GB652819A - Improvements relating to landing gear for aircraft - Google Patents
Improvements relating to landing gear for aircraftInfo
- Publication number
- GB652819A GB652819A GB24404/48A GB2440448A GB652819A GB 652819 A GB652819 A GB 652819A GB 24404/48 A GB24404/48 A GB 24404/48A GB 2440448 A GB2440448 A GB 2440448A GB 652819 A GB652819 A GB 652819A
- Authority
- GB
- United Kingdom
- Prior art keywords
- wheels
- wheel
- undercarriage
- centre
- nose
- 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
- B64C25/34—Alighting gear characterised by elements which contact the ground or similar surface wheeled type, e.g. multi-wheeled bogies
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Aviation & Aerospace Engineering (AREA)
- Handcart (AREA)
Abstract
652,819. Retractable undercarriages. TROENDLE, J. A. Sept. 17, 1948, No. 24404. Convention date, Sept. 19, 1947. [Class 4] In order to reduce drag during take-off one or more of the landing wheels of an aircraft are retracted during the take-off run, the vertical line through the centre of gravity passing through or between those wheels which remain in contact with the ground. In the case of a tandem-wheel undercarriage as shown in Fig. 1, the nose wheel 3<SP>1</SP> is retracted during the take-off run and at the same time the strut carrying the rear wheel 2<SP>1</SP> is swung forwardly to bring the wheel beneath the centre of gravity. The nose and tail wheels of a tricycle undercarriage may be operated in a similar manner, Figs. 4-6 (not shown). Figs. 7 and 8 show a four-wheel undercarriage, of which the tail and nose wheels 231, 241 are disposed on the longitudinal axis, while the remaining wheels 21<SP>1</SP>, 22<SP>1</SP> are disposed laterally thereof and also in line with the centre of gravity. The order of raising the wheels is 24<SP>1</SP>-23<SP>1</SP>-21<SP>1</SP> and 22<SP>1</SP>. Other undercarriage arrangements are described.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US652819XA | 1947-09-19 | 1947-09-19 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB652819A true GB652819A (en) | 1951-05-02 |
Family
ID=22061605
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB24404/48A Expired GB652819A (en) | 1947-09-19 | 1948-09-17 | Improvements relating to landing gear for aircraft |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB652819A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2724566A (en) * | 1952-11-03 | 1955-11-22 | Jean A Troendle | Control arrangement for aircraft |
-
1948
- 1948-09-17 GB GB24404/48A patent/GB652819A/en not_active Expired
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2724566A (en) * | 1952-11-03 | 1955-11-22 | Jean A Troendle | Control arrangement for aircraft |
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