定应力老化下固体发动机界面力学性能退化及寿命评估方法

  • 孙海涛 ,
  • 戴凡皓 ,
  • 袁杰红 ,
  • 周坤林 ,
  • 李道奎 ,
  • 申志彬
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  • 1. 国防科技大学
    2. 国防科技大学空天科学学院

收稿日期: 2025-12-03

  修回日期: 2026-04-15

  网络出版日期: 2026-04-20

基金资助

国家自然科学基金

Method for evaluating interfacial mechanical property degradation and service life of solid rocket motors under constant-stress aging

  • SUN Hai-Tao ,
  • DAI Fan-Hao ,
  • YUAN Jie-Hong ,
  • ZHOU Kun-Lin ,
  • LI Dao-Kui ,
  • SHEN Zhi-Bin
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Received date: 2025-12-03

  Revised date: 2026-04-15

  Online published: 2026-04-20

摘要

固体火箭发动机粘接界面的长期贮存老化是影响结构可靠性的关键问题之一。现有高温加速试验方法难以真实反映服役状态下的应力-时间耦合场,对界面性能衰减规律的预测存在局限。在接近实际贮存温度条件下开展了多应力水平挂载老化试验,并提取最大抗拉强度、最大伸长率和有效断裂能等力学参数。建立了考虑时间-应力耦合效应的指数型老化动力学模型,并引入Zhukov关系描述性能变化速率与老化应力之间的定量关系。结果表明,在高应力条件下,最大抗拉强度在老化前10天内即下降至初始值的约60%,有效断裂能降至约三分之一;而在低应力条件下性能衰减幅度明显减缓,体现出显著的应力依赖性和时间累积效应。进一步结合某立式贮存发动机有限元仿真,提取了衬层界面Mises应力历程,将所建老化模型与服役应力相匹配,预测粘接界面安全贮存寿命约为8.4年。该方法能够定量表征界面老化过程,为界面寿命评估提供依据,并为发动机结构安全性分析和贮存可靠性设计提供参考。

本文引用格式

孙海涛 , 戴凡皓 , 袁杰红 , 周坤林 , 李道奎 , 申志彬 . 定应力老化下固体发动机界面力学性能退化及寿命评估方法[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2026.33185

Abstract

Long-term storage-induced aging of the bonded interface in solid rocket motors (SRMs) is a critical factor influencing structural integrity and service reliability. Conventional high-temperature accelerated aging tests cannot realistically reproduce the stress-time coupled fields experienced under actual service conditions, leading to limitations in predicting interfacial property degradation. In this study, multi-level constant-stress aging tests were conducted under temperature conditions close to practical storage environments, and key mechanical parameters including maximum tensile strength, maximum elongation and effective fracture energy were extracted. An exponential aging kinetics model incorporating time-stress coupling was developed, wherein the Zhukov relation was introduced to quantitatively describe the dependence of degradation rate on the applied stress level. The results indicate that, under high-stress conditions, the maximum tensile strength decreases to approximately 60% of its initial value within the first 10 days of aging, while the effective fracture energy drops to nearly one-third. In contrast, the degradation under low-stress conditions is significantly slower, demonstrating pronounced stress dependence and cumulative time effects. By further integrating finite element simulations of a vertically stored SRM, the Mises stress history along the liner propellant interface was extracted and coupled with the proposed aging model. The predicted safe storage life of the bonded interface is approximately 8.4 years. The proposed method enables quantitative characterization of interfacial aging behavior and provides a reliable basis for service life assessment, offering valuable guidance for structural safety analysis and storage reliability design of SRMs.

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