GB485414A - Improvements in or relating to self-folding struts for aeroplane landing chassis - Google Patents
Improvements in or relating to self-folding struts for aeroplane landing chassisInfo
- Publication number
- GB485414A GB485414A GB10183/37A GB1018337A GB485414A GB 485414 A GB485414 A GB 485414A GB 10183/37 A GB10183/37 A GB 10183/37A GB 1018337 A GB1018337 A GB 1018337A GB 485414 A GB485414 A GB 485414A
- Authority
- GB
- United Kingdom
- Prior art keywords
- elements
- strut
- self
- relating
- 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
- B64C25/14—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like fore-and-aft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Body Structure For Vehicles (AREA)
Abstract
485,414. Aircraft alighting gear. SOC. D'INVENTIONS AERONAUTIQUES ET MECANIQUES S. I. A. M. April 9, 1937, No. 10183. Convention date, May 26, 1936. [Class 4] In a retractable landing-gear for aeroplanes comprising a self-folding strut including two spaced elements joined together by a third element and adapted to be extended or folded by the action of an extensible driving member supported by the strut, the driving member is articulated at one end to one of the three elements and at its other to one of the other two elements, means being provided for conjugating the relative movements of the two spaced elements. In one form, a folding strut A B is articulated to a shock-absorber J and to the aircraft. The two elements A, B of the strut are connected by triangular links 15 connected to one portion of a jack 12 the other portion of which is pivoted to the element A. The elements A, B are further connected by a link 7 or in a modification by gear teeth on the ends of the elements A, B. Stops 16, 17 form abutments to limit movement of the undercarriage in its extended or retracted condition.. Specifications 442,133 and 457,982 are referred to.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR485414X | 1936-05-26 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB485414A true GB485414A (en) | 1938-05-19 |
Family
ID=8903910
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB10183/37A Expired GB485414A (en) | 1936-05-26 | 1937-04-09 | Improvements in or relating to self-folding struts for aeroplane landing chassis |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB485414A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE889400C (en) * | 1940-12-31 | 1953-09-10 | Morane Saulnier S A | Laterally retractable landing gear for aircraft |
-
1937
- 1937-04-09 GB GB10183/37A patent/GB485414A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE889400C (en) * | 1940-12-31 | 1953-09-10 | Morane Saulnier S A | Laterally retractable landing gear for aircraft |
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