Advanced residual strength degradation rate Modeling for advanced composite structures.
Volume 2.
Tasks II and III /
K.N. Lauraitis, J.T. Ryder, D.E. Pettit.

Description

Main Author

Lauraitis, K. N.

Related Names

Pettit, D. E., author.
Ryder, J. T., author.
Air Force Wright Aeronautical Laboratories
Air Force Flight Dynamics Laboratory (U.S.)
Lockheed-California Company

Language(s)

English

Published

Wright-Patterson Air Force Base, Ohio : Flight Dynamics Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, United States Air Force, 1981.

Subjects

Statics > Statics / Testing.
Strength of materials.
Materials > Materials / Fatigue.
Laminated materials.
Composite materials.

Summary

This report presents the results of the first task of the last two tasks of a three-task program focusing on the study of relationship between damage propagation and residual strength of graphite/epoxy laminates. Specimens of two laminate types, a 32-ply quasi-isotropic and 24-ply 67%-0, containing a centered poorly drilled hole were evaluated in this study. Baseline static tension and compression tests were conducted at high and low strain rates and at elevated temperature.

Note

Research supported by the United States Air Force Wright Aeronautical Laboratories, Flight Dynamics Laboratory, and performed by Lockheed-California Company.
"The program was conducted by the Structures and Materials Department of the Lockheed-California Company."
"Final Report for 1 July 1979 to 29 May 1981."
ADA115184 (from http://www.dtic.mil).
"July 1981."

Physical Description

xliv, 281 pages : illustrations, figures, tables ; 28 cm.

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