Evaluation of the Crack Gage Concept for Monitoring Aircraft Flaw Growth Potential. Volume 1. Technical Discussion.
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)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jun 01, 1979
- Accession Number
- ADA076421
Entities
People
- Gary G. Cassatt
Organizations
- Boeing