GB493120A - Improvements in the suspension and mounting of internal combustion engines or other engine units - Google Patents
Improvements in the suspension and mounting of internal combustion engines or other engine unitsInfo
- Publication number
- GB493120A GB493120A GB7982/38A GB798238A GB493120A GB 493120 A GB493120 A GB 493120A GB 7982/38 A GB7982/38 A GB 7982/38A GB 798238 A GB798238 A GB 798238A GB 493120 A GB493120 A GB 493120A
- Authority
- GB
- United Kingdom
- Prior art keywords
- engine
- rings
- aircraft
- supports
- rubber
- 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
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
- B64D27/02—Aircraft characterised by the type or position of power plant
- B64D27/04—Aircraft characterised by the type or position of power plant of piston type
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
- Springs (AREA)
Abstract
493,120. Resilient mountings. JULIEN, M. F. A., and PAULSEN, J. F. March 30, 1937, No. 7982/38. Convention date, March 28, 1936. Divided out of 493,107, [Group XXXIII]. [Class 108 (iii)] [Also in Group XXXIII] Rubber supports at each end of an aircraft engine comprise, Fig. 1, a metal ring 19a on the engine adhesively connected between rubber rings 21a which are adhesively connected to cylindrical parts 20a on the frame of the aircraft. A similar mounting is employed at the rear of the engine. In Fig. 3, the engine is carried by links 5 having extensions 22 to which are secured links 5a extending between the cylinders. Brackets 9a extend from the engine and are supported by rubber mountings in rings 6a. In Fig. 7 the engine is secured to elastic supports comprising rings 24a, 24b which are supported by other elastic supports 25a, 25b connected to the aircraft frame. The supports provide longitudinal as well as angular oscillation about the crankshaft axis.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR493120X | 1936-03-28 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB493120A true GB493120A (en) | 1938-09-30 |
Family
ID=8904604
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB7982/38A Expired GB493120A (en) | 1936-03-28 | 1937-03-30 | Improvements in the suspension and mounting of internal combustion engines or other engine units |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB493120A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2671441A (en) * | 1948-09-10 | 1954-03-09 | Clyde W Harris | Variable heat insulating apparatus and solar heating system comprising same |
| CN103557752A (en) * | 2013-10-29 | 2014-02-05 | 北京航天发射技术研究所 | Filling device for guided missile cold-ejection power device |
-
1937
- 1937-03-30 GB GB7982/38A patent/GB493120A/en not_active Expired
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2671441A (en) * | 1948-09-10 | 1954-03-09 | Clyde W Harris | Variable heat insulating apparatus and solar heating system comprising same |
| CN103557752A (en) * | 2013-10-29 | 2014-02-05 | 北京航天发射技术研究所 | Filling device for guided missile cold-ejection power device |
| CN103557752B (en) * | 2013-10-29 | 2016-03-30 | 北京航天发射技术研究所 | The cold power set filling equipment launched of guided missile |
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