GB496054A - Improvements in controls for aircraft - Google Patents
Improvements in controls for aircraftInfo
- Publication number
- GB496054A GB496054A GB14635/37A GB1463537A GB496054A GB 496054 A GB496054 A GB 496054A GB 14635/37 A GB14635/37 A GB 14635/37A GB 1463537 A GB1463537 A GB 1463537A GB 496054 A GB496054 A GB 496054A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cylinder
- aircraft
- pilot
- piston
- horn
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64C—AEROPLANES; HELICOPTERS
- B64C13/00—Control systems or transmitting systems for actuating flying-control surfaces, lift-increasing flaps, air brakes, or spoilers
Landscapes
- Engineering & Computer Science (AREA)
- Automation & Control Theory (AREA)
- Aviation & Aerospace Engineering (AREA)
- Aerodynamic Tests, Hydrodynamic Tests, Wind Tunnels, And Water Tanks (AREA)
- Mechanical Control Devices (AREA)
- Toys (AREA)
Abstract
496,054. Controlling aircraft. ANDREWS, W. R., and SCOTTISH AIRCRAFT & ENGINEERING CO., Ltd. May 26, 1937, No. 14635. [Class 4] An aircraft control includes an overbalanced control surface 1, an auxiliary surface 2 pivoted thereto, pilot-operated means for, and which permits movement under aerodynamic forces of, the surface 1 and means for operating the surface 2 which is arranged so that the surface 2 moves relatively to and in the same direction as the surface 1. As shown, the surface 2 is controlled through a piston-rod 9 connected to a horn 4. The piston carried by the rod 9 moves in a cylinder B pivotally mounted on the aircraft. A horn 3 on the surface 1 is con. nected to a piston moving in a cylinder A and connected to a lever arm 6 controlled by the pilot. Opposite ends of the cylinder A are connected to opposite ends of the cylinder B. The cylinder B is of smaller diameter and longer than cylinder A. The lengths of the links 5, 9 and their points of attachment may be capable of adjustment on the ground for trimming purposes. The mechanism may be duplicated and damping-devices may be inserted in the pilot's controls. Movements of the pistons may be damped.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB14635/37A GB496054A (en) | 1937-05-26 | 1937-05-26 | Improvements in controls for aircraft |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB14635/37A GB496054A (en) | 1937-05-26 | 1937-05-26 | Improvements in controls for aircraft |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB496054A true GB496054A (en) | 1938-11-24 |
Family
ID=10044798
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB14635/37A Expired GB496054A (en) | 1937-05-26 | 1937-05-26 | Improvements in controls for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB496054A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2563757A (en) * | 1945-07-23 | 1951-08-07 | Lockheed Aircraft Corp | All-movable horizontal tail |
| CN114001915A (en) * | 2021-11-02 | 2022-02-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Plate type hinge moment balance |
-
1937
- 1937-05-26 GB GB14635/37A patent/GB496054A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2563757A (en) * | 1945-07-23 | 1951-08-07 | Lockheed Aircraft Corp | All-movable horizontal tail |
| CN114001915A (en) * | 2021-11-02 | 2022-02-01 | 中国空气动力研究与发展中心超高速空气动力研究所 | Plate type hinge moment balance |
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