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Quick Release Assemblies for Aircraft Landing Gear

A technology for aircraft landing gear and release components, applied in landing gear, aircraft parts, aircraft and other directions, can solve the problems of cumbersome, heavy, missing parts, etc.

Active Publication Date: 2017-04-26
HONDA PATENTS & TECH NORTH AMERICA
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

A disconnect assembly may be provided in conjunction with the torque link members to facilitate such disconnection of the torque link members; however, known disconnect devices or assemblies are heavy, overly complex, prone to missing parts, and often cumbersome or cumbersome, and / or likely to be a hindrance in a detached state (e.g., dangling lanyards)

Method used

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  • Quick Release Assemblies for Aircraft Landing Gear
  • Quick Release Assemblies for Aircraft Landing Gear
  • Quick Release Assemblies for Aircraft Landing Gear

Examples

Experimental program
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Effect test

Embodiment Construction

[0020] Referring now to the drawings, which are shown in order to illustrate one or more exemplary embodiments and not to limit them, figure 1 An aircraft landing gear or rack assembly, generally designated by the reference numeral 10, is shown. The aircraft landing gear 10 consists of an aircraft landing gear strut 12 having an upper part 14 and a lower part 16 , wherein the lower part 16 is telescopically and rotationally movable relative to the upper part 14 . The upper part 14 may also be connected to the lower part 16 by a torque link 11 having a secondary torque link member 18, 24 and three connections A, B, C.

[0021] More specifically, the upper torque link member 18 has a first end 20 and a second end 22 . The first end 20 is connected to the upper portion 14 at the upper connection portion A. As shown in FIG. The lower torque link member 24 also has a first end 26 and a second end 28 . The first end 26 is connected to the lower portion 16 at the lower connection ...

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PUM

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Abstract

A torque link member for an aircraft landing gear comprising a first end for connection to a lower or upper portion of an aircraft landing gear and a second end for connection to another torque link member. The locking pin is disposed on one of the upper portion, the lower portion, the first end or the second end. The locking pin is axially movable between an engaged position and a disengaged position, in which the locking pin protrudes to engage the first end, the second end, the upper portion, the lower portion, or the second end of the other torque link member. Mating hole engagement. The latch is biased toward the engaged position and is movable to the disengaged position against the bias.

Description

[0001] This application claims the benefit of US Provisional Patent Application Serial No. 61 / 394,250, filed October 18, 2010, which is hereby incorporated by reference in its entirety. technical field [0002] The present disclosure relates generally to quick release assemblies, and in particular to quick release assemblies for aircraft landing gear struts, although the quick release assemblies may be suitable for other applications as well. Background technique [0003] The front landing gear of an aircraft generally consists of an aircraft landing gear strut of the type having an upper cylindrical portion and a lower piston portion telescopically or reciprocally accommodated in the cylindrical portion. The upper cylindrical portion is connected to the underside of the front portion of the aircraft. A wheel carrier rotatably mounting the landing wheels is fixed to the piston portion. The relative movement between the lower piston portion and the upper cylindrical portion ...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): B64C25/58
CPCB64C25/14B64C25/50B64C2025/006F16C11/02F16C11/045F16C2326/43Y10T403/602
Inventor C.T.奥康奈尔
Owner HONDA PATENTS & TECH NORTH AMERICA