GB549211A - Improvements in or relating to fluid pressure remote control systems - Google Patents

Improvements in or relating to fluid pressure remote control systems

Info

Publication number
GB549211A
GB549211A GB593841A GB593841A GB549211A GB 549211 A GB549211 A GB 549211A GB 593841 A GB593841 A GB 593841A GB 593841 A GB593841 A GB 593841A GB 549211 A GB549211 A GB 549211A
Authority
GB
United Kingdom
Prior art keywords
valve
pipes
valves
flow
jacks
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
Application number
GB593841A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Bendix Aviation Corp
Original Assignee
Bendix Aviation Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by Bendix Aviation Corp filed Critical Bendix Aviation Corp
Priority to GB593841A priority Critical patent/GB549211A/en
Publication of GB549211A publication Critical patent/GB549211A/en
Expired legal-status Critical Current

Links

Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B64AIRCRAFT; AVIATION; COSMONAUTICS
    • B64CAEROPLANES; HELICOPTERS
    • B64C25/00Alighting gear
    • B64C25/02Undercarriages
    • B64C25/08Undercarriages non-fixed, e.g. jettisonable
    • B64C25/10Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like
    • B64C25/18Operating mechanisms
    • B64C25/22Operating mechanisms fluid

Abstract

549,211. Hydraulic machines ; valves. CLEVELAND, F. J. (Bendix Aviation Corporation). May 7, 1941, No. 5938. [A Specification was laid open to inspection under Sect. 91 of the Acts, Nov. 8, 1941.] [Classes 69 (ii) and 135] [Also in Group XXXIII] For synchronizing the movements of two or more elements of an aircraft control or a landing gear a self-adjusting valve described below is inserted between the pump and the power cylinders of a hydraulic servomotor to secure equality of flow to the cylinders. A system is described comprising two double-acting jacks fed through two reversing valves from pipes 38, 39 leading from a valve casing 22 supplied with pressure fluid through a pipe 21. Passages 23, 24, 25 are formed in the walls of the casing which has a cylindrical liner 27 in which slides a grooved piston 26. Holes 33, 34 in the liner admit pressure fluid to the grooves in the piston, the fluid issuing through longitudinally arranged narrow slits 36, 37 in the liner to the passages 24, 25 and the pipes 38, 39. Any increase of flow through one slit or the other causes a fall of pressure in the passages 24 or 25 and consequently on the corresponding end of the piston which then moves to correct the inequality. This subject-matter appears also in the Specification, corresponding to the Provisional Specification, placed open to inspection under Sect. 91 on the 8th November, 1941. The following subjectmatter appears only in the Specification as accepted. Fig. 4 shows a modified valve in which pressure fluid through a pipe 21a can flow directly to a passage 60 and past non-return valves 54 55 to the pipes 38a, 39a, but return flow through the two pipes 38a, 39a, is equalized by the valve 26 which is similar to that shown in Fig. 1 except that it has a single central groove 49. Two such valve devices are shown in Fig. 6 connected to opposite ends of two jacks 13, 14 the two inlets 21a being connected by pipes 66, 67 to a valve 65. This valve places the two pipes alternatively into communication with the pressure and reservoir sides 64, 68 of a pump system including an accumulator 62 and in either case the return flow from the jacks is controlled by one of the valves 26 while the pressure fluid has free access through the valves 54, 55 to the appropriate ends of the two jacks. Should unequal but proportionate flow through the two branches be required the slits 36, 37 are made of different shapes or sizes or the areas of the valve ends exposed to the fluid pressure may differ.
GB593841A 1941-05-07 1941-05-07 Improvements in or relating to fluid pressure remote control systems Expired GB549211A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB593841A GB549211A (en) 1941-05-07 1941-05-07 Improvements in or relating to fluid pressure remote control systems

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB593841A GB549211A (en) 1941-05-07 1941-05-07 Improvements in or relating to fluid pressure remote control systems

Publications (1)

Publication Number Publication Date
GB549211A true GB549211A (en) 1942-11-11

Family

ID=9805435

Family Applications (1)

Application Number Title Priority Date Filing Date
GB593841A Expired GB549211A (en) 1941-05-07 1941-05-07 Improvements in or relating to fluid pressure remote control systems

Country Status (1)

Country Link
GB (1) GB549211A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2415603A (en) * 1943-08-26 1947-02-11 Hydraulic Dev Corp Inc Hydraulic constant speed control system for parallel-connected hydraulic motors
US2423264A (en) * 1943-04-28 1947-07-01 Hydraulic Control Engineering Equalizing valve
US3015338A (en) * 1958-10-07 1962-01-02 Bendix Corp Flow divider
US3305037A (en) * 1964-08-21 1967-02-21 Int Harvester Co Control valve for track laying tractor
CN103527540A (en) * 2012-07-06 2014-01-22 哈尔滨飞机工业集团有限责任公司 Pressure selector valve applied to undercarriage
CN104482105A (en) * 2014-12-30 2015-04-01 哈尔滨通航科技开发有限公司 Air inflation device for high-pressure chamber and low-pressure chamber of buffering strut of aircraft landing gear

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2423264A (en) * 1943-04-28 1947-07-01 Hydraulic Control Engineering Equalizing valve
US2415603A (en) * 1943-08-26 1947-02-11 Hydraulic Dev Corp Inc Hydraulic constant speed control system for parallel-connected hydraulic motors
US3015338A (en) * 1958-10-07 1962-01-02 Bendix Corp Flow divider
US3305037A (en) * 1964-08-21 1967-02-21 Int Harvester Co Control valve for track laying tractor
CN103527540A (en) * 2012-07-06 2014-01-22 哈尔滨飞机工业集团有限责任公司 Pressure selector valve applied to undercarriage
CN104482105A (en) * 2014-12-30 2015-04-01 哈尔滨通航科技开发有限公司 Air inflation device for high-pressure chamber and low-pressure chamber of buffering strut of aircraft landing gear
CN104482105B (en) * 2014-12-30 2016-03-09 哈尔滨通航科技开发有限公司 Undercarriage damper leg high low pressure chamber charger

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