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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

This paper compares the ballistic impact response of advanced fiber composites and metals. These comparisons are made within the framework of a methodology that defines the necessary data and analysis requirements for evaluating the survivability of combat aircraft designs.

A side-by-side comparison was made of the available residual strength and damage size test data for metals and fiber composites damaged by small arms projectiles. In addition, the available composite data was used to extend a model for predicting the ultimate strength of composite tension panels damaged by bullets. This model was used in conjunction with an existing model for metals to extend the comparisons to equal strength, equal stiffness, or equal weight structural panels.

The results show that both metal and fiber composite panels lose a significant percent of their undamaged strength (50 percent or more) when impacted with small arms projectiles. For the cases considered, the percent reduction in the fiber composite panels was greater than in the metal panels. These results are considered to be preliminary for structural evaluations, however, because only simple panel data were used in the comparison.

1.
Avery
,
J. G.
and
Porter
,
T. R.
, “
A Parametric Evaluation of Lightweight Metal and Composite Structure Exposed to Gunfire
,” Army Symposium on Solid Mechanics,
Ocean City, Md.
,
1972
.
2.
Olster
,
E. F.
and
Woodbury
,
H. A.
, “
Evaluation of Ballistic Damage Resistance and Failure Mechanisms of Composite Materials
,” Avco Corp., Air Force Contract F33615-70-C-1570, AFML-TR-72-79,
04
1972
.
3.
Suarez
,
J. A.
, “
Vulnerability of Composite Aircraft Structures
,” Grumman Aerospace Corp., Air Force Contract F33615-71-C-1111, AFFDL-TR-72-8,
02
1972
.
4.
Advanced Development on Vulnerability/Survivability of Advanced Composite Structures
,” McDonnell-Douglas Corp., Air Force Contract F33615-71-C-1414, AFML-TR-73-152,
05
1973
.
5.
Hayes
,
R. D.
 et al
, “
Flightworthy Graphite Fiber Reinforced Composite Aircraft Primary Structural Assemblies
,” Northrup Corp., Air Force Contract F33615-69-C-1490 (Project 6169), AFML-TR-71-276,
04
1972
.
6.
Avery
,
J. G.
and
Burch
,
G. T.
, Jr.
, “
An Aircraft Structural Combat Damage Model
,” The Boeing Co., Air Force Contract F33615-69-C-1581, AFFDL-TR-70-115 and 116,
11
1970
.
7.
Jones
,
B.
,
Durchlaub
,
E.
, and
Beta
,
B.
Aircraft Structural Vulnerability to Conventional Weapons
,” Martin Marietta Corp., Air Force Contract F33615-67-C-1660, AFFDL-TR-68-105,
08
1968
.
8.
Jensen
,
J.
and
Thorndyke
,
P.
, “
Aircraft Wing Structural Concepts with Improved Ballistic Damage Tolerance
,” GDC-DDG69-002,
General Dynamics, Convair Div.
,
1969
.
9.
Avery
,
J. G.
,
Porter
,
T.R.
, and
Walter
,
R. W.
, “
Designing Aircraft Structure for Resistance and Tolerance to Battle Damage
,” AIAA 4th Aircraft Design, Flight Test, and Operations Meeting,
08
1972
.
10.
Repair Technology for Boron/Epoxy Composites
,” Interim Report, Air Force Materials Laboratory Contract F33615-69-C-1498,
Grumman Aircraft Engineering Corp.
11.
Rogers
,
C. W.
 et al
, “
Structural Airframe Application of Advanced Composite Materials
,” Vol.
4
, Sec. 4, AFML-TR-69-101,
10
1969
.
12.
Bowie
,
O. L.
, “
Analysis of an Infinite Plate Containing Radial Cracks Originating from the Boundary of an Internal Circular Hole
,”
Journal of Mathematics and Physics
 0097-1421, Vol.
35
,
1956
.
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