Effect of impact damage on the compression strength of filamentary-composite hat-stiffened panels
An experimental investigation was conducted to evaluate the effect of low-velocity impact damage on the compression strength of filamentary-composite hat-stiffened panels. Twenty-four specimens of three design configurations fabricated from graphite-epoxy and boron-epoxy materials were tested. All three design configurations met the design buckling requirements in the undamaged condition. The impact damage was caused by firing aluminum spheres at the panels to simulate impact on aircraft from runway stones. Panels were damaged by impact in the hat cap or in the skin beneath the hat cap (regions of high axial stiffness) and in the skin between stiffeners (region of low axial stiffness). The panels were relatively insensitive to impact damage in the regions of low axial stiffness but were very sensitive to impact damage in the regions of high axial stiffness. Test results suggest that impact damage may be more dependent on the matrix properties than on the fiber properties of the composite materials considered.
- Research Organization:
- NASA Langley Research Center, Hampton, VA
- OSTI ID:
- 6833100
- Report Number(s):
- CONF-780502-
- Journal Information:
- Sci. Adv. Mater. Process Eng. Proc.; (United States), Journal Name: Sci. Adv. Mater. Process Eng. Proc.; (United States) Vol. 23; ISSN SMPCB
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
360303* -- Composite Materials-- Mechanical Properties-- (-1987)
AIRCRAFT COMPONENTS
BORON
CARBON
COMPOSITE MATERIALS
COMPRESSION STRENGTH
DAMAGE
DESIGN
ELEMENTAL MINERALS
ELEMENTS
EPOXIDES
FAILURE MODE ANALYSIS
GRAPHITE
IMPACT TESTS
MATERIALS
MATERIALS TESTING
MECHANICAL PROPERTIES
MECHANICAL TESTS
MINERALS
NONMETALS
ORGANIC COMPOUNDS
ORGANIC OXYGEN COMPOUNDS
SEMIMETALS
SYSTEM FAILURE ANALYSIS
SYSTEMS ANALYSIS
TESTING