固体火箭发动机药柱抗蠕变增强结构优化设计  

Optimization design of anti-creep reinforcement structure for solid rocket motor propellant grain

作　　者：刘孟洋 高经纬 严波 张晓飞 LIU Mengyang;GAO Jingwei;YAN Bo;ZHANG Xiaofei(College of Aerospace Science and Engineering,National University of Defense Technology,Changsha 410073,China;College of Electrical and Information Engineering,Hunan University,Changsha 410082,China)

机构地区：[1]国防科技大学空天科学学院,长沙410073 [2]湖南大学电气与信息工程学院,长沙410082

出　　处：《机械强度》2025年第3期121-128,共8页Journal of Mechanical Strength

基　　金：国家自然科学基金项目(52375278)。

摘　　要：针对长期立贮固体火箭发动机(Solid Rocket Motor,SRM)产生的蠕变问题,提出一种在不改变药柱基本结构的前提下,通过在药柱基质中植入特定形状的功能性可燃芯模(即“增强结构”)抑制药柱蠕变。首先,通过三维数值模拟方法分析固化降温和立式自重耦合作用下药柱蠕变分布规律。随后,采用变密度法中的固体各向同性材料惩罚模型(Solid Isotropic Material with Penalization,SIMP)对增强结构进行拓扑优化设计,确定植入增强结构的基本几何构型。最后,对比分析拓扑优化后增强结构的抗蠕变作用,得到最终优化设计结果。结果表明,在特定工况下,与无增强结构相比,含增强结构的固体火箭发动机药柱总变形、应力、应变下降明显,能有效抑制药柱蠕变。To address the creep issue that arises during the long-term vertical storage of solid rocket motor(SRM),a method was proposed that involved embedding a specially shaped functional combustible core model(reinforcement structure)into the propellant grain matrix without altering the basic structure of the grain.Initially,the distribution patterns of creep in the propellant grain under the coupled effect of solidification cooling and vertical self-weight were analyzed by using threedimensional numerical simulation methods.Subsequently,the reinforcement structure was designed by using the solid isotropic material with penalization(SIMP)method for topology optimization,determining the geometric configuration of the embedded reinforcement structure.Finally,the final optimized design results were determined through comparative analysis of the anti-creep effect of the topology-optimized reinforcement structure.The research results demonstrate that the deformation stress and strain of the solid rocket motor propellant grain with the reinforcement structure are significantly reduced compared to those without the reinforcement structure,effectively suppressing the creep of the grain.

关 键 词：固体火箭发动机 蠕变 拓扑优化 有限元方法 

分 类 号：V512[航空宇航科学与技术—航空宇航推进理论与工程]