GB517370A - Improvements relating to aircraft undercarriages with resilient wheel units - Google Patents
Improvements relating to aircraft undercarriages with resilient wheel unitsInfo
- Publication number
- GB517370A GB517370A GB15892/38A GB1589238A GB517370A GB 517370 A GB517370 A GB 517370A GB 15892/38 A GB15892/38 A GB 15892/38A GB 1589238 A GB1589238 A GB 1589238A GB 517370 A GB517370 A GB 517370A
- Authority
- GB
- United Kingdom
- Prior art keywords
- spindle
- wheel
- shock
- piston
- liquid
- 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
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
- B64C25/36—Arrangements or adaptations of wheels, tyres or axles in general
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Fluid-Damping Devices (AREA)
Abstract
517,370. Aircraft alighting gear. BOUND, R. H. May 27, 1938, No. 15892. [Class 4] An aircraft landing wheel is mounted on a pair of pistons and cylinder shock absorbers spaced by the wheel spindle and adapted to displace liquid against resilient resistance in a chamber in the spindle. The wheel spindle 7 is formed integrally with the shock absorber cylinders 4 which are pivoted at 2a to the wheel fork 1. The piston rod 3 is pivoted at 3a to the fork. The shock absorber liquid is adapted to be forced through an opening 13 and past a valve 12 against one side' of a piston 14 in the spindle 7, which contains a corresponding piston for the shock absorber on the other side of the wheel. The space between the pistons is charged with compressed air. In a modification the liquid from both shock absorbers is led by passages 44, Fig. 4, to a single piston 46 arranged transversely of the axis of the spindle. The liquid spaces of the shock absorbers is annular through which pass the piston rods 33. The shock-absorber cylinders are formed in the wheel spindle 34. A lever 32 is pivoted at 32a to the wheel fork 31a and surrounds the end of the spindle 34 to which it is secured by studs 35 and closes the end of the shock-absorber cylinder. Specifications 473,756 and 473,768 are referred to.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB15892/38A GB517370A (en) | 1938-05-27 | 1938-05-27 | Improvements relating to aircraft undercarriages with resilient wheel units |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB15892/38A GB517370A (en) | 1938-05-27 | 1938-05-27 | Improvements relating to aircraft undercarriages with resilient wheel units |
Publications (1)
Publication Number | Publication Date |
---|---|
GB517370A true GB517370A (en) | 1940-01-29 |
Family
ID=10067412
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB15892/38A Expired GB517370A (en) | 1938-05-27 | 1938-05-27 | Improvements relating to aircraft undercarriages with resilient wheel units |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB517370A (en) |
-
1938
- 1938-05-27 GB GB15892/38A patent/GB517370A/en not_active Expired
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