Patent US4293784A successfully refreshed from Google Patents.
US4530271A
Expired / Lapsed
US
⏱️ 0.0 years remaining
Electric actuator system with hydraulic coupling as protection against mechanical jamming
Assignee: Lockheed Martin Corp
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Filing: 1983-06-21
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Granted: 1985-07-23
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Expires: 2003-06-21
Abstract
Abstract 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.
Inventors
- 👤 Michael J. Cronin
Bibliographic Details
Application Number
—
Jurisdiction
US
Data Source
google_patents
Last Synchronized
2026-11-05 08:17
CPC Classifications
F; F15; F15B; F15B18/00
Claims Analysis
Total Claims: 16
Claim 1
Independent Claim
260 words
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.
Claim 2
Dependent Claim
260 words
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.
Claim 3
Dependent Claim
21 words
The actuator assembly as set forth in claim 1 wherein said sealing member is a piston slidably mounted within said cylinder.
Claim 4
Dependent Claim
55 words
The actuator assembly as set forth in claim 2 wherein one of said pair of connecting members is an output shaft coupled to said piston and to said control surface and said other one of said pair of connecting members is an input shaft coupled to said cylinder and said output shaft of said actuator.
Claim 5
Dependent Claim
51 words
The actuator assembly as set forth in claim 2 wherein one of said pair of connecting members is coupled to said piston and said output shaft of said actuator and said other one of said pair of connecting members is an output shaft coupled to said cylinder and said control surface.
Claim 6
Dependent Claim
33 words
The actuator assembly as set forth in claim 3 or 4 wherein a sleeve is mounted to said aircraft structure, and said hydraulic cylinder is at least partially slidably mounted within said sleeve.
Claim 7
Dependent Claim
20 words
The actuator assembly as set forth in claim 5 wherein said valve means is a normally closed solenoid operated valve.
Claim 8
Dependent Claim
16 words
The actuator assembly as set forth in claim 1 wherein said actuator is a rotary actuator.
Claim 9
Dependent Claim
66 words
The actuator assembly as set forth in claim 7 wherein said sealing member is a vane rotatably mounted within said cylinder, and one of said coupling members is an input shaft coupled to said vane and to said output shaft of said rotary actuator and said second of one of said coupling members is a flange attached to said hydraulic cylinder and to said control surface.
Claim 10
Dependent Claim
20 words
The actuator assembly as set forth in claim 8 wherein said valve means is a normally closed solenoid actuated valve.
Claim 11
Dependent Claim
210 words
An actuator assembly for an aircraft having a fixed structure to which a movable control surface is mounted thereto comprising: a supporting frame attached to said structure; a rotary actuator mounted to said frame, said actuator having a threaded output shaft; a hydraulic coupling comprising: at least one hydraulic cylinder movably mounted to said frame, said at least one hydraulic cylinder filled with a substantially incompressible fluid; a piston movably mounted within said at least one hydraulic cylinder and dividing said at least one hydraulic cylinder into first and second portions; a piston rod coupled to said piston and having an end protruding out of said at least one hydraulic cylinder; passage means connecting said first and second portions of said at least one hydraulic cylinder; and valve means mounted in said passage means, said valve means having a first position sealing off said first portion to a second portion connecting said first and second portions; a translating nut assembly movably mounted to said threaded output shaft and to said piston rod, said nut adapted to translate along the length of said threaded output shaft upon rotation of said output shaft; and a member connected to said at least one hydraulic cylinder adapted to couple to said movable control surface.
Claim 12
Dependent Claim
210 words
An actuator assembly for an aircraft having a fixed structure to which a movable control surface is mounted thereto comprising: a supporting frame attached to said structure; a rotary actuator mounted to said frame, said actuator having a threaded output shaft; a hydraulic coupling comprising: at least one hydraulic cylinder movably mounted to said frame, said at least one hydraulic cylinder filled with a substantially incompressible fluid; a piston movably mounted within said at least one hydraulic cylinder and dividing said at least one hydraulic cylinder into first and second portions; a piston rod coupled to said piston and having an end protruding out of said at least one hydraulic cylinder; passage means connecting said first and second portions of said at least one hydraulic cylinder; and valve means mounted in said passage means, said valve means having a first position sealing off said first portion to a second portion connecting said first and second portions; a translating nut assembly movably mounted to said threaded output shaft and to said piston rod, said nut adapted to translate along the length of said threaded output shaft upon rotation of said output shaft; and a member connected to said at least one hydraulic cylinder adapted to couple to said movable control surface.
Claim 13
Dependent Claim
15 words
The actuator assembly of claim 10 including said frame being of a hollow cylindrical shape.
Claim 14
Dependent Claim
33 words
The actuator assembly as set forth in claim 11 including said hydraulic coupling having an annular opening and said rotary actuator at least partially mounted within said annular opening of said hydraulic coupling.
Claim 15
Dependent Claim
24 words
The actuator assembly as set forth in claim 12 wherein movement of said at least one hydraulic coupling is guided by said cylindrical frame.
Claim 16
Dependent Claim
19 words
The actuator assembly as set forth in claim 13 wherein said valve is a normally closed solenoid actuated valve.
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USPTO Annuity & Maintenance Windows
| Annuity Stage | Window Opens | Payment Deadline | Surcharge Period Until | Estimated Fee | Status |
|---|---|---|---|---|---|
| 3.5 Years (Year 4) | 1988-07-22 | 1989-01-21 | 1989-07-23 | $2000.00 | Window Closed / Lapsed |
| 7.5 Years (Year 8) | 1992-07-22 | 1993-01-21 | 1993-07-23 | $3760.00 | Window Closed / Lapsed |
| 11.5 Years (Year 12) | 1996-07-22 | 1997-01-21 | 1997-07-23 | $7700.00 | Window Closed / Lapsed |