GB687903A - Improvements relating to aircraft retractable landing gear - Google Patents
Improvements relating to aircraft retractable landing gearInfo
- Publication number
- GB687903A GB687903A GB10131/51A GB1013151A GB687903A GB 687903 A GB687903 A GB 687903A GB 10131/51 A GB10131/51 A GB 10131/51A GB 1013151 A GB1013151 A GB 1013151A GB 687903 A GB687903 A GB 687903A
- Authority
- GB
- United Kingdom
- Prior art keywords
- sleeve
- piston
- strut
- liquid
- landing gear
- 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
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
Abstract
687,903. Hydro-pneumatic shock-absorbers. ELECTROL, Inc. April 30, 1951 [June 16, 1950], No. 10131/51. Class 108 (iii). [Also in Group XXXIII] A hydro-pneumatic shock-absorber for an aircraft undercarriage comprises an inner sleeve 41, with a tubular piston member 43 secured to its upper end. slidable in an outer cylinder 12 and carrying a piston 44 intermediate its ends by which the damping air and liquid are compressed. The upper end of the strut carries a second sleeve 47 disposed within the sliding sleeve 41 and provided at its lower end with a piston 49 carrying a ring 50 in sliding engagement with the sleeve 41, and also provided with an orifice 51 for the passage of the damping liquid. Extension of the strut is limited by the piston 43 engaging the end of a sleeve 39 mounted between the sliding sleeve 41 and the outer cylinder 12. Compressed air and liquid are supplied through a valve 52 at the top of the strut.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US687903XA | 1950-06-16 | 1950-06-16 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB687903A true GB687903A (en) | 1953-02-25 |
Family
ID=22084727
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB10131/51A Expired GB687903A (en) | 1950-06-16 | 1951-04-30 | Improvements relating to aircraft retractable landing gear |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB687903A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE1114710B (en) * | 1958-08-11 | 1961-10-05 | Rotol Ltd | Aircraft landing gear |
| US3011777A (en) * | 1957-11-06 | 1961-12-05 | Bendix Corp | Retractable strut |
| CN107914867A (en) * | 2017-12-06 | 2018-04-17 | 南京航空航天大学 | The adaptive deformation alighting carriage of friction lock and its control method |
| CN110001935A (en) * | 2019-05-07 | 2019-07-12 | 广州中国科学院沈阳自动化研究所分所 | A kind of unmanned plane is from active platform landing auxiliary device |
-
1951
- 1951-04-30 GB GB10131/51A patent/GB687903A/en not_active Expired
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3011777A (en) * | 1957-11-06 | 1961-12-05 | Bendix Corp | Retractable strut |
| DE1114710B (en) * | 1958-08-11 | 1961-10-05 | Rotol Ltd | Aircraft landing gear |
| CN107914867A (en) * | 2017-12-06 | 2018-04-17 | 南京航空航天大学 | The adaptive deformation alighting carriage of friction lock and its control method |
| CN107914867B (en) * | 2017-12-06 | 2023-10-27 | 南京航空航天大学 | Friction locking self-adaptive deformation landing gear and control method thereof |
| CN110001935A (en) * | 2019-05-07 | 2019-07-12 | 广州中国科学院沈阳自动化研究所分所 | A kind of unmanned plane is from active platform landing auxiliary device |
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