| タイトル | Method of vibration isolating an aircraft engine |
| 本文（外部サイト） | http://hdl.handle.net/2060/20080004397 |
| 著者（英） | Butler, Lawrence; Dawes, Peter W.; Bender, Stanley I. |
| 著者所属（英） | General Electric Co. |
| 発行日 | 1991-07-02 |
| 言語 | eng |
| 内容記述 | A method for coupling an engine to a support frame for mounting to a fuselage of an aircraft using a three point vibration isolating mounting system in which the load reactive forces at each mounting point are statically and dynamically determined. A first vibration isolating mount pivotably couples a first end of an elongated support beam to a stator portion of an engine with the pivoting action of the vibration mount being oriented such that it is pivotable about a line parallel to a center line of the engine. An aft end of the supporting frame is coupled to the engine through an additional pair of vibration isolating mounts with the mounts being oriented such that they are pivotable about a circumference of the engine. The aft mounts are symmetrically spaced to each side of the supporting frame by 45 degrees. The relative orientation between the front mount and the pair of rear mounts is such that only the rear mounts provide load reactive forces parallel to the engine center line, in support of the engine to the aircraft against thrust forces. The forward mount is oriented so as to provide only radial forces to the engine and some lifting forces to maintain the engine in position adjacent a fuselage. Since each mount is connected to provide specific forces to support the engine, forces required of each mount are statically and dynamically determinable. |
| NASA分類 | Aeronautics (General) |
| 権利 | No Copyright |
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