基于Pro/E的参数化驱动固体发动机模装设计

Parameter-driven assembly model design ofsolid rocket motors based on Pro/E

为实现参数化驱动的固体火箭发动机结构设计、零件装配及其与平行层燃面退移的一体化集成,以Pro/E族表技术为核心,利用WinForm框架和XML等技术,提出了实现固体火箭发动机结构参数化模装设计和整机自动化装配的技术途径,实现了发动机各零部件三维模型的参数化驱动及发动机整机的自动化装配,实现了复杂三维药柱退移过程中的拓扑结构变化。该研究开发完成固体火箭发动机结构参数化模装设计软件系统,系统中包含29个发动机零件,通过灵活设定结构参数,可自动化构建多达720种不同结构形式的发动机结构实体模型,实现平行层燃面退移,得到发动机工作过程中的动态结构质量特性,同时计算出发动机的内弹道性能,并且具有可扩展性。该技术能够为进一步研究固体火箭发动机的设计、仿真、优化的一体化系统奠定基础。

In order to implement parameter-driven structural design,parts assembly and parallel-layer burning surface regression of grains for solid rocket motors(SRMs),a method for the parametric design of SRM structures and the automatic assembly of the entire SRM was proposed based on Pro/E family tables,WinForm Frameworks,XML etc.The method can achieve parametric drive of part models,automatic assembly of the whole SRM,as well as achieving topological structure change in the process of complex three-dimensional burning surfaces regression.Moreover,a parametric assembly model design software system was developed.Built with 29 part models,the system can construct models for SRMs of 720 different structures automatically,based on flexible structural parameters,so as to achieve parallel-layer burning surface regression,as well as acquire the structural mass characteristics of the SRMs during operation,and calculate the interior ballistic performance.With great scalability,the system contributes to the study of integrated system for SRM design,simulation and optimization.