基于推力矢量控制的固体火箭发动机气体二次喷射研究  

Investigation on secondary gas injection for solid rocket motor based on thrust vector control

作　　者：吴雄[1] 张为华 

机构地区：[1]国防科技大学航天与材料工程学院,长沙410073

出　　处：《固体火箭技术》2006年第2期103-106,109,共5页Journal of Solid Rocket Technology

摘　　要：采用二维雷诺平均方程和κ-ε湍流模型,对固体火箭发动机气体二次喷射复杂干扰内流场进行了数值模拟。借助数值模拟技术,对气体二次喷射推力矢量喷管的部分方案进行了初步探索,研究了不同喷射参数对气体二次喷射流场特征及侧向控制力的影响,并分析了其原因。结果表明,二次喷射气体的喷射孔位置、喷射角及喷射总压等因素对侧向力的影响相互耦合,适中的喷射孔位置、逆流喷射角及较大的喷射总压都能有效增加侧向力及矢量角。The complex inner flow-field of secondary gas injection for SRM was numerically simulated by using two-dimensional average Reynolds equations and the K-8 turbulent model. Partial scheme for secondary injection of thrust vector nozzle was preliminarily explored by means of numerical simulation technology. The influences of different injection parameters on flow-field of secondary gas injection and the side force were analyzed and investigated. The results show that the effects of the position of injection hole ,the injection angle and the injection total pressure on the side force were coupled with each other, and moderate position of injection hole, countercurrent injection angle and bigger injection total pressure can make the side force and vector angle of the nozzle increase effectively.

关 键 词：固体推进剂火箭发动机 气体二次喷射 推力矢量控制 数值模拟 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]