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ASTM Selected Technical Papers
Composite Materials: Fatigue and Fracture (Third Volume)
By
TK O'Brien
TK O'Brien
1
U.S. Army Aerostructures Directorate (AVSCOM), NASA Langley Research Center
,
Hampton, Virginia
;
symposium chairman and editor
.
Search for other works by this author on:
ISBN-10:
0-8031-1419-2
ISBN:
978-0-8031-1419-7
No. of Pages:
838
Publisher:
ASTM International
Publication date:
1991

This research studied the effects of an inserted circular delamination on the strength of an eight-ply, quasi-isotropic composite laminate. Cylindrical panels were loaded compressively, and the global buckling load of the delaminated plies were examined. It was found that, for the level of delamination defect investigated, a linear bifurcation analysis gave fairly accurate predictions of the global panel strength. Load values, which caused local instabilities in the region of panel damage, were also recorded and compared to an approximate analysis.

During the experimental phase of this research, certain physical responses of the panels led to a set of simplifying assumptions. It was thought that there existed a value of strain that when applied to a circular delamination would cause the sublaminate to buckle. The value of strain in the sublaminate should be related to a value of strain in the curved panel. Some method of relating these two values of strain was suggested by the results of experimental tests.

1.
Horban
,
B. A.
and
Palazotto
,
A. N.
, “
Experimental Buckling of Cylindrical Composite Panels with Eccentrically Located Circular Delaminations
,”
Journal of Spacecraft and Rockets
 0022-4650, Vol.
24
, No.
4
, July–Aug., 1987, pp. 349–352.
2.
Siefert
,
G. R.
and
Palazotto
,
A. N.
, “
The Effect of a Centrally Located Midplane Delamination on the Instability of Composite Panels
,”
Journal of Experimental Mechanics
, Vol.
26
, No.
4
,
12
1986
, pp. 330–336.
3.
Wilkins
,
D. J.
, “
Compression Buckling Tests of Laminated Graphite/Epoxy Curved Panels
,” AIAA Paper No. 74-32, presented at the AIAA Twelfth Aerospace Sciences Meeting,
Washington, DC
,
American Institute of Aeronautics and Astronautics
,
30
01
1974
.
4.
Almroth
,
B. O.
,
Brogan
,
F. A.
, and
Stanley
,
G. M.
, “
Structural Analysis of General Shells
,”
Volume II User Instruction for STAGSC-1
,
Lockheed Palo Alto Research Laboratory
,
CA
,
01
1981
.
5.
Sandhu
,
R. S.
, “
Alternate Strength Analysis of Symmetric Laminates
,” Technical Report AFFDL-TR-73-137, AD 779927,
Air Force Flight Dynamics Laboratory
, Wright Patterson Air Force Base, OH,
02
1974
.
6.
Dym
,
C. L.
and
Shames
,
I. H.
,
Solid Mechanics—A Variational Approach
,
McGraw-Hill
,
New York
,
1973
.
7.
Shivakumar
,
K. N.
and
Whitcomb
,
J. D.
, “
Buckling of a Sublaminate in a Quasi-Isotropic Composite Laminate
,”
Journal of Composite Materials
, Vol.
19
,
01
1985
, pp. 2–18.
8.
Wilder
,
B. L.
, “
A Study of Damage Tolerance In Curved Composite Panels
,” Masters thesis,
School of Engineering, The Air Force Institute of Technology
, AFIT/GA/AA/88M-3,
03
1988
.
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