Accession Number:

ADA301800

Title:

Strength of Graphite/Epoxy Bolted Wing-Skin Splice Specimens Subjected to Outdoor Exposure Under Constant Load and Yearly Fatigue Loading.

Descriptive Note:

Technical paper,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Report Date:

1986-01-01

Pagination or Media Count:

36.0

Abstract:

The results of an experimental study to provide long-term durability data on detailed full-scale graphiteepoxy wing-skin joint designs under environmental exposure and cyclic loading associated with commercial transport aircraft are reported. The specimens consisted of a single-row bolt configuration fabricated from T3005208 and a double-row bolt configuration fabricated from T3005209. The unpainted specimens were exposed to the outdoor environment under a sustained tensile load, and at yearly intervals, they were subjected to fatigue loading. Experimental results showed a slight reduction in residual tensile strength for both graphiteepoxy joints under the exposure times and fatigue loadings reported. A 7.5-percent decrease in residual strength was observed for the T3OO52O single-row joint after 5 years exposure and two lifetimes of fatigue loading. A 5.3-percent decrease in residual strength was observed for the T3005209 double-row joint after 7 years exposure and 2.8 lifetimes of fatigue loading. The 5208 epoxy material was more susceptible to degradation by ultraviolet radiation than the 5209 epoxy material

Subject Categories:

  • Commercial and General Aviation
  • Laminates and Composite Materials

Distribution Statement:

APPROVED FOR PUBLIC RELEASE