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Reliability aspects of a composite bolted scarf jointThe design, fabrication, static test, and fatigue test of both tension and compression graphite-epoxy candidates for a wing splice representative of a next-generation transport aircraft was the objective of the reported research program. A single-scarf bolted joint was selected as the design concept. Test specimens were designed and fabricated to represent an upper-surface and a lower-surface panel containing the splice. The load spectrum was a flight-by-flight random-load history including ground-air-ground loads. The results of the fatigue testing indicate that, for this type of joint, the inherent fatigue resistance of the laminate is reflected in the joint behavior and, consequently, the rate of damage accumulation is very slow under realistic fatigue loadings.
Document ID
19760033591
Document Type
Conference Proceedings
Authors
Reed, D. L. (General Dynamics/Fort Worth TX, United States)
Eisenmann, J. R. (General Dynamics Corp. Fort Worth, Tex., United States)
Date Acquired
August 8, 2013
Publication Date
January 1, 1975
Subject Category
STRUCTURAL MECHANICS
Funding Number(s)
CONTRACT_GRANT: NAS1-11974
Distribution Limits
Public
Copyright
Other