Achieving "One Up Assembly" By Reduction of Interface Burr Height in Aluminum, Graphite, and Advanced Titanium/Graphite Hybrid (Tigr) Material

Document Number: 2003-01-2896

Date Published: September 2003

Author(s):
Tanni Sisco - Boeing Co.

Abstract:
In aircraft assembly, a burr left at the interface of any joint is considered a source of potential fatigue life degradation. Burrs can act as an additional stress concentration, leading to fretting, inducing failures. It could also open moisture paths resulting in corrosion.

Burrs can affect the fatigue life of various structures differently depending on the type of joint, material, fastener, and installation process.

Traditionally, we have disassembled and deburred the interface with various tools such as sand paper, file, chamfer tool, hook, or other tools.

Disassembly and deburring of airplane major parts are time consuming and costly. In addition achieving "one up assembly" is not viable unless interfacial burr can be eliminated or reduced to the point where it will not affect fatigue life.

In this investigation, the possibility of "one up assembly" via creation of concentric and adjacent clamping in various materials is studied. This paper also investigates the effect of interface burr on the fatigue life of the joint.

File Size: 981K
Product Status: In Stock

See other papers presented at Aerospace Manufacturing Technology Conference & Exposition, September 2003, Montreal, QC, CANAD, Session: Advanced Material Joining and Processing

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