固体火箭发动机装药结构完整性研究进展

Recent Progress upon Structural Integrity Analysis of Solid Rocket Motor Grain

针对固体火箭发动机装药结构完整性的计算与评估问题,总结与分析中外复合固体推进剂本构模型、结构完整性解析模型、结构完整性数值仿真。研究表明:首先,复合固体推进剂具有力学性能复杂的特点,分析影响复合固体推进剂力学性能的主要因素,为建立合适的本构模型提供方向;其次,复合固体推进剂不可压缩、大变形、黏弹性性能,对装药结构完整性计算精度具有重要影响,分析提高求解精度的处理方法,为结构完整性精确计算与评估提供基础;最后,总结结构完整性分析的解析模型,为验证数值仿真提供了解析解。通过总结与分析,为装药结构完整性分析提供方向,为进一步优化装药设计提供理论基础。

In order to perform the evaluation of structural integrity analysis for solid rocket motor,a large amount of studies on the composite propellant constitutive model,analysis model,and finite element model were concluded and analyzed.The important influences on the mechanical properties of composite solid propellant were discussed,which,due to the complex and various mechanical properties,provided a direction to develop the reasonable constitutive model of propellant.Secondly,as large deformation,viscoelastic,and incompressible of composite solid propellant could increase the difficulty of structural integrity analysis,the relevant approaches were concluded to treat those problems in order to improve the accuracy of evaluation of structural integrity analysis.Thirdly,the analytical model was summarized for structural integrity analysis of solid rocket motor grain,which provided analytical solution for veri-fying numerical simulation.The results can be taken as the reference of structural integrity analysis of solid rocket motor grain.Furthermore,the results are helpful to optimize the grain design.