固体火箭发动机燃烧室喷管一体化网格生成

推进技术 ›› 1999, Vol. 20 ›› Issue (4): 29-31.

固体火箭发动机燃烧室喷管一体化网格生成

张正科,刘宇

北京航空航天大学宇航学院;北京航空航天大学宇航学院

发布日期:2021-08-15
基金资助:
航空工业总公司高校自选课题

GRIDS METHOD FOR CHAMBER NOZZLE INTEGRATED DESIGN IN SOLID ROCKET ENGINE

School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing,100083;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing,100083

Published:2021-08-15

摘要/Abstract

摘要： 给出固体火箭发动机燃烧室喷管一体化网格策略，用二维方法生成平面网格经旋转或堆砌形成空间网格。对网格正交性受几何域形状限制的情况进行了讨论。给出了一种燃烧室－喷管外形的网格结果。

关键词: 固体火箭发动机;燃烧室;火箭发动机喷管;一体化设计;格网法

Abstract: A grid strategy for the complete chamber nozzle configuration of solid rocket motor was presented.Two dimensional method was used to generate grid on flat plane The plane was rotated or stacked to form volume grid. The dependence of the realization of grid orthogonality on configuration geometry was discussed. The grid generation result for a chamber nozzle configuration was given.

Key words: Solid propellant rocket engine;Combustion chamber;Rocket engine nozzle;Integrated design;Grids method

张正科,刘宇. 固体火箭发动机燃烧室喷管一体化网格生成[J]. 推进技术, 1999, 20(4): 29-31.