Abstract: Theoretical model to evaluate rocket nozzle’s misalignment thrust was set up from non symmetric fluid laws from subsonic, transonic to supersonic flow in nozzle. The equations were solved by high accuracy numerical scheme as the implicit finite volume TVD. The software Nvc integrated by above functions was formed which includes all process such as nozzle grid generation, numerical calculation and misalignment thrust analysis. The application software owns friendly interface based on WINDOWS, is rather convenient which free designers from complicate calculation and raises design efficiency greatly. By comparison with many experiment data, corresponding calculations from Nvc can satisfy the demand of rocket motor’s design, which may reduce experiment quantities or save cost.

Key words: Rocket engine nozzle;Rocket thrust;Thrust misalignment angle;Numerical simulation

摘要： 利用火箭喷管从亚声速、跨声速到超声速的非对称流动数学模型建立了计算喷管推力偏心的理论模型 ,并采用高精度有限体积TVD格式求解数值方程 ,可以对火箭发动机喷管的推力偏心特性进行评估与设计 ,并集成为Nvc软件。该软件完成了从喷管网格生成、数值计算到推力偏心分析全过程 ,界面友好 ,使用方便 ,大大提高了设计效率。通过大量的计算与试验结果的比较 ,计算结果可以满足工程需要 ,减少试验次数 ,节约成本 ,具有广泛的用途

关键词: 火箭发动机喷管;火箭推力;推力偏心角;数值仿真