Accession Number:

ADA191058

Title:

Impact Damage Tolerance of Carbon Fibre and Hybrid Laminates.

Descriptive Note:

Technical rept.,

Corporate Author:

ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)

Personal Author(s):

• Dorey, G.
• Sigety, P.
• Stellbrink, K.
• Hart, W. G.

Report Date:

1987-10-01

Pagination or Media Count:

68.0

Abstract:

This was the second phase of a collaborative research programme on impact damage tolerance of composite materials, carried out at four European aerospace research establishments under the auspices of GARTEUR Action Group SMAG01. The first phase had been a round robin that established that the four laboratories could produce similar results on a common carbon fibre laminate, showing that barely visible impact damage BVID significantly reduced the static strength but had little effect on the fatigue strength at 10 to the 6th power cycles of fully reversed axial loading. The second phase tended to confirm the results of phase one over a wider range of materials and test parameters. Studies were made of the damage growth under fatigue loading. Improvements in performance were achieved by the use of surface plies of various fabrics. Keywords Great Britain.

Descriptors:

• *LAMINATES
• *FIBER REINFORCED COMPOSITES
• *REINFORCED PLASTICS
• CARBON FIBERS
• FATIGUE(MECHANICS)
• LOADS(FORCES)
• LABORATORIES
• HYBRID SYSTEMS
• LAMINATES
• DAMAGE
• GROWTH(GENERAL)
• STRENGTH(MECHANICS)
• UNITED KINGDOM
• TOLERANCE
• AXES
• LOAD DISTRIBUTION
• IMPACT TESTS
• STRENGTH WEIGHT RATIO
• TABLES(DATA)

Subject Categories:

• Laminates and Composite Materials
• Plastics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE