GB221606A - Improvements in landing carriages for aircraft - Google Patents
Improvements in landing carriages for aircraftInfo
- Publication number
- GB221606A GB221606A GB1814523A GB1814523A GB221606A GB 221606 A GB221606 A GB 221606A GB 1814523 A GB1814523 A GB 1814523A GB 1814523 A GB1814523 A GB 1814523A GB 221606 A GB221606 A GB 221606A
- Authority
- GB
- United Kingdom
- Prior art keywords
- axle
- vertical
- shocks
- dash
- pot
- 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
- B64C25/62—Spring shock-absorbers; Springs
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
221,606. Hill, R. M., and Robinson, E. July 13, 1923. Shock absorbers, applications of; land-wheels. -In an aircraft undercarriage for absorbing both lateral and vertical shocks, the wheels are rotatably mounted on a common axle or on separate axles guided under the action of shock absorbing means, by vertical and horizontal guides. In the form shown in Fig. 1, each wheel 12 is mounted on a separate axle 6 which slides horizontally in a sleeve pivoted on a fulcrum pin 8 and acting as a horizontal guide for the axle. Rubber cord looped over spools 11 mounted on the undercarriage framework and spools 10 fixed to the inner end of the axle, absorb lateral shocks. The axle slides in a rigid vertical guide in the undercarriage framework 7. A known form of shock absorber 14 absorbs the vertical shocks when the axle moves about the fulcrum pin 8. A spring 13 between the sleeve and the axle end serves as a buffer on the return movement of the axle. According to a modification in which lateral shocks in two directions are absorbed, the axle 6, Fig. 3, is centralized by rubber rings 15, separated by metal washers 16, fitted on each side of the fulcrum pin 8. An internal or external oil dash-pot may also be fitted. As shown in Fig. 3, a dash-pot cylinder 17 is secured inside the axle, and a plunger 18, pierced with leak holes, is connected to the fulcrum pin 8. In another modification, the ends of the wheel axle, which is centralized by rubber rings 21, Fig. 4, slide horizontally in sockets 23 mounted upon vertical dash-pot struts 7. A dash-pot device similar to that shown in Fig. 3 may be combined with this arrangement to assist in absorbing lateral shocks.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1814523A GB221606A (en) | 1923-07-13 | 1923-07-13 | Improvements in landing carriages for aircraft |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB1814523A GB221606A (en) | 1923-07-13 | 1923-07-13 | Improvements in landing carriages for aircraft |
Publications (1)
Publication Number | Publication Date |
---|---|
GB221606A true GB221606A (en) | 1924-09-18 |
Family
ID=10107414
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1814523A Expired GB221606A (en) | 1923-07-13 | 1923-07-13 | Improvements in landing carriages for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB221606A (en) |
-
1923
- 1923-07-13 GB GB1814523A patent/GB221606A/en not_active Expired
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