气体二次喷射推力矢量控制系统参数优化与试验研究  

Investigation on Secondary Gas Injection for Solid Rocket Motor Based on DOE

作　　者：张泽远[1,2] 邢国强 ZHANG Zeyuan;XING Guoqiang(China Airborne Missile Academy,Henan Luoyang 471009,China;Aviation Key Laboratory of Science and Technology on Airborne Guided Weapons,Henan Luoyang 471009,China)

机构地区：[1]中国空空导弹研究院,河南洛阳471009 [2]航空制导武器航空科技重点实验室,河南洛阳471009

出　　处：《弹箭与制导学报》2020年第1期102-104,109,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金(2014ZC12005)资助。

摘　　要：采用优化设计结合数值模拟的方法对固体火箭发动机气体二次喷射复杂干扰喷管内流场进行了数值计算,研究了二次喷射流与主流相互耦合作用机制以及二次喷射推力矢量流动机理。通过对影响侧向控制力的喷射流物理参数、喷射孔位置、角度以及喷管几何参数的主效应和交互作用分析,找到了主因素及交互作用的影响规律。结合总结出的最大矢量角参数组合,开展优化方案的试验验证。The complex inner flow-field of secondary gas injection for solid rocket motor was numerically investigated by optimization design.The influences of different injection parameters on flow-field of secondary gas injection and the side force were analyzed and investigated.It gained the structures of shockwave series of secondary gas injection vector nozzle and complex main/secondary flow image by numerical simulation.By analyzing the main and alternation factors,the influence rule of the position of injection hole,the injection angle,the injection total pressure and total temperature on flow-field of secondary gas has been summarized.The optimization parameters are validated by test.

关 键 词：固体火箭发动机 气体二次喷射 推力矢量 优化设计 

分 类 号：TJ760.33[兵器科学与技术—武器系统与运用工程] V231.3[航空宇航科学与技术—航空宇航推进理论与工程]