Abstract
The use of carbon fiber reinforced polymer (CFRP) composites in modern aircraft has become common as a result of the advantage in the strength to weight ratio the material provides. A limitation to using CFRPs on aircraft stem from their low resistance to low velocity impact (LVI) damage. In these instances, LVI causes barely visible impact damage (BVID) such that the indication of impact on the structure is barely noticeable. These impacts have the potential to generate fiber and matrix failure and cause delamination between lamina which ultimately reduces the compressive load carrying capability of the composite. This study performs an experimental analysis on the knockdown in compressive load carrying capability over a range of impact energies that produce BVID on thick composite panels of 40, 48, and 56 plies.
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