Accession Number:

ADA080927

Title:

Compression Fatigue of Impact Damaged Graphite Epoxy Sandwich Beams.

Descriptive Note:

Final rept.,

Corporate Author:

NAVAL AIR DEVELOPMENT CENTER WARMINSTER PA AIRCRAFT AND CREW SYSTEMS TECHNOLOGY DIRECTORATE

Personal Author(s):

Report Date:

1978-04-20

Pagination or Media Count:

53.0

Abstract:

The resistance of composite aircraft structures to handling and impact loadings is an important consideration in assessing their suitability for long term operational service. The specific threat addressed in this study is that of low speed 0 to 30ms, hard object, transverse normal impact dropped tool, runway stones, etc.. The objective is to characterize the damage which occurs to composite faced sandwich structures under realistic impact conditions and determine the effect of this damage on residual compression fatigue properties. The sandwich construction selected for study consisted of AS3501-6 graphiteepoxy face sheets of 0 OR - 450 SUBS CONSTRUCTION BONDED TO HRP-316-5.5 honeycomb core. This construction is representative of sandwich construction generally used in flaps, spoilers, and access doors. Static indentation tests were conducted on sandwich panels supported on a rigid foundation, and dropped weight impact tests were performed on simply supported sandwich beams. Comparison of the results of these tests indicates that static tests in conjunction with a simple 2-degree-of-freedom dynamic model can be used to accurately simulate low velocity, hard object impacts on sandwich structures for impact velocities up to 6.1 ms. Test results of indentation versus static load is used in the dynamic model to predict the indentation which would occur for any particular impact case.

Subject Categories:

  • Aircraft
  • Laminates and Composite Materials
  • Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE