固体火箭发动机多物理场仿真参数化实体建模方法研究

Jiaren Ren, Futing Bao, Ran Wei, Lin Dai, Jiandong Zhang
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引用次数: 1

摘要

固体火箭发动机(SRM)设计工程师迫切需要一种能够高效设计SRM并实现参数在限定范围内调整的方法,以大致评估SRM的质量特性,并快速获得用于燃烧回归情况下工作过程模拟的多物理场。基于Creo平台,分别利用自顶向下建模的概念和特征建模的方法,提出了SRM参数化设计和燃烧回归跟踪的标准流程。另外,Creo的二次开发将参数修改、模型生成、文件导出等功能封装在程序中,避免了手工操作的复杂性和繁琐性。
本文章由计算机程序翻译,如有差异,请以英文原文为准。
Research on The Parametric Solid Modeling Method of Solid Rocket Motor for Multiphysics Simulation
Solid Rocket Motor (SRM) design engineers urge for a method that can design SRM with high efficiency and realize the adjustment of the parameters within limits, aiming at roughly evaluating the quality characteristics of the SRM and rapidly getting the multi-physics fields used for working process simulation under the circumstances of the burning regression. Based on the Creo platform, this paper proposed a standard process for parametric design of SRM and tracking the burning regression by utilizing the concept of Top-down modeling and the method of feature modeling respectively. Additionally, the function of modifying parameters, regenerating models, and exporting files was encapsulated in programs by the secondary development of Creo, avoiding the complexity and tediousness of manual operation.
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