固体火箭发动机装药设计的一种燃面推移方法研究

Research on a burning surface transition method ofsolid rocket motor grain design

固体火箭发动机装药设计是固体火箭发动机设计的核心内容之一,找到一种针对复杂三维装药的通用燃面推移计算方法具有重要的工程应用价值。研究使用UG NX二次开发平台工具SNAP和Block UIStyler编写装药设计建模程序,并采用射线摇摆旋转相交法(IRSR)进行装药表面离散;然后,依照几何燃烧定律用C++编写与一维内弹道耦合的装药燃面推移计算程序,得到装药在整个燃烧过程中的内流场参数变化情况。该计算程序以链表为基础结构交织成网状数据结构来管理装药燃面的离散点信息,并配以相应的面积计算方法,在指定步长的迭代计算过程中,可判定识别并处理点奇异、点过密或者过稀、面交汇的情况,避免计算失真。结果表明,此基于燃面推移的设计方法可准确捕捉装药燃烧过程中的复杂拓扑结构变化,与实际情况吻合较好,适用于非槽平端单通道装药或者实心装药。

Solid rocket motor grain design was one of the cores of solid rocket motor design.To find a universal burning surface transition calculation method for complex three-dimensional grains of arbitrary shapes had important engineering application value.This paper used the UG NX secondary development platform tool SNAP and Block UIStyler to write the dialog program to design and model grain,and used the method for intersection by ray swing and rotating(IRSR)to discretize the grain surfaces.Then used C++to write a calculation program for the grain combustion surfaces transition in accordance with the geometrical combustion law and coupled with the one-dimensional internal trajectory to obtain the internal flow field parameters during the whole combustion process.The calculation program manages the discrete point information of the grain to interweave into a network data structure based on the linked list as the basic,and took the corresponding area calculation.And during this calculation process which the elapsed time step was specified in,the program could identify and handle where the points were singular,where the points were too dense or too sparse,and where the faces meet to avoid calculation distortion.The results show that this method base on combustion surface transition can accurately capture the complex topology changes during the combustion process.And it is in good agreement with the actual situation and is suitable for non-slotted flat-end single-channel grain or solid grain.