气体二次喷射推力向量控制数值仿真

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. 

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

The complex inner flow-field of secondary gas injection for solid rock et motor were numerically investigated using three-dimensional average Favre N -S equations and the k-ε turbulent models. Three-order spatial scheme an d implicit point Jacobi algorithm were used to solve these equations. The basal explore of the integrant scheme for secondary gas injection vector nozzle was do ne by dint of the numerical simulation technology. The influences of the flow-f ield of secondary gas injection and the side force by different injection parame ters were studied and investigated. The results show that the position of the in jection hole, the injection total temperature and total pressure that affected t he side force of the nozzle are coupling. Moderate position of the injection ho le, hot gas and biggish injection total pressure increases the side force and ve ctor angle of the nozzle effectively. The hot gas injection system has higher ef ficiency. The side force increases linearly with the augmentation of the seconda ry injection total pressure.