GB545915A - Improvements in or relating to resilient engine mounts - Google Patents
Improvements in or relating to resilient engine mountsInfo
- Publication number
- GB545915A GB545915A GB17778/40A GB1777840A GB545915A GB 545915 A GB545915 A GB 545915A GB 17778/40 A GB17778/40 A GB 17778/40A GB 1777840 A GB1777840 A GB 1777840A GB 545915 A GB545915 A GB 545915A
- Authority
- GB
- United Kingdom
- Prior art keywords
- ring
- engine
- aircraft
- tube
- tubes
- 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
- 238000010276 construction Methods 0.000 abstract 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
- B64D27/02—Aircraft characterised by the type or position of power plants
- B64D27/04—Aircraft characterised by the type or position of power plants of piston type
Landscapes
- Engineering & Computer Science (AREA)
- Aviation & Aerospace Engineering (AREA)
- Vibration Prevention Devices (AREA)
Abstract
545,915. Aircraft engine mountings. UNITED AIRCRAFT CORPORATION. Dec. 17, 1940, No. 17778. Convention date, Dec. 20, 1939. [Class 4] [Also in Group XXVI] An engine, particularly an aircraft engine, is connected by spring arms to a ring mounted resiliently on the framework of the aircraft. In the construction shown in Figs. 2 and 4, the engine 10 is connected to a ring 18 by converging spring-arms 14 each consisting of a tube which tapers from the ends to an elliptical waist, the arrangement providing different spring-rates in directions tangential and radial to the ring. Each arm is formed with a foot 60 secured to the engine by bolts 58, and a threaded stem 54 which is parallel to the axes of the ring and extends through a sleeve 52 in the ring and into a tube 34 having a cap 42 welded to the tube. The stem has a key 55 engaging a slot in the tube, and is secured by a tubular nut 62. The nuts are accessible through the outer ends of the tubes 34. The sides of the tubes may be cut away to facilitate access to the nuts. The tubes 34 form part of a welded tubular frame 22, 24, 32 which is secured to the framework of the aircraft by bolts passing through caps 44.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US545915XA | 1939-12-20 | 1939-12-20 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB545915A true GB545915A (en) | 1942-06-18 |
Family
ID=21992157
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB17778/40A Expired GB545915A (en) | 1939-12-20 | 1940-12-17 | Improvements in or relating to resilient engine mounts |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB545915A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
-
1940
- 1940-12-17 GB GB17778/40A patent/GB545915A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110844090A (en) * | 2019-10-11 | 2020-02-28 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
| CN110844090B (en) * | 2019-10-11 | 2022-11-22 | 中国直升机设计研究所 | Supporting type mounting device of piston engine of helicopter |
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