固化降温对复杂装药燃面退移过程中力学响应的影响研究  

Impact of curing cooling on mechanical response of complex grain during burning surface regression

作　　者：张艺仪 何允钦[1] 李文韬 梁国柱[1] ZHANG Yiyi;HE Yunqin;LI Wentao;LIANG Guozhu(School of Astronautics,Beihang University,Beijing 102206,China)

机构地区：[1]北京航空航天大学宇航学院,北京102206

出　　处：《推进技术》2025年第1期196-206,共11页Journal of Propulsion Technology

摘　　要：固体推进剂的力学性能是固体火箭发动机研制的关键问题之一,为了探究三维复杂装药在燃面退移过程中的力学响应以及固化降温对药柱力学性能的影响,对药柱处于固化降温阶段和燃面退移阶段的本构模型进行了耦合推导,采用实体造型法燃面退移技术耦合结构分析,充分利用商业有限元软件的参数化建模、预处理、后处理能力,得到了复杂装药在多个物理过程耦合下的力学响应。计算结果表明,某型固体火箭发动机从零应力温度(75℃)降温到20℃造成的应力应变场对燃面退移过程中药柱的力学响应影响显著,最大应力会增加93.2%,最大应变会增加83.5%。燃面退移过程中,药柱应力应变的最大值随燃烧时间呈整体下降趋势,但会受内弹道性能和结构变化共同影响出现波动。考虑固化降温的最大应力、应变曲线分别比不考虑固化降温的曲线平均高出58.8%,65.2%。总体而言,燃烧过程中药柱的力学响应会受燃面拓扑结构影响,固化降温的影响使燃面退移过程中的应力应变始终大于不考虑固化降温的情形。The mechanical performance of solid propellants plays a crucial role in the advancement of solid rocket motors.To explore the mechanical behavior of three-dimensional complex propellants during the burning surface regression process and investigate the impact of the curing cooling process on the mechanical performance of propellant grains,a comprehensive derivation of constitutive models for propellant grains in both stages was conducted.The coupling of burning surface regression with structural analysis was achieved using solid modeling methods.This approach leveraged the parametric modeling,preprocessing,and post-processing capabilities of commercial finite element software to capture the mechanical response of complex propellants under multiple coupling physical processes.The simulation results revealed that the stress and strain fields induced by the temperature decrease from the zero-stress temperature(75℃)to 20℃in a specific type of solid rocket motor significantly influenced the mechanical response of the propellant grain during the burning surface regression process.The maximum stress increased by 93.2%,and the maximum strain increased by 83.5%.Despite an overall decreasing trend,the maximum values of stress and strain in the propellant grain exhibited instability during the burning surface regression process,influenced by the combined effects of internal ballistic performance and structural changes.The maximum stress and strain curves,when considering curing cooling,were respectively 58.8%and 65.2%higher on average compared to the curves without considering curing cooling.In general,the mechanical response of the propellant during the combustion process was found to be influenced by the topological structure of the burning surface.The impact of curing cooling results in stress and strain during the burning surface regression process consistently being higher than the scenario where curing cooling is not considered.

关 键 词：固体推进剂 粘弹性力学 固化降温 燃面退移 装药 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]