GB452324A - A system of retractable landing gear for aeroplanes - Google Patents
A system of retractable landing gear for aeroplanesInfo
- Publication number
- GB452324A GB452324A GB11736/35A GB1173635A GB452324A GB 452324 A GB452324 A GB 452324A GB 11736/35 A GB11736/35 A GB 11736/35A GB 1173635 A GB1173635 A GB 1173635A GB 452324 A GB452324 A GB 452324A
- Authority
- GB
- United Kingdom
- Prior art keywords
- cylinder
- leg
- pivoted
- constituted
- extension
- 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)
- Transmission Devices (AREA)
Abstract
452,324. Retractable undercarriages for aircraft. SOC. D'INVENTIONS AERONAUTIQUES ET MECANIQUES S. 1. A. M., 1, Route des Alpes, Fribourg, Switzerland. April 16, 1935, No. 11736. Convention date, Jan. 12. [Class 4] In a retractable landing gear for aeroplanes of the kind in which a wheel or the like is carried by a leg constituted by two hinged members, one of which acts as a pneumatic or oleo-pneumatic shock-absorber, the movement of the leg is guided during retraction and extension by a directing bar of constant length hinged at one end on a fixed point on the aeroplane and at the other on the non-mobile (cylinder) member of the shock absorber. In one form, Figs. 1 and 2, a wheel 1 is carried by a leg 2, pivotally mounted on the aircraft structure at 3 and constituted by two elements hinged together at 6, the lower element consisting of a shock absorbing strut comprising a cylinder c and piston p. A directing bar 9 is pivoted at 8 to the aircraft structure and at 7 to the cylinder c of the shock absorber. Retraction and extension are effected by means of a jack 10 pivoted to the aircraft structure at 11 and to cylinder c at 12. In another form, Fig. 2, retraction and extension ace effected by a jack 13 pivoted at one end on a fixed point 14 and acting at the other on a hinge 15 provided in an auxiliary leg 16-16. According to the Specification as open to inspection under Sect. 91, the wheel carrying member 2 might be constituted by any device of elastic character or otherwise. This subject-matter does not appear in the Specification as accepted.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR452324X | 1935-01-12 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB452324A true GB452324A (en) | 1936-08-20 |
Family
ID=8900962
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB11736/35A Expired GB452324A (en) | 1935-01-12 | 1935-04-16 | A system of retractable landing gear for aeroplanes |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB452324A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10000282B2 (en) | 2015-06-02 | 2018-06-19 | Safran Landing Systems Uk Ltd | Aircraft landing gear assembly |
-
1935
- 1935-04-16 GB GB11736/35A patent/GB452324A/en not_active Expired
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10000282B2 (en) | 2015-06-02 | 2018-06-19 | Safran Landing Systems Uk Ltd | Aircraft landing gear assembly |
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