收敛-扩张喷管中运用次流推力矢量控制技术的计算研究  

Computational investigation of secondary flow thrust vector control technology used in a convergent-divergent nozzle

作　　者：邓远灏[1] 钟梓鹏[1] 宋文艳[1] 

机构地区：[1]西北工业大学动力与能源学院,西安710072

出　　处：《固体火箭技术》2005年第1期29-32,共4页Journal of Solid Rocket Technology

摘　　要：采用二阶TVD格式的有限体积法耦合RNGκ ε湍流模型和非平衡壁面函数求解二维守恒型雷诺平均N S方程,数值模拟了运用次流推力矢量控制技术的二维收敛 扩张喷管中的流动现象。计算结果表明,随着喷管压比的增加,次流喷射所产生的激波向扩张段下游移动,且喷管矢量角不断减小到一固定值;次流压比的增加将导致激波向扩张段上游移动,且喷管矢量角不断增加;次流压比对激波和矢量角的影响比喷管压比更强。The finite volume method with second-order TVD scheme was used to solve the 2D Reynolds average N-S equation by coupling RNS k-Ε turbulence model and non-equilibrium wall function. Flow phenomena in 2D convergent-divergent nozzle using secondary flow thrust vector control technology were numerically simulated. The calculation results show that the shock wave generated by secondary flow jet move toward downstream divergent section and the thrust vector angle gradually decreases to a preset value as the nozzle pressure ratio increases. Along with the increase of the secondary flow pressure ratio, the shock move toward upstream divergent section and the thrust vector angle gradually increases; the effect of the secondary flow pressure ratio on the shock wave and the thrust vector angle is stronger than the effect of nozzle pressure ratio.

关 键 词：推力矢量控制技术 喷管 计算研究 收敛 雷诺平均N-S方程 κ-ε湍流模型 有限体积法 TVD格式 壁面函数 流动现象 数值模拟 计算结果 扩张段 压比 守恒型 RNG 二维 波向 

分 类 号：V23[航空宇航科学与技术—航空宇航推进理论与工程] V435.23