Aircraft joint, aircraft assembly, installation tool and structural part joining method
A technology for structural components and aircraft, applied in aircraft assembly, aircraft parts, rotating parts that resist centrifugal force, etc., can solve problems such as increased cost, structural component cost, heavy maintenance, irregularity, etc.
Pending Publication Date: 2019-06-04
AIRBUS OPERATIONS GMBH
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Problems solved by technology
This conservative approach ultimately results in designs that require a greater number of fasteners to transfer a given load, resulting in a higher degree of redundancy, however, the structural assembly also costs more due to the increased number of attached parts to manufacture, would be heavier and require more maintenance
Furthermore, in some cases, the holes may be so irregular that redundancy will not compensate for incorrect seating of the fasteners, resulting in the holes and solid bushings needing to be reworked, or even causing the part to be scrapped
Additionally, the use of various sizes of solid bushings requires storage and asset management, which takes up space on the assembly floor and resources
Furthermore, the process of fitting a solid bushing into an existing bore may itself lead to damage to the component, especially in the case of composite materials
This in turn may require reworking, which may be time consuming and thus potentially costly
Method used
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Embodiment Construction
[0020] refer to figure 1 , shows an aircraft 101 having wings 103 (wings also referred to as airfoils) extending generally horizontally across a fuselage 105 . Extending substantially horizontally from either side of the rear portion of the fuselage 105 is another wing 107 (also referred to as a horizontal stabilizer). Extending vertically from the rear upper part of the fuselage 105 is a further wing 109 (also referred to as a vertical empennage).
[0021] The wings 103, 109, 107 and fuselage 105 may be formed from structural components joined together by structural joints that serve to constrain movement of at least one pair of components relative to each other once the joint is secured, in other words, the pair The components are fixedly attached to each other. Each structural component may itself be formed from smaller structural components joined together by a further number of joints.
[0022] The wings 103, 107, 109 each have a leading edge 111 and a trailing edge 11...
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Abstract
An aircraft joint comprises: a first structural component provided with an attachment hole that is configured to receive an corresponding attachment fastener provided by a second structural component;a curable composite bush compressed and cured between an outer diameter of the attachment fastener and the attachment hole when the first component is mounted to the second component, wherein the curable composite bush, when cured, prevents radial displacement of the attachment fastener within the attachment hole. The invention also provides an aircraft assembly comprising the aircraft joint, a tool for installing the composite bush and a method for joining a first aircraft structural component to the second aircraft structural component.
Description
technical field [0001] The present technology relates to curable composite liners for aircraft joints, aircraft joints, aircraft structural assemblies including the aircraft joints, and methods and tools for installing curable composite liners. Background technique [0002] During assembly of an aircraft structure, it is known to attach two or more parts by drilling and installing one or more fasteners in predetermined hole positions after they are mounted in a fixed position relative to each other. One or more components are attached together at joints. Once the fasteners are installed, the joints are made and the larger structural assembly is formed. It is known that solid liners can be used during assembly of structural joints and components. Solid bushings are used when there is an undesired eccentricity or play between the fastener and the corresponding hole in which it is seated, and this undesired eccentricity or play is to be eliminated to ensure proper fit of the ...
Claims
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IPC IPC(8): B64C1/00B64C1/06B64F5/10
CPCB64C3/26B64F5/10Y02T50/40F16C33/201F16C33/208F16C2208/82F16C2208/04B64C3/50B64C3/28B29C65/4835
Inventor 弗洛里安·洛伦茨达斯廷·沙皮
Owner AIRBUS OPERATIONS GMBH