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<p>This study presents an efficient and unified numerical model to investigate the thermal buckling behavior of composite laminates with cutouts subjected to a uniform temperature field, a critical issue in aerospace, automotive, and marine structures where cutouts are commonly used for access ports, weight reduction, or system integration. The geometry of the cutout is parametrically described using a superelliptic equation, which allows for seamless characterization of various shapes, including diamond, circular, elliptical, and rectangular cutouts, by adjusting the shape index and semi‑axis lengths. The Independent Coordinate Coupling Method (ICCM) is employed to establish independent displacement fields for the intact plate domain and the cutout domain, respectively. By enforcing displacement compatibility conditions within the cutout domain, the two sets of generalized coordinate systems are coupled, thereby avoiding the cumbersome integration required by traditional methods for complex cutout geometries. This work presents, for the first time, a unified framework that integrates the superellipse equation with the ICCM for thermal buckling analysis, enabling seamless parametric study of cutout shape transitions—from diamond to rectangle—which has not been addressed in prior literature. Based on classical laminated plate theory and the principle of minimum potential energy, the governing equations for thermal buckling are derived and transformed into a generalized eigenvalue problem to solve for the critical buckling temperature. Numerical examples systematically analyze the effects of shape index, cutout size, cutout orientation, cutout location, and boundary conditions on the buckling performance. Key findings reveal that the critical buckling temperature varies in three distinct stages with the shape index, and the influence of cutout location is strongly coupled with boundary conditions and cutout dimensions. The results demonstrate excellent agreement with existing studies, providing engineers with a powerful theoretical tool for rapidly assessing the thermal stability of composite structures with various cutout configurations.</p>

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Unified analysis of thermal buckling in composite laminates with cutouts using independent coordinate coupling method and superellipse equations

  • 期刊论文

  • 发表日期：

    2026年7月2日

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  • Mingyang Wang,
  • Changfu Hu

摘要

This study presents an efficient and unified numerical model to investigate the thermal buckling behavior of composite laminates with cutouts subjected to a uniform temperature field, a critical issue in aerospace, automotive, and marine structures where cutouts are commonly used for access ports, weight reduction, or system integration. The geometry of the cutout is parametrically described using a superelliptic equation, which allows for seamless characterization of various shapes, including diamond, circular, elliptical, and rectangular cutouts, by adjusting the shape index and semi‑axis lengths. The Independent Coordinate Coupling Method (ICCM) is employed to establish independent displacement fields for the intact plate domain and the cutout domain, respectively. By enforcing displacement compatibility conditions within the cutout domain, the two sets of generalized coordinate systems are coupled, thereby avoiding the cumbersome integration required by traditional methods for complex cutout geometries. This work presents, for the first time, a unified framework that integrates the superellipse equation with the ICCM for thermal buckling analysis, enabling seamless parametric study of cutout shape transitions—from diamond to rectangle—which has not been addressed in prior literature. Based on classical laminated plate theory and the principle of minimum potential energy, the governing equations for thermal buckling are derived and transformed into a generalized eigenvalue problem to solve for the critical buckling temperature. Numerical examples systematically analyze the effects of shape index, cutout size, cutout orientation, cutout location, and boundary conditions on the buckling performance. Key findings reveal that the critical buckling temperature varies in three distinct stages with the shape index, and the influence of cutout location is strongly coupled with boundary conditions and cutout dimensions. The results demonstrate excellent agreement with existing studies, providing engineers with a powerful theoretical tool for rapidly assessing the thermal stability of composite structures with various cutout configurations.