Composite landing gear apparatus and methods
First Claim
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.
1 Assignment
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Accused Products
Abstract
Composite landing gear apparatus and methods are disclosed. In one embodiment, a composite component includes an elongated member having a first composite portion coupled to a second composite portion by a pair of composite sidewall portions and forming an elongated cavity therebetween. The first composite portion includes a plurality of first layers, each first layer having a plurality of first fibers disposed therein. Similarly, the second composite portion includes a plurality of second layers, each second layer having a plurality of second fibers disposed therein. The first and second fibers are oriented substantially parallel to a longitudinal axis of the elongated cavity. 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.
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Citations
8 Claims
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1. A landing gear assembly for an aircraft, comprising:
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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. - View Dependent Claims (2, 3, 4)
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5. A landing gear assembly for an aircraft, comprising:
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a receiving member configured to be coupled to a frame member of the aircraft, the receiving member including a receiving portion defining a 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 receiving portion includes a wall member having at least one aperture disposed therein, the first end of the elongated member being coupled to the receptacle by an attachment member passing through the aperture, the wall member including a structurally-weakened portion proximate the aperture. - View Dependent Claims (6)
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7. A landing gear assembly for an aircraft, comprising:
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a receiving member adapted to be coupled to a frame member of the aircraft, the receiving member including a receiving portion defining a receptacle, wherein the receiving portion includes a wall member having at least one aperture disposed therein, the wall member including a structurally-weakened portion proximate the aperture and an elongated member having a first end disposed within the receptacle and a second end operatively coupled to a landing member, the first end of the elongated member being coupled to the receptacle by an attachment member passing through the aperture, the structurally-weakened portion being adapted to structurally fail at a first load level applied to the landing member, and the elongated member being adapted to structurally fail at a second load level applied to the landing member, the first load level being lower than the second load level. - View Dependent Claims (8)
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Specification