Analysis reveals the relationship between damage scale and load capacity in composite laminates, suggesting design improvements for structures with holes.
Composites have a high specific strength, high specific modulus, high-temperature resistance, fatigue resistance, and other advantages, and are widely used in aerospace. Due to the anisotropy of materials, the damage forms and mechanisms of composite structures are significantly different from those of metal materials. Therefore, the research on the relationship between residual compressive strength and damage scale of laminates with holes has important engineering significance. The bearing capacity of T700/BA9916 composite laminates under compression load is studied in this paper. Patran/NASTRAN finite element software was used to analyze composite laminates with a single hole and two holes. The parametric modeling of laminates with holes is realized by PCL language, and the relationship between ultimate load and damage scale is concluded. This can provide theoretical guidance and a basis for the design of the parts with holes in composite structures and the maintenance of the damaged structures with holes.
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Xiaoxia Huang (2025) studied this question.
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