Patent ID: 8985516
Filing Date: 2015-03-24
Classification: B23B,B29C,B32B,B64C,Y10T

Abstract:
1. A structure of an aircraft comprising: a first structural member having a first major longitudinal axis including an inboard end on the longitudinal axis, and a distal outboard end on the longitudinal axis; a second structural member having a second major longitudinal axis parallel to the first major longitudinal axis, the second structural member bonded to the first structural member using an adhesive along a bondline having a third major longitudinal axis parallel to the first and second major longitudinal axes and between the first structural member and the second structural member where substantially similar strain may occur between the first structural member and the second structural member when under a load; and a flexible interface component disposed between the first structural member and the second structural member and only at an end portion of the bondline along the third major longitudinal axis between the first structural member and the second structural member where a differential in strain may occur between the first structural member and the second structural member when under a load, the flexible interface component at the end portion of the bondline being disposed proximate to the inboard end of the first structural member opposite the distal outboard end of the first structural member.