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<p>Understanding the cyclic response of aerospace materials is essential for aircraft structural safety and reliability. This study investigates the shear plastic behavior of Carbon Fiber Reinforced Thermoplastic Polymer (CFRTP) composite laminates under cyclic loading, focusing on ply orientation effects. Monotonic tensile tests on T700/PEKK composite laminates with two different ply angles revealed significant differences in stress–strain behavior across orientations in both elastic and plastic phases. Novel cyclic loading–unloading tests were then designed and performed to address gaps in existing literature. A simplified constitutive model for transversely isotropic media was developed based on micromechanical principles, accounting for ply orientation effects. This model, implemented as a user-defined material subroutine (UMAT), accurately predicts the shear plastic behavior of unidirectional CFRTP laminates across various ply angles. The model demonstrates significant engineering applications in aerospace structural design and safety assessment. It can be integrated into design workflows for critical components, enabling precise weight optimization while maintaining safety margins. Additionally, it provides valuable insights for analyzing joint regions, designing impact-resistant structures, and predicting residual strength after plastic deformation under complex loading conditions representative of actual flight profiles. This research contributes to understanding composite aircraft structure durability and reliability, supporting their safe and efficient service life while reducing certification testing costs.</p>

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Modeling nonlinear behavior of T700/PEKK thermoplastic composites under shear cyclic loading for aerospace applications

  • 期刊论文

  • 发表日期：

    2025年6月23日

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  • Linghui Liu,
  • Zhikai Zhao,
  • Xiuhua Chen

摘要

Understanding the cyclic response of aerospace materials is essential for aircraft structural safety and reliability. This study investigates the shear plastic behavior of Carbon Fiber Reinforced Thermoplastic Polymer (CFRTP) composite laminates under cyclic loading, focusing on ply orientation effects. Monotonic tensile tests on T700/PEKK composite laminates with two different ply angles revealed significant differences in stress–strain behavior across orientations in both elastic and plastic phases. Novel cyclic loading–unloading tests were then designed and performed to address gaps in existing literature. A simplified constitutive model for transversely isotropic media was developed based on micromechanical principles, accounting for ply orientation effects. This model, implemented as a user-defined material subroutine (UMAT), accurately predicts the shear plastic behavior of unidirectional CFRTP laminates across various ply angles. The model demonstrates significant engineering applications in aerospace structural design and safety assessment. It can be integrated into design workflows for critical components, enabling precise weight optimization while maintaining safety margins. Additionally, it provides valuable insights for analyzing joint regions, designing impact-resistant structures, and predicting residual strength after plastic deformation under complex loading conditions representative of actual flight profiles. This research contributes to understanding composite aircraft structure durability and reliability, supporting their safe and efficient service life while reducing certification testing costs.