考虑燃面退移的固体火箭发动机仿真模型生成技术

Simulation Model Generation Technology of Solid Rocket Motor Considering Burning Surface Regression

装药、结构、流场域、声场域等多物理场模型是用于固体火箭发动机设计的重要仿真模型。构建大量不同燃面退移距离下的多物理场模型存在人工操作易错、效率低的问题。为快速批量化地获得不同燃面退移距离下固体火箭发动机的多物理场文件,基于Creo软件平台,采用自上而下的建模理念,对固体火箭发动机参数化建模,利用装药的特征造型方法,对燃面退移进行追踪;并对Creo平台进行二次开发,实现用户输入命令即可实现仿真模型的自动再生、导出等功能。利用所提出的仿真模型生成标准流程以及辅助设计应用程序,为火箭发动机设计人员提供了一种高效的建模思路,简化了烦琐的重复性工作,降低了人工操作错误的可能。

The grain,the structure,the flow field and the acoustic field are critical to solid rocket motor(SRM)design,where engineers are urging for a typical SRM with high efficiency and could realize the adjustment of the parameters within limits.Aiming at evaluating the quality characteristics of the SRM roughly and getting the multiphysics fields used for process simulation rapidly under the burning regression,utilising the Creo platform,this paper proposed a standard process for the parametric design of a solid rocket motor and tracking the burning regression,applying the concept of top-down modelling and the method of feature modelling respectively.Additionally,this paper has conducted the secondary development of Creo,the function of modifying parameters,regenerating models and exporting files was encapsulated in programs,avoiding the complexity and misoperation of manual operation.