GB762722A - Improvements in or relating to locking devices, more particularly for the hydraulic actuators of aircraft landing gear - Google Patents
Improvements in or relating to locking devices, more particularly for the hydraulic actuators of aircraft landing gearInfo
- Publication number
- GB762722A GB762722A GB29777/54A GB2977754A GB762722A GB 762722 A GB762722 A GB 762722A GB 29777/54 A GB29777/54 A GB 29777/54A GB 2977754 A GB2977754 A GB 2977754A GB 762722 A GB762722 A GB 762722A
- Authority
- GB
- United Kingdom
- Prior art keywords
- piston
- fingers
- sleeve
- locking
- cylinder
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Actuator (AREA)
Abstract
762,722. Hydraulic actuators. BENDIX AVIATION CORPORATION. Oct. 15, 1954 [Nov. 18, 1953], No. 29777/54. Class 69 (2). A hydraulic actuator for raising and lowering the undercarriage of aircraft comprises a piston and cylinder and means for locking the piston at one end of the cylinder. A valve unit is also carried within the cylinder and is actuated to allow pressure liquid to effect movement of the piston only after the locking means is released. The piston in a tube piston 38 slidable within a cylinder 30'and is provided at one end with fingers 102 adapted to spring over an inwardly projecting sleeve 55, when the piston is moved to contract by pressure exerting a force on surface 56, to engage the end 104 of the fingers beyond the end of the sleeve. In this position the fingers are locked by the end of a locking sleeve 68 slidably mounted on inner sections 62, 64 projecting within the cylinder and held in the locking position by a spring 70. Upon pressure fluid entering port 86, it is fed into a chamber 76 by passing over the square edges of a valve 90, Figs. 2 and 3. The pressure exerted bears on the edge 69 of the sleeve 68 and forces it to move against the spring and to release its end from locking engagement with the fingers 102. A projection 103 on the inside of the sleeve 68 engages the valve 90 when the end of the sleeve disengages the fingers and lifts the valve from its seating permitting pressure fluid to pass through holes 94 in section 64 and to flow through a central tube 96. The tube 96 carries a wall 100 at its end which serves as the stationary end wall of an expansion chamber 98 of which the inside of the piston forms the remaining walls. The piston therefore extends to raise the undercarriage. A micro-switch 118 is provided to give an indication whether the locking elements are in their locked or unlocked position, and is operated by a feeler 124 which engages both the fingers and end of tube 68 to ensure their correct positioning. The feeler is pivoted on an arm 120 which holds the contacts of the switch open when the piston is correctly locked in its retracted position.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US762722XA | 1953-11-18 | 1953-11-18 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB762722A true GB762722A (en) | 1956-12-05 |
Family
ID=22130941
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB29777/54A Expired GB762722A (en) | 1953-11-18 | 1954-10-15 | Improvements in or relating to locking devices, more particularly for the hydraulic actuators of aircraft landing gear |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB762722A (en) |
Cited By (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2286227A (en) * | 1994-01-18 | 1995-08-09 | Dowty Aerospace Gloucester | Actuator |
US9688390B2 (en) | 2012-09-17 | 2017-06-27 | Safran Landing Systems Uk Ltd | Landing gear assembly |
CN110356545A (en) * | 2019-08-21 | 2019-10-22 | 成都弗格森液压机电有限公司 | A kind of unmanned plane undercarriage control retaining mechanism |
-
1954
- 1954-10-15 GB GB29777/54A patent/GB762722A/en not_active Expired
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2286227A (en) * | 1994-01-18 | 1995-08-09 | Dowty Aerospace Gloucester | Actuator |
GB2286227B (en) * | 1994-01-18 | 1997-05-28 | Dowty Aerospace Gloucester | Actuator |
US9688390B2 (en) | 2012-09-17 | 2017-06-27 | Safran Landing Systems Uk Ltd | Landing gear assembly |
CN110356545A (en) * | 2019-08-21 | 2019-10-22 | 成都弗格森液压机电有限公司 | A kind of unmanned plane undercarriage control retaining mechanism |
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