GB207867A - Improvements in hydraulically actuated mechanism applicable for use in the control gear of aeroplanes and for other purposes - Google Patents
Improvements in hydraulically actuated mechanism applicable for use in the control gear of aeroplanes and for other purposesInfo
- Publication number
- GB207867A GB207867A GB24133/22A GB2413322A GB207867A GB 207867 A GB207867 A GB 207867A GB 24133/22 A GB24133/22 A GB 24133/22A GB 2413322 A GB2413322 A GB 2413322A GB 207867 A GB207867 A GB 207867A
- Authority
- GB
- United Kingdom
- Prior art keywords
- piston
- valve
- pressure liquid
- purposes
- aeroplanes
- 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)
- Hydraulic Motors (AREA)
Abstract
207,867. English Electric Co., Ltd., and Manning, W. O. Sept. 6, 1922. Hydraulic transmission of power; liquidpressure engines. - Hydraulic mechanism for operating the tail plane of an aeroplane or for other purposes comprises a motor cylinder 6, Fig. 1, connected through a valve casing 5 and a reversing valve 3 with a manually operated or power pump or pumps 1, leakage being replenished from a, tank 9 through suction valves 10, 11. The valve casing of the motor cylinder contains spring-closed valves 46, 47, Fig. 3, either of which may be opened by the pressure liquid to allow the liquid to act on one side of the piston 20, the pressure liquid simultaneously acting through a piston 58 to open the other valve to put the other side of the piston to exhaust. In order to prevent damage through continued pumping after the piston has reached the end of its stroke, the cylinder is provided at each end with an opening uncovered by the piston immediately before the end of the stroke, so that the pressure liquid may pass through this opening and a spring- closed by-pass valve to the exhaust.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB24133/22A GB207867A (en) | 1922-09-06 | 1922-09-06 | Improvements in hydraulically actuated mechanism applicable for use in the control gear of aeroplanes and for other purposes |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB24133/22A GB207867A (en) | 1922-09-06 | 1922-09-06 | Improvements in hydraulically actuated mechanism applicable for use in the control gear of aeroplanes and for other purposes |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB207867A true GB207867A (en) | 1923-12-06 |
Family
ID=10206894
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB24133/22A Expired GB207867A (en) | 1922-09-06 | 1922-09-06 | Improvements in hydraulically actuated mechanism applicable for use in the control gear of aeroplanes and for other purposes |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB207867A (en) |
-
1922
- 1922-09-06 GB GB24133/22A patent/GB207867A/en not_active Expired
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