GB521708A - Improvement in suspension devices - Google Patents
Improvement in suspension devicesInfo
- Publication number
- GB521708A GB521708A GB33904/38A GB3390438A GB521708A GB 521708 A GB521708 A GB 521708A GB 33904/38 A GB33904/38 A GB 33904/38A GB 3390438 A GB3390438 A GB 3390438A GB 521708 A GB521708 A GB 521708A
- Authority
- GB
- United Kingdom
- Prior art keywords
- elasticity
- engine
- members
- blocks
- added
- 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
Abstract
521,708. Mounting aircraft engines. JULIEN, M. F. A., and ROCARD, Y. A. Nov. 22, 1938, No. 33904. Convention date, Nov. 23, 1937. [Class 4] An aeroplane engine mounted with torsional and radial elasticity upon supports which are subjected to reciprocating vibrations during flight, has the radial elasticity of the suspension in the direction of the characteristic vibrations of the support designed to bring the engine and the support nearly into resonance, damping means being added to the system. Fig. 4 shows an engine mounted on resilient blocks 3 giving radial and torsional elasticity as in Specification 451,577, additional members 5 giving added elasticity in a vertical direction. The elasticities of the blocks 3 and members 5 are so chosen as to give a vertical vibration frequency equal to or less than the characteristic pulsations of the wing on which the engine is mounted. The members 5 may be omitted and the elasticity of the blocks 3 suitably varied, or a hydraulic damping device may be added. Fig. 6 shows an engine nacelle suspended from a wing by resilient members 5, 5<1> controlled by a hydraulic damper 7.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| FR521708X | 1937-11-23 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB521708A true GB521708A (en) | 1940-05-29 |
Family
ID=8917400
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB33904/38A Expired GB521708A (en) | 1937-11-23 | 1938-11-22 | Improvement in suspension devices |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB521708A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0437868A1 (en) * | 1988-11-10 | 1991-07-24 | The Boeing Company | Apparatus and methods for reducing aircraft lifting surface flutter |
| CN105882984A (en) * | 2016-05-24 | 2016-08-24 | 北京浩恒征途航空科技有限公司 | Oil-drive multi-rotor aircraft |
-
1938
- 1938-11-22 GB GB33904/38A patent/GB521708A/en not_active Expired
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0437868A1 (en) * | 1988-11-10 | 1991-07-24 | The Boeing Company | Apparatus and methods for reducing aircraft lifting surface flutter |
| CN105882984A (en) * | 2016-05-24 | 2016-08-24 | 北京浩恒征途航空科技有限公司 | Oil-drive multi-rotor aircraft |
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