Patent ID: 7467763
Filing Date: 2008-12-23
Classification: B64C

Abstract:
1. A landing gear assembly for an aircraft, comprising: a receiving member configured to be coupled to a frame member of the aircraft, the receiving member including a receiving portion defining a receptacle, the receiving member including a structurally-weakened portion proximate the receptacle; and an elongated member having a first end disposed within and coupled to the receptacle and a second end operatively coupled to a landing member, the elongated member further having a first composite portion coupled to a second composite portion by a pair of composite sidewall portions and forming an elongated cavity therebetween, wherein the first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein, and wherein the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein, wherein the first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity, and wherein the composite sidewall portions include a plurality of third layers, each third layer having a plurality of third fibers disposed therein, the third fibers being cross-woven and non-parallel with the longitudinal axis, wherein the structurally-weakened portion is configured to structurally fail before the elongated member when a load is applied to the landing member.