GB526352A - Shock absorbing means for aircraft landing gear - Google Patents
Shock absorbing means for aircraft landing gearInfo
- Publication number
- GB526352A GB526352A GB8148/39A GB814839A GB526352A GB 526352 A GB526352 A GB 526352A GB 8148/39 A GB8148/39 A GB 8148/39A GB 814839 A GB814839 A GB 814839A GB 526352 A GB526352 A GB 526352A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cylinder
- piston
- tube
- liquid
- carries
- 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
- B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface
- B64C25/58—Arrangements or adaptations of shock-absorbers or springs
- B64C25/60—Oleo legs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
526,352. Shock-absorbers. SOC. DE MECANIQUE GENERALE. March 14; 1939, No. 8148. Convention date, March 18, 1938. [Class 108 (iii)] In a hydro-pneumatic shock absorber for aircraft landing gear, a lower cylinder 5 terminates in a wheel bearing 6 and slides within a casing 1 which carries, by means of a ball joint, a cylinder 10 within the cylinder 5. The cylinder 10 carries a piston 14, and the tube 17, attached to the bearing 6, carries a piston 18 with valve 19, moving in the cylinder 10. The piston 18 and tube 17 allow the passage of liquid from cylinder 10 to cylinder 5 through openings 21, 22. A tapering pin 24 is carried by the cylinder 10 and projects into the tube 17. A byepass 25 through the part 13 carried by cylinder 10 is regulated by screw 26. On landing, the cylinder 5 is forced into the casing 1, the piston 18 sliding in the cylinder 10 with the valve 19 open so that liquid passes freely to the underside of the piston, and no vacuum is produced. On the return stroke, valve 19 closes and liquid below the piston passes into cylinder 5 through the constricted passage 25. Liquid in cylinder 10 also returns to cylinder 5 through openings 21, 22. Compression of the air may be varied by adjusting the length of tube 11, which is connected to the corresponding tube on the associated shock absorber, and to an inflating device.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| LU526352X | 1938-03-18 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB526352A true GB526352A (en) | 1940-09-17 |
Family
ID=19732858
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB8148/39A Expired GB526352A (en) | 1938-03-18 | 1939-03-14 | Shock absorbing means for aircraft landing gear |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB526352A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2433631A (en) * | 1944-01-27 | 1947-12-30 | Smith Corp A O | Weld fabricated yoke |
| US8690432B2 (en) | 2009-04-27 | 2014-04-08 | Messier-Dowty Limited | Bearing assembly |
-
1939
- 1939-03-14 GB GB8148/39A patent/GB526352A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2433631A (en) * | 1944-01-27 | 1947-12-30 | Smith Corp A O | Weld fabricated yoke |
| US8690432B2 (en) | 2009-04-27 | 2014-04-08 | Messier-Dowty Limited | Bearing assembly |
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