气体二次喷射推力向量控制数值仿真  

Numerical simulation of secondary gas injecting for thrust-vector-control

作　　者：吴雄 张为华 王中伟 

机构地区：[1]国防科学与技术大学航天与材料工程学院,长沙410073

出　　处：《北京航空航天大学学报》2007年第1期42-45,共4页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家863基金资助项目(2005AA765030)

摘　　要：采用基于Favre平均的三维N-S方程和k-ε湍流模型对固体火箭发动机气体二次喷射推力向量喷管复杂干扰内流场进行数值模拟;采用三阶精度空间差分格式和隐式Jacobi时间点迭代方法进行求解;借助数值模拟技术对气体二次喷射推力向量喷管方案进行了初步探索,研究了不同喷射条件对气体二次喷射流场特征及侧向控制力的影响作用;研究表明,二次喷射气体喷射孔位置、总温及总压等因素对侧向力影响具有耦合作用,合适的喷射孔位置和高温燃气以及较大喷射总压都能有效增加侧向力及向量角;燃气二次喷射系统具有较高的效率;侧向力随二次喷射流总压增加而线性增大.The complex inner flow-field of secondary gas injection for solid rocket motor were numerically investigated using three-dimensional average Favre N-S equations and the k-ε turbulent models. Three-order spatial scheme and implicit point Jacobi algorithm were used to solve these equations. The basal explore of the integrant scheme for secondary gas injection vector nozzle was done by dint of the numerical simulation technology. The influences of the flow-field of secondary gas injection and the side force by different injection parameters were studied and investigated. The results show that the position of the injection hole, the injection total temperature and total pressure that affected the side force of the nozzle are coupling. Moderate position of the injection hole, hot gas and biggish injection total pressure increases the side force and vector angle of the nozzle effectively. The hot gas injection system has higher efficiency. The side force increases linearly with the augmentation of the secondary injection total pressure.

关 键 词：气体二次喷射 推力向量控制 数值模拟 

分 类 号：V231.3[航空宇航科学与技术—航空宇航推进理论与工程]