| 摘要 |
<p>A method for reducing vibration in a rotary system (140; 240a; 240b; 340a; 340b) of an aircraft (100), for example an aeroplane or a rotorcraft, such as a helicopter, comprising balancing said rotary system (140; 240a; 240b; 340a; 340b),characterized by providing a substantially circular chamber (232a, 233a, 234b, 235a, 236a, 237a; 232b, 233b, 234b, 235b, 237b; 335a; 335b; 433a; 433b; 433c; 535a; 535b; 535c) having a fulcrumon an axis (260a; 260b; 360a; 360b; 460a; 460b; 460c; 560a; 560b; 560c) of a shaft (131; 231a; 231b; 331a; 331b; 431a; 431b; 431c; 531a; 531b; 531c) of said rotary system (140; 240a; 240b; 340a; 340b) and being partially filled with an amount of a thixotropic balancing substance (338a; 338b; 438a; 438b; 438c; 538a; 538b; 538c). An apparatus, and a system, for reducing vibration in a rotary system (140; 240a; 240b; 340a; 340b) of an aircraft (100) according to the method.</p> |
