固体火箭发动机燃烧室喷管一体化网格生成

GRIDS METHOD FOR CHAMBER NOZZLE INTEGRATED DESIGN IN SOLID ROCKET ENGINE

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。

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.