某姿轨控动力装置内流场研究  

Investigation on Internal Flow Field of Attitude-orbit Controlled Impetus Motor

作　　者：张泽远[1,2] 郭颜红[1] 丁永强[1] 

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》2014年第6期103-106,118,共5页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金项目(20110112005)资助

摘　　要：装备姿轨控发动机的空空导弹能大幅提高对目标拦截的范围,实现提前拦截、防区外拦截。文中基于多喷管单室固体发动机方案,研究内弹道工作特性,采用数值模拟的方法研究内流参数分布规律,通过详细内流场仿真,发现动力装置均能正常工作,内部流场通畅,气动参数基本呈均匀分布,但多喷管之间存在一定程度的相互影响和干扰。通过试验验证该动力装置的工作特性。The airborne missile with attitude-orbit controlled impetus motor can head off the target in farther area and earlier occasion,even out of defense region. The project of solid propellant rocket engine with multi-nozzle was implemented,and the paper put importance on the investigation of interior ballistics characteristic. By analyzing the influencing factors,the parameter distributing law on internal flow field was analyzed and summarized. The result shows that the impetus motor can work normally and the internal flow field is symmetrical,but there is some interference in these nozzles. The working performance of impetus motor is validated in examination.

关 键 词：姿轨控 内弹道 数值模拟 性能试验 

分 类 号：V435[航空宇航科学与技术—航空宇航推进理论与工程]