中文摘要：

以固体火箭发动机喷管燃气舵绕流流场为研究对象,采用数值模拟技术,通过离散求解流动方程及相关湍流模型方程,对包含舵基、舵片和发动机喷管在内的复杂流场进行了变参数分析,获得并揭示了舵基、舵片附近的流动现象和流动特点。验证了所引入的数值模拟方法的有效性,分析结果对舵基、舵片的结构安装以及控制机构的设计具有借鉴意义。

英文摘要：

The flow around a solid rocket engine jet vane with a nozzle was numerically simulated. The flow controlling equations coupled with relevant turbulence model equations are discreted numerically by using appropriate computational techniques,and a parametric analysis is carried on for the complicated flows over the vane base,vane patch,and engine shell. Especially,the flow phenomena and properties near the the vane base and vane patch are obtained and discussed. Results show that the numerical simulation methods introduced and employed here are effective and valid,and it is useful for the designs and installations of the vane base and vase patch and related control equipments.