固体火箭发动机药柱热老化结构分析方法

推进技术 ›› 2017, Vol. 38 ›› Issue (12): 2865-2871.

• 先进材料　推进剂　燃料 • 上一篇下一篇

固体火箭发动机药柱热老化结构分析方法

邓斌¹,徐明利¹,方传波¹,张维星²

火箭军装备研究院，北京 100094,火箭军装备研究院，北京 100094,火箭军装备研究院，北京 100094,西昌卫星发射中心，四川西昌 615000

发布日期:2021-08-15
作者简介:邓斌，男，博士，研究领域为固体发动机结构完整性分析与寿命预估。
基金资助:
武器装备预研项目。

A Thermo-Aging Structural Analysis Method for Solid Rocket Motor Grain

Equipment Academy of the Rocket Force，Beijing 100094，China,Equipment Academy of the Rocket Force，Beijing 100094，China,Equipment Academy of the Rocket Force，Beijing 100094，China and Xichang Satellite Launch Center，Xichang 615000，China

Published:2021-08-15

摘要/Abstract

摘要： 为研究推进剂热老化过程中的发动机结构分析方法，建立了一种含老化效应的粘弹性本构模型，基于增量有限元法对该本构进行了数值离散，导出了本构方程的增量形式，并提出了应力更新方法；基于Abaqus软件二次开发技术，编写了相应材料子程序并开展了算例分析。结果表明，老化粘弹性本构可表征分析过程的材料老化影响；本文有限元解与对应解析解吻合良好，分析方法及算法程序有效，可用于三维条件下的固体发动机药柱老化粘弹性有限元分析。

关键词: 复合固体推进剂; 热化学老化; 材料子程序; 老化结构分析

Abstract: For the purpose of studying the structural analysis method for solid rocket motor with thermo-aging evolution of propellant，a three-dimensional thermoviscoelastic constitutive model with aging evolution is built，and it is numerically studied and discretized into incremental form by integration algorithms，and the stress-updating method is presented according to incremental law. Then the Abaqus-based material subroutine and its structural analysis module are built and applied into several examples. Obtained results show that the aging-viscoelastic model can well simulate the aging-mechanical behavior of the propellant，and the results given by the model have high accuracy and agree well with the comparison ones，and the designed analysis method as well as its code are effective and would be applied to three-dimensional aging-viscoelastic finite element analysis for practical SRM grain.

Key words: Composite solid propellant；Thermochemical aging；Material subroutine；Aging-mechanical analysis

邓斌,徐明利,方传波,张维星. 固体火箭发动机药柱热老化结构分析方法[J]. 推进技术, 2017, 38(12): 2865-2871.

DENG Bin¹,XU Ming-li¹,FANG Chuan-bo¹,ZHANG Wei-xing². A Thermo-Aging Structural Analysis Method for Solid Rocket Motor Grain[J]. Journal of Propulsion Technology, 2017, 38(12): 2865-2871.

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[17] 邓斌, 申志彬, 谢燕, 等. 含损伤粘弹性本构及其在有限元分析中的实现[J]. 推进技术, 2013, 34(5): 699-705. (DENG Bin, SHEN Zhi-bin, XIE Yan, et al. Viscoelastic Constitutive Model with Damage Evolution and Its Implementation in Finite Element Analysis[J]. Journal of Propulsion Technology, 2013, 34(5): 699-705.)(编辑:史亚红)　　　　　　　　　　　　　*　收稿日期:2016-07-29；修订日期:2016-09-30。基金项目:武器装备预研项目。作者简介:邓斌,男,博士,研究领域为固体发动机结构完整性分析与寿命预估。E-mail: dbhj0@sina.cn

固体火箭发动机药柱热老化结构分析方法

A Thermo-Aging Structural Analysis Method for Solid Rocket Motor Grain

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