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Purpose <p>In aerospace engineering, composite bolted joints are critical components that may be subjected to complex&#xa0;shock loads characterized by short duration, high load amplitude, and a broad frequency spectrum. This study&#xa0;presents a novel damage boundary model based on the shock response spectrum (SRS) to evaluate the reliability of&#xa0;composite bolted joints under such extreme conditions.</p> Methods <p>Composite bolted joints were fabricated using T300 carbon fibers and epoxy resin laminates. Controlled&#xa0;shock loading was applied using a high-acceleration pneumatic shock test system. The shock loads were quantified&#xa0;through pseudo-velocity and absolute acceleration parameters, and the structural response was analyzed using the&#xa0;finite element method (FEM). To further understand the dynamic stress behavior, the empirical mode decomposition&#xa0;(EMD) technique was employed to extract intrinsic mode functions (IMFs) from the time-domain stress responses.&#xa0;These IMFs allowed for a detailed assessment of the modal contributions to the overall stress. An optimized mode&#xa0;superposition approach was then used to establish a damage failure boundary specific to complex shock&#xa0;environments.</p> Results and Conclusions <p>The results demonstrate that the proposed model can effectively predict damage&#xa0;boundary in composite bolted joints subjected to complex shock loading. The maximum relative error between&#xa0;dominant modal frequencies obtained from FEM and experimental data was less than 2%. The predicted damage&#xa0;boundaries consistently fell within a ±1.5 dB envelope of the corresponding simulated boundaries. Moreover, the&#xa0;integration of EMD with the ABS-SUM modal superposition method achieved a prediction error of less than 2.5% for&#xa0;critical equivalent stress, significantly outperforming traditional SRSS and CQC methods.</p>

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Damage Failure Boundary of Composite Bolted Joints Under Complex Shock Environments

  • 期刊论文

  • 发表日期：

    2025年6月7日

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  • Shuai Ma,
  • Yifei Nan,
  • Yi Sun,
  • Yongbin Dang

摘要

Purpose

In aerospace engineering, composite bolted joints are critical components that may be subjected to complex shock loads characterized by short duration, high load amplitude, and a broad frequency spectrum. This study presents a novel damage boundary model based on the shock response spectrum (SRS) to evaluate the reliability of composite bolted joints under such extreme conditions.

Methods

Composite bolted joints were fabricated using T300 carbon fibers and epoxy resin laminates. Controlled shock loading was applied using a high-acceleration pneumatic shock test system. The shock loads were quantified through pseudo-velocity and absolute acceleration parameters, and the structural response was analyzed using the finite element method (FEM). To further understand the dynamic stress behavior, the empirical mode decomposition (EMD) technique was employed to extract intrinsic mode functions (IMFs) from the time-domain stress responses. These IMFs allowed for a detailed assessment of the modal contributions to the overall stress. An optimized mode superposition approach was then used to establish a damage failure boundary specific to complex shock environments.

Results and Conclusions

The results demonstrate that the proposed model can effectively predict damage boundary in composite bolted joints subjected to complex shock loading. The maximum relative error between dominant modal frequencies obtained from FEM and experimental data was less than 2%. The predicted damage boundaries consistently fell within a ±1.5 dB envelope of the corresponding simulated boundaries. Moreover, the integration of EMD with the ABS-SUM modal superposition method achieved a prediction error of less than 2.5% for critical equivalent stress, significantly outperforming traditional SRSS and CQC methods.