Accession Number:

ADA301305

Title:

Effect of Measured Material Properties on the Finite Element Analysis of an OH-58 Composite Tail Boom.

Descriptive Note:

Technical memorandum,

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION HAMPTON VA LANGLEY RESEARCH CEN TER

Personal Author(s):

Report Date:

1985-10-01

Pagination or Media Count:

29.0

Abstract:

A static and dynamic finite element analysis was conducted on a U.S. Army OH-58 composite tail boom and compared with test data. The tail boom was a filament-wound graphiteepoxy monocoque structure. The structural design of the composite tail boom skin was based on 50-percent graphite fiber volume. However, material tests on representative samples of the tail boom skin revealed that the graphite fiber-volume fraction varied from 44.6 to 49.3 percent. To determine the effect of using measured material properties, static and dynamic finite element analyses were conducted for three fiber-volume conditions of 45, 48, and 50 percent. The static and dynamic model with the 45-percent fiber-volume graphite skins gave the closest agreement with test data. AN

Subject Categories:

  • Helicopters
  • Laminates and Composite Materials

Distribution Statement:

APPROVED FOR PUBLIC RELEASE