made of fiber-reinforced plastic is provided so as to extend at least in the pair of linear portions are bonded together, whereby the pair of linear portions and the coupling portion are formed, and the metal frame is provided so as to extend from the fulcrum shaft attachment portion to the cylinder attachment portion.