Hydraulic actuator for semi levered landing gear

Active Publication Date: 2012-05-24
THE BOEING CO
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Benefits of technology

[0011]The advantageous embodiments also provide for an actuator including a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons are contained within a common outer wall. A manifold is connected to the first, second, and third hydraulic pistons. The manifold is disposed relative to the first, second, and third hydraulic pistons such that a fluid moving in the manifold can control positions of the first, second, and third hydraulic pistons.
[0012]The embodiments also provide for a vehicle including a fuselage, a wing connected to the fuselage, and a landing gear assembly connected to at least one of the fuselage and the wing. The vehicle further includes a hydraulic actuator connected to the landing gear assembly. The hydraulic actuator includes a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons ar

Problems solved by technology

The use of a shrink-link disadvantageously increases the complexity, expense and weight of the resulting semi-levered landing gear.
Mechanical linkages also may not provide sufficiently desired damping during landing or bogie beam pitch dampening while on the ground.
While a s

Method used

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  • Hydraulic actuator for semi levered landing gear
  • Hydraulic actuator for semi levered landing gear
  • Hydraulic actuator for semi levered landing gear

Examples

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Embodiment Construction

[0026]The present invention now will be described more fully hereinafter with reference to the accompanying drawings, in which preferred advantageous embodiments of the invention are shown. This invention may, however, be embodied in many different forms and should not be construed as limited to the advantageous embodiments set forth herein; rather, these advantageous embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. Like numbers refer to like elements throughout.

[0027]The advantageous embodiments recognize these issues and present a solution that is flexible, durable, relatively inexpensive compared to other struts, and light weight. Additionally, the advantageous embodiments have added further value to aircraft operation in that the advantageous embodiments aid an aircraft in both landing and lift off. The advantageous embodiments aid an aircraft to lift off by increasing the a

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Abstract

A device including a first hydraulic piston, a second hydraulic piston disposed within the first hydraulic piston, and a third hydraulic piston disposed within both the first hydraulic piston and the second hydraulic piston. The first, second, and third hydraulic pistons are contained within a common outer wall. A manifold is connected to the first, second, and third hydraulic pistons. The manifold is disposed relative to the first, second, and third hydraulic pistons such that a fluid moving in the manifold can control positions of the first, second, and third hydraulic pistons.

Description

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Claims

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Application Information

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Owner THE BOEING CO
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