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71.发明授权LOAD INDICATOR AND METHOD FOR DETECTING A HARD LANDING OR AN OVERLOAD FORCE DURING TOWING OF AN AIRCRAFT 有权拖飞机过程中最后的显示及检测方法的硬着陆或过多接触对
公开(公告)号：EP2190744B1
公开(公告)日：2012-04-18
申请号：EP08806342.5
申请日：2008-09-19
发明人： INNS, Martyn , SMITH, Steve
CPC分类号： F16C23/045 , B64C25/00 , B64D2045/008 , B64F5/60 , F16C11/045 , F16C17/24 , F16C2326/43 , G01L5/0071
摘要： A load indicator comprises a load bearing assembly of first and second load bearing members (23, 22) connected together to bear a lateral load applied to the first member (23), the first load bearing member defining a cavity (25) with the second load bearing member such that it is frangible above an indicator load, and the cavity (25) containing an indicator liquid which escapes from the cavity once the first load bearing member is fractured by said load. The load bearing members (22, 23) comprise cylindrical members arranged concentrically with the outer member (23) having a portion of reduced thickness to render it frangible and to define the cavity (25). The cavity (25) includes an internal volume within the second load bearing member (22). The load indicator may be configured as a load bearing pin to connect two components.
摘要翻译： 的载荷指示器包括连接在一起以承受施加到第一构件（23）的横向载荷时，第一承载第一和第二承载部件（23，22）的承载组件构件限定了与第二空腔（25） 承载构件搜索做了它是易碎的上面加载指示符，以及含有一旦第一承载构件是由所述负载断裂从腔逸出指示器液体的腔体（25）。 所述承重构件（22，23）包括具有减小的厚度的一部分，以使其易碎，并限定所述空腔（25）与所述外部件（23）同心布置的圆柱形构件。 所述空腔（25）包括在所述第二承载构件（22）内的内部容积。 负载指示符可以被配置为承载销连接两个部件。
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公开(公告)号：EP2248720A3
公开(公告)日：2011-11-16
申请号：EP10174045.4
申请日：2006-08-04
发明人： Bennett, Ian , Lang, Richard , Menezes, Robert
摘要： A semi-levered landing gear for an aircraft comprises a main shock absorber strut (1) with upper and lower telescoping portions, with the upper portion pivotally connectable to the airframe. The landing gear further comprises a bogie beam (4) to extend fore and aft of the airframe with at least one forward axle and one aft axle for respective forward and aft wheels and a main pivot between the forward and aft axle pivotally connected to the lower portion of the main shock absorber strut and an auxiliary actuator mechanism comprising a spring unit (11) pivotally connected at a lower end to an auxiliary pivot on the bogie forward of the main pivot, and at an upper end to an anchor point (112) offset from the pivot connection of the upper portion to the aircraft fuselage so that during stowing both the strut and spring unit pivot together about different pivot points, which causes a relative longitudinal movement between the main pivot and auxiliary pivot that further tilts the bogie beam to a stowing position.
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公开(公告)号：EP2190744A1
公开(公告)日：2010-06-02
申请号：EP08806342.5
申请日：2008-09-19
发明人： INNS, Martyn , SMITH, Steve
CPC分类号： F16C23/045 , B64C25/00 , B64D2045/008 , B64F5/60 , F16C11/045 , F16C17/24 , F16C2326/43 , G01L5/0071
摘要： A load indicator comprises a load bearing assembly of first and second load bearing members (23, 22) connected together to bear a lateral load applied to the first member (23), the first load bearing member defining a cavity (25) with the second load bearing member such that it is frangible above an indicator load, and the cavity (25) containing an indicator liquid which escapes from the cavity once the first load bearing member is fractured by said load. The load bearing members (22, 23) comprise cylindrical members arranged concentrically with the outer member (23) having a portion of reduced thickness to render it frangible and to define the cavity (25). The cavity (25) includes an internal volume within the second load bearing member (22). The load indicator may be configured as a load bearing pin to connect two components.
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