An aircraft landing gear shock absorber strut (24) includes an outer barrel (26) having a bore defining an opening; an inner cylinder (28) having a first end region movably coupled within the bore and a second end region extending out of the opening, the inner cylinder being arranged to move along a longitudinal axis of the bore between a first condition in which the shock absorber strut is compressed and a second condition in which the shock absorber strut is extended, the inner barrel is biased by a spring force to assume a second condition; a mechanical extension stop (OS) arranged to engage the abutment surface of the inner barrel to limit the extension of the shock absorber strut; and a rotatable member defining a threaded surface (TS) configured to axially drive the extension stop to move the inner barrel from the second condition towards the first condition to compress the shock absorber strut, the rotatable member being arranged such that a spring force cannot rotate the rotatable member to allow the shock absorber strut to extend.
一种飞行器起落架减震器支柱(24),包括:外筒(26),外筒具有限定开口的膛;内筒(28),内筒具有可移动地联接在膛内的第一端部区域和伸出开口的第二端部区域,内筒布置成沿着膛的纵向轴线在第一状况与第二状况之间移动,在第一状况中减震器支柱压缩,而在第二状况中减震器支柱伸展,内筒被弹簧力偏置成呈现第二状况;机械伸出止动部(OS),机械伸出止动部布置成接合内筒的抵接表面,以限制减震器支柱的伸展;以及可旋转构件,该可旋转构件限定螺纹表面(TS),螺纹表面构造成轴向驱动伸出止动部,以使内筒从第二状况朝向第一状况移动以压缩减震器支柱,可旋转构件布置成使得弹簧力不能使可旋转构件转动以允许减震器支柱伸展。
Aircraft landing gear shock absorber strut
飞行器起落架减震器支柱
2024-04-26
Patent
Electronic Resource
Chinese