Multi-piece fastener with self-indexing nut
a multi-piece, self-indexing technology, applied in the direction of screw, load-modified fastener, coupling, etc., can solve the problems of difficult installation, difficult positioning of traditional attachment methods and fasteners in such regions, and poor ergonomics
Active Publication Date: 2012-03-27
THE BOEING CO
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Problems solved by technology
Aerospace and military applications often provide unique challenges to design and manufacturing.
Often manufacturing requires the assembly of multiple elements within regions providing limited clearance and reduced accessibility.
Traditional attachment methodologies and fasteners may be difficult to position within such regions.
The use of traditional fasteners, such as commonly used bolt assemblies, can result in difficult installation, ergonomic issues, inconsistent torque application, and sub-optimum joint fatigue performance.
One such assembly that suffers from the aforementioned concerns is the wing side-of-body joint assembly used in aerospace applications.
The limited clearance present in the chord elements, however, dictates undesirable constraints on how the bolts may be orientated and their installation sequence.
Often, limited clearance may make traditional bolt assemblies virtually impossible to utilize or re-torque after installation.
Torque application from the head side often results in the bolt turning inside the hole, which can score the bolt and / or fastener and result in galling and improper bolt tensioning.
The limited clearance imposed by the chord elements, however, makes such nut-side torque application unfeasible in certain locations.
Further difficulties arise where a fastener assembly requires a precisely tightened nut (threaded head fastener).
As the nut is located in a low clearance region, examination of the nut is difficult or impossible while it is being tightened.
This tightening and re-tightening process requires much trial and error which is time-consuming and difficult.
Method used
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[0024]Referring now to FIG. 1, which is an illustration of an aircraft 10 in accordance with the present invention. The aircraft 10 is comprised of a plurality of joint assemblies wherein traditional fastening and assembly techniques may unfeasible or cost prohibitive. One such joint assembly is referred to as the wing side-of-body joint assembly 12, see FIG. 2. The wing side-of-body joint assembly 12 is located where the wing 14 joints the aircraft body side 16. This joint assembly 12 is very important as it is used to join a variety of structures together to form a reliable joint that is preferably highly resistant to joint fatigue.
[0025]As illustrated in FIG. 2, the joint assembly 12 is used to join a variety of different structures. Aluminum or titanium chords 18, also referred to as a first joint element, are utilized to join primary structures such as aluminum or carbon fiber-reinforced composite skin elements 20, also referred to as a second joint element, stringers 22, strin...
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According to a preferred embodiment, a multi-piece fastener with self-indexing nut is disclosed. The multi-piece fastener is designed for use in low clearance areas such as aircraft wing side-of-body joint locations. The multi-piece fastener comprises a stud comprising an elongated part extending between a first end face and a second end face, a threaded head fastener, a threaded tail fastener, and a wrenching feature. A self-indexing feature is provided on the stud and head fastener which allows automatic orientation of the head fastener with respect to the stud.
Description
RELATED APPLICATION[0001]This application is a continuation-in-part of, and claims priority from, pending prior application Ser. No. 11 / 162,260 filed Sep. 2, 2005, and is incorporated by reference herein.TECHNICAL FIELD[0002]The present invention relates generally to a method and apparatus for improving installation of joint elements in limited clearance situations, and more particularly to a method and apparatus utilizing a multi-piece fastener to secure joint elements.BACKGROUND[0003]Aerospace and military applications often provide unique challenges to design and manufacturing. Often manufacturing requires the assembly of multiple elements within regions providing limited clearance and reduced accessibility. Traditional attachment methodologies and fasteners may be difficult to position within such regions. In addition, assembly of such structures commonly requires precise tensioning of such fasteners to minimize stresses and insure proper functioning. The use of traditional fast...
Claims
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IPC IPC(8): F16B35/00
CPCB64C1/06F16B5/0275B64C1/26Y10T403/75Y10T29/49948
Inventor PORTER, JOHN R.RUFIN, ANTONIO C.
Owner THE BOEING CO
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