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ASTM Selected Technical Papers
Foreign Object Impact Damage To Composites
By
LB Greszczuk
LB Greszczuk
1
McDonnell Douglas Astronautics Co.
,
Huntington Beach, Calif. symposium chairman
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ISBN-10:
0-8031-0357-3
ISBN:
978-0-8031-0357-3
No. of Pages:
252
Publisher:
ASTM International
Publication date:
1975

The residual static and impact fracture strengths of boron/epoxy laminates were obtained from tests using .30 and .50-caliber AP and 23-mm API projectiles. These strengths were compared to the static fracture and impact fracture strengths of 6A1-4V titanium, 7075-T6 aluminum, and 2024-T81 aluminum. Results have shown that the boron/epoxy system possesses residual and impact fracture tension strengths as high or higher than those exhibited by metals of similar strength, when maximum structural damage envelopes are considered. All testing was performed using composite panel thicknesses and projectile diameters which resulted in thickness to diameter ratios in the range, 0.051 < T/D < 0.153.

1.
Suarez
,
J. A.
, “
Vulnerability of Composite Aircraft Structures
,” Technical Report AFFDL-TR-72-8,
Air Force Flight Dynamics Laboratory
,
1972
.
2.
Olster
,
E. F.
and
Woodbury
,
H. A.
, “
Evaluation of Ballistic Damage Resistance and Failure Mechanisms of Composite Materials
,” Technical Report AFML-TR-72-79,
1972
.
3.
Clark
,
H. T.
, “
Advanced Development on Vulnerability/Survivability of Advanced Composite Structures
,” Interim Reports, Air Force Contract F33615-71-C-1414,
McDonnell Aircraft Company
, 1971–1973.
4.
Burch
,
J. T.
, Jr.
and
Avery
,
J. G.
, “
An Aircraft Structural Combat Damage Model
,” Technical Report AFFDL-TR-70-115, Vol.
1
,
Air Force Flight Dynamics Laboratory
,
1970
.
5.
MIL-A-8866 (ASG),
Flight Maneuver Load Spectra
,
1960
.
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