GB565463A - Improvements in aircraft fluid pressure remote control systems - Google Patents
Improvements in aircraft fluid pressure remote control systemsInfo
- Publication number
- GB565463A GB565463A GB10839/41A GB1083941A GB565463A GB 565463 A GB565463 A GB 565463A GB 10839/41 A GB10839/41 A GB 10839/41A GB 1083941 A GB1083941 A GB 1083941A GB 565463 A GB565463 A GB 565463A
- Authority
- GB
- United Kingdom
- Prior art keywords
- pump
- injector
- reservoir
- control systems
- pipe
- 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
- B64C25/00—Alighting gear
- B64C25/02—Undercarriages
- B64C25/08—Undercarriages non-fixed, e.g. jettisonable
- B64C25/10—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
- B64C25/18—Operating mechanisms
- B64C25/22—Operating mechanisms fluid
Abstract
565,463. Hydraulic control systems. DOWTY EQUIPMENT, Ltd., and BURKE, P. W. Aug. 25, 1941, No. 10839. [Class 69 (ii)] [Also in Group XXVIII] To ensure correct action without cavitation of a liquid supply system for operating hydraulic motors on aircraft an injector device is arranged between the reservoir 11 of the fluid supply system and the pump 3 which is preferably of the kind described in Specifications 534,847, 524,384, 524,199, [all in Group XXVIII]. As applied to a power system such as described in Specification 531,465 in which jacks 17 are operated from the pump 3 under the control of a valve 16, the outlet pipe 15 of the pump 3 is connected to the injector nozzle 21, which draws fluid from a pipe 10 connected to the reservoir 11 and delivers it to the inlet 4 of the pump 3. The injector thus acts as a booster. The pump is provided with a centrifuge return outlet 14 connected by a pipe 23 to the reservoir which acts to cool the pump. The circuit may include an additional injector 24 which supplies a low pressure hydraulic motor 25 under control of a, valve 26.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB10839/41A GB565463A (en) | 1941-08-25 | 1941-08-25 | Improvements in aircraft fluid pressure remote control systems |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB10839/41A GB565463A (en) | 1941-08-25 | 1941-08-25 | Improvements in aircraft fluid pressure remote control systems |
Publications (1)
Publication Number | Publication Date |
---|---|
GB565463A true GB565463A (en) | 1944-11-13 |
Family
ID=9975271
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB10839/41A Expired GB565463A (en) | 1941-08-25 | 1941-08-25 | Improvements in aircraft fluid pressure remote control systems |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB565463A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2181494A (en) * | 1985-10-03 | 1987-04-23 | Draegerwerk Ag | Piston dosing pump for a fluid |
-
1941
- 1941-08-25 GB GB10839/41A patent/GB565463A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2181494A (en) * | 1985-10-03 | 1987-04-23 | Draegerwerk Ag | Piston dosing pump for a fluid |
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