固体火箭发动机点火装置方案设计通用算法模块研究

Study on the General Algorithm Module for Solid Rocket Motor Ignition Device Scheme Design

为解决现有点火装置设计“系统研究少、设计经验性强、方案通用性差”的问题,对不同类型点火装置的方案设计过程进行了系统性分析,提出了点火装置方案设计的通用设计方法及流程,在此基础上采用面向对象技术开发相应的通用算法模块,包含所需要的数据字典以及专业算法的实现。完成5种类型点火装置方案设计全过程,获得方案设计的结构参数与性能参数,同时基于Creo实现了参数化三维模装设计快速建模。该通用算法模块不仅可以独立运行,也可集成至有关的固体火箭发动机总体方案设计系统软件中。利用所开发的算法模块对FG-02固体火箭发动机点火装置以及常见的管式点火装置方案进行案例设计,结果表明所建立的点火装置方案设计流程及开发的通用算法模块具有较好的适应性,提高了设计效率和经济性,可为点火装置的方案论证和初步工程设计提供支持。

The existing research on ignition device designs face problems of insufficient systematic research,strong reliance on design experience,and limited versatility.To solve these problems,a systematic analysis of design processes for various types of ignition device was presented.A more general design methodology and process for ignition device solutions was proposed.On this basis,the object-oriented technology was used to develop the corresponding general algorithm module,containing the essential data dictionaries and the implementation of specialized algorithms.The entire process for the scheme design of five types of ignition devices was completed,obtaining structural and performance parameters for the design.Simultaneously,a rapid parametric three-dimensional modeling based on Creo was realized.The algorithm module is not only capable of independent operation but can also be integrated into the relevant software for overall solid rocket motor scheme design systems.Case designs for the FG-02 solid rocket motor ignition device and common tubular ignition device were conducted using the developed algorithm module.The designed results indicate that the established ignition device scheme design process and developed general algorithm module exhibit ideal adaptability.This improvement enhances design efficiency and cost-effectiveness,providing support for ignition device scheme demonstration and preliminary engineering design.