GB580476A - Retractable landing gear for aircraft - Google Patents
Retractable landing gear for aircraftInfo
- Publication number
- GB580476A GB580476A GB10201/45A GB1020145A GB580476A GB 580476 A GB580476 A GB 580476A GB 10201/45 A GB10201/45 A GB 10201/45A GB 1020145 A GB1020145 A GB 1020145A GB 580476 A GB580476 A GB 580476A
- Authority
- GB
- United Kingdom
- Prior art keywords
- strut
- axis
- hinged
- flight
- shock
- 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
- B64C25/12—Undercarriages non-fixed, e.g. jettisonable retractable, foldable, or the like sideways
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Pivots And Pivotal Connections (AREA)
- Transmission Devices (AREA)
Abstract
580,476.. Landing-gear. MORANE-SAULNIER. April 23, 1945, No. 10201. Convention date, July 25, 1944. [Class 4] A folding strut with hinged members 3, 4, Fig. 1, is hinged at its ends to a shock-strut 1, retractable into a wing 12 about an axis X-Y in the direction of flight, and to a fixed part of the aeroplane in such a manner that the plane of the folding strut is always parallel to the direction of flight. The strut member 4 is hinged to the shock-strut 1 by being pivoted about an axis 9 to a sleeve 8, mounted on part 7, attached to strut 1, to turn about-axis Z-T at right angles to axis 9 and which is also in the direction of flight ; the strut member 3 may be similarly hinged to the aeroplane structure or may be connected by a universal joint such as a ball-and-socket. The jack 17 for retracting the shock-strut may be connected directly thereto or, as shown in Fig. 12, and as described in French Specification 793,094, may be connected to the strut members 3, 4, member 3 is connected to the aeroplane wing by ball-andsocket 20.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR580476X | 1944-07-25 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB580476A true GB580476A (en) | 1946-09-09 |
Family
ID=8956810
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB10201/45A Expired GB580476A (en) | 1944-07-25 | 1945-04-23 | Retractable landing gear for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB580476A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2417933A (en) * | 2004-09-10 | 2006-03-15 | Airbus Uk Ltd | Landing gear support assembly for an aircraft |
-
1945
- 1945-04-23 GB GB10201/45A patent/GB580476A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB2417933A (en) * | 2004-09-10 | 2006-03-15 | Airbus Uk Ltd | Landing gear support assembly for an aircraft |
| US7793885B2 (en) | 2004-09-10 | 2010-09-14 | Airbus Uk Limited | Landing gear support |
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