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Accession Number:
ADA076421
Title:
Evaluation of the Crack Gage Concept for Monitoring Aircraft Flaw Growth Potential. Volume 1. Technical Discussion.
Corporate Author:
BOEING WICHITA CO KS
Report Date:
1979-06-01
Abstract:
The results of a test program to evaluate the ability of a bonded on precracked coupon to monitor the growth of flaws in the basic structure are included. All testing utilized 7075-T651 aluminum from a single plate. Both constant thickness and stepped crack gages were evaluated. Evaluation of a wide range of sensitivity in crack gage crack growth response was made. Structure flaws of, 1 corner flaw at a hole, 2 through flaws at a hole and 3 center notch flaw were evaluated. The cyclic test loading included constant amplitude of two R ratios and three representative aircraft usage flight profiles. Strain gage instrumentation was used to measure structure stresses and load transferred into the crack gages. Author
Descriptive Note:
Final rept. 1 Jul 77-1 Dec 78,
Supplementary Note:
See also Volume 2, AD-A076 320.
Pages:
0113
Contract Number:
F33615-77-C-5073
File Size:
36.49MB
