发明名称 Landing gear door damping mechanism for aircraft
摘要 <p>The invention provides a damping mechanism which comprises a damper (27); and a coupling mechanism. The coupling mechanism comprises a coupling member (25) which is pivotally attached to the damper and has a pivot bearing (26) for pivotally connecting the coupling member to a structure when in use; anda fitting (22,40) which can be engaged with the coupling member to couple the fitting with the damper and disengaged with the coupling member to decouple the fitting from the damper. More, the coupling member (25) has a pair of parallel planar faces which taper outwardly from the pivot bearing(26) to a convex curved edge (34), an upper edge (35) and a lower edge (36); and a first (37) and a second recess (38) formed in the convex curved edge (34), a rib (39) between the first and the second recesses and, a third recess (36a) formed in the lower edge (36)</p>
申请公布号 EP2644500(A1) 申请公布日期 2013.10.02
申请号 EP20130163772 申请日期 2012.03.27
申请人 AIRBUS OPERATIONS (S.A.S) 发明人 VEERABADRAN, KAROUNEN
分类号 B64C25/16;B64C1/14;E05B77/00;F16F15/00 主分类号 B64C25/16
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