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Published byEmiliano Solly Modified over 2 years ago

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Failure of laminated composites Progressive failure is needed to predict ultimate failure We will limit ourselves to first ply failure

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Maximum strain or maximum stress failure – in plane loads

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Example Prequel

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Tsai-Pagano constants

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A* matrix and laminate strains

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45-deg ply

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Other load combinations

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Laminate failure envelope Combining the two envelopes Does it agree with previous calculations?

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If we wanted to check using Hoffman First need to translate strain limits to stress limits (in Gpa) Next calculate stresses in 0-deg ply How does it look? Please check.

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Terms in Hoffman Criterion Ratios: Criterion adds up to 6.1, large violation. By how much approximately do we need to reduce the stresses? Why the large discerpancy between the two criteria?

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