Abstract
This paper analyzes the post-impact pressure loss test data of eight test configurations of composite fuselage hat-type stringers and measures each composite stringer’s residual compressive strength. It compares the bearing capacity and failure strain of different configurations of stringers with and without BVID initial impact damage. Based on the test data and analysis, the optimal configuration of the stringer is selected, which plays a guiding role in the structural design of composite panels.
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