-
-
公开(公告)号：EP3670336A1
公开(公告)日：2020-06-24
申请号：EP18214631.6
申请日：2018-12-20
IPC分类号： B64C25/34
摘要： An aircraft landing gear assembly comprising: a bogie beam pivotally coupled to a support member: a pitch trimmer assembly including a pitch trimmer actuator configured to exert a biasing force in a first direction and a bias force transmission assembly configured to receive the biasing force in the first direction and bias the bogie beam towards a predetermined neutral position relative to the support member irrespective of the initial position of the bogie beam.
-
公开(公告)号：EP3118479B1
公开(公告)日：2018-08-22
申请号：EP15176867.8
申请日：2015-07-15
发明人： Simonneaux, Yann , Whitman, Steve
摘要： A magnetic shock absorber (11) comprising a first body (12) slidably coupled to a second body (14) via a first bearing (24a) arranged to move in sliding engagement with a first counter-face portion (26a). A first array of magnets (18) associated with the first body is arranged to magnetically interact with a second array of magnets (22) is associated with the second body to absorb compression or extension loads applied to the shock absorber. The first bearing and the first counter-face portion each have a non-circular cross section profile (27) to inhibit axial relative rotation between the bodies.
-
公开(公告)号：EP3279085A1
公开(公告)日：2018-02-07
申请号：EP16182695.3
申请日：2016-08-04
发明人： Simonneaux, Yann
IPC分类号： B64C25/60
CPC分类号： B64C25/60
摘要： An aircraft landing gear shock absorber strut (10) including: a casing (11) formed from titanium and including a wall portion defining a first bore (6) which is open at a first axial face of the casing; a non-titanium tubular sleeve (11a) fitted within the first bore, the tubular sleeve having a sleeve wall which defines a second bore that is open at the first axial face of the casing, the sleeve wall being thinner than the wall portion of the casing; a sliding tube (1) having a first end region defining a piston which is slidably housed within the second bore and a second end region which projects from the first axial face of the casing so that the sliding tube (1) can move axially relative to the casing between a compressed shock absorber condition and an extended shock absorber condition, the first end region of the sliding tube (1) defining a first bearing (12) having a first bearing surface arranged in sliding contact with the sleeve; and a second bearing (4) coupled to the casing within the first bore and having a second bearing surface arranged for sliding contact with the sliding tube, the second bearing being situated closer to the first axial face of the casing in comparison to the first bearing.
摘要翻译： 1。一种飞机起落架减震器支柱（10），包括：由钛形成的壳体（11），所述壳体包括限定第一孔（6）的壁部分，所述第一孔在所述壳体的第一轴向面处开口; 一个安装在第一孔内的非钛管状套筒（11a），管状套筒具有一个套筒壁，套筒壁形成一个在套筒的第一轴向面开口的第二孔，套筒壁比第一孔的壁部分薄 套管; 具有第一端部区域和第二端部区域的滑动管（1），所述第一端部区域限定可滑动地容纳在所述第二孔内的活塞，所述第二端部区域从所述壳体的第一轴向面突出，使得所述滑动管（1）能够相对于所述滑动管 （1）的第一端部区域限定第一轴承（12），所述第一轴承具有布置成与所述套筒滑动接触的第一支承表面; 和第二轴承（4），所述第二轴承（4）在所述第一孔内与所述壳体联接并且具有布置成与所述滑动管滑动接触的第二轴承面，所述第二轴承与所述第一轴承相比更靠近所述壳体的第一轴向面 。
-
公开(公告)号：EP3251950A1
公开(公告)日：2017-12-06
申请号：EP16172398.6
申请日：2016-06-01
发明人： Simonneaux, Yann , Smith, Jon
CPC分类号： B64C25/62 , B64C25/60 , B64F5/60 , F16F9/0245 , G01D5/2291 , G05B19/04
摘要： The present invention relates to a method for pressurising and depressurising a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurisation level of a shock absorber. As such, the shock absorber may be pressurised to the correct level without applying an iterative approach, greatly reducing initialisation time.
摘要翻译： 本发明涉及一种用于对飞机的减震器加压和减压的方法。 更具体地说，涉及一种使用飞机重量和环境温度来计算减震器所需的增压水平的方法。 这样，减震器可以被加压到正确的水平，而无需应用迭代方法，从而大大减少了初始化时间。
-
-
-
-
搜索结果
5 条记录 (耗时 0.013 秒)
