초록 ▼

An actuator system for controlling the position of an aerodynamic control surface of an aircraft, such as an aileron, is disclosed. An actuator (12) having an output shaft (14) is mounted to a frame attached to the aircraft structure. A hydraulic coupling (32) is mounted on one side to the output sh

An actuator system for controlling the position of an aerodynamic control surface of an aircraft, such as an aileron, is disclosed. An actuator (12) having an output shaft (14) is mounted to a frame attached to the aircraft structure. A hydraulic coupling (32) is mounted on one side to the output shaft (14) of the actuator (12) and the other side to the control surface (50) and comprises a hydraulic cylinder (34) having a sealing member (36) movably mounted therein dividing the cylinder (34) into two portions (38, 40). The output shaft (14) of the actuator (12) is coupled to the cylinder (34) and an output shaft is attached to the sealing member (36) at one end and at its opposite end to the control surface or vice versa. A connecting tube (54) is provided coupling the two portions of the hydraulic cylinder together. The tube incorporates a valve (58) having a first position sealing off the two portions from each other and a second position providing a passageway therebetween. Thus, if the actuator (12) is working and the valve (56) is closed, an essentially solid connection is achieved between the actuator (12) and the control surface (50), thus allowing the actuator to move the control surface upon command. Should the actuator fail, the valve (56) can be opened, allowing fluid to flow from portion to portion. Thus, a redundant actuator can continue to control the position of the control surface while the disabled actuator is effectively decoupled from the control surface for the piston (36) will just move back and forth within the cylinder (34) as the control surface moves.

대표청구항 ▼

An actuator assembly for an aircraft having a fixed structure to which a movable control surface is mounted comprising: a supporting frame attached to said structure; an actuator mounted to said frame, said actuator having an output shaft; a hydraulic coupling comprising: a hydraulic cylinder movabl

An actuator assembly for an aircraft having a fixed structure to which a movable control surface is mounted comprising: a supporting frame attached to said structure; an actuator mounted to said frame, said actuator having an output shaft; a hydraulic coupling comprising: a hydraulic cylinder movably mounted to said structure, said hydraulic cylinder filled with a substantially incompressible fluid; a pair of connecting members coupled to said hydraulic cylinder, one of said pair of connecting members coupled to said output shaft of said actuator and the other of said pair of connecting members coupled to said control surface; a sealing member movably mounted in said cylinder, dividing said cylinder into first and second portions, said sealing member cooperating with said fluid to prevent relative movement between said pair of connecting members; passage means connecting said first and second portions of said cylinder; and valve means mounted in said passage means, said valve means having a first position sealing off said first and second portions from each other and a second position coupling said first and second portions together; such that when said valve is in the first position, relative movement between the pair of connecting members is prevented and a substantially solid coupling is made between said actuator and said control surface and when said valve is in the second position the sealing member is free to move relative to said cylinder and, thus, said pair of connecting members are movable with respect to each other, thus allowing the movement of said control surface regardless of actuator output shaft position.