GB802021A - Improvements in or relating to landing gear for aircraft - Google Patents
Improvements in or relating to landing gear for aircraftInfo
- Publication number
- GB802021A GB802021A GB35804/55A GB3580455A GB802021A GB 802021 A GB802021 A GB 802021A GB 35804/55 A GB35804/55 A GB 35804/55A GB 3580455 A GB3580455 A GB 3580455A GB 802021 A GB802021 A GB 802021A
- Authority
- GB
- United Kingdom
- Prior art keywords
- arm
- aircraft
- leg
- wheel
- plunger
- 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
- B64C25/18—Operating mechanisms
- B64C25/20—Operating mechanisms mechanical
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Dampers (AREA)
Abstract
802,021. Aircraft undercarriages. SOC. D'INVENTIONS AERONAUTIQUES ET MECANIQUES S.I.A.M. Dec. 13, 1955 [Jan. 13, 1955], No. 35804/55. Class 4. In a retractable undercarriage for aircraft wherein means are provided to adjust the position of the wheel with respect to the leg to avoid obstacles during retraction, the leg J contains an inner sleeve C which carries at its lower end an arm C<SP>1</SP> to which is pivoted a further arm B carrying the wheel R. A shock absorber 1 is connected at its lower end to arm B and at its upper end to a plunger 3 within sleeve C, said plunger having a connection with a link 6 pivotally connected at 8 to a bell-crank 7 mounted on a pivot 5 carried by an extension of the leg J. One arm of bell-crank 7 is formed with a cam-slot 9 which co-operates with a pin 10 on the lower end of an arm 11 which is fixed in the aircraft and carries the retraction pivot 12 of the undercarriage. During retraction of the undercarriage, co-operation between pin 10 and cam slot 9 causes the bell crank to rotate with respect to leg J and thereby draw plunger 3 and shock absorber 1 upwardly within sleeve C to cause the axis of wheel R to follow the path T in order that the wheel may avoid the structural obstacles N.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR802021X | 1955-01-13 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB802021A true GB802021A (en) | 1958-09-24 |
Family
ID=9246101
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB35804/55A Expired GB802021A (en) | 1955-01-13 | 1955-12-13 | Improvements in or relating to landing gear for aircraft |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB802021A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2140365A (en) * | 1983-05-25 | 1984-11-28 | Messier Hispano Sa | Landing gear for an aircraft structure |
-
1955
- 1955-12-13 GB GB35804/55A patent/GB802021A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2140365A (en) * | 1983-05-25 | 1984-11-28 | Messier Hispano Sa | Landing gear for an aircraft structure |
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