塞式喷管侧向喷流仿真研究  

Lateral jet simulation study of annular throat plug nozzle

作　　者：柳长安[1] 李光熙[1] 吕奇伟[1] 

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2013年第2期59-62,73,共5页Journal of Rocket Propulsion

基　　金：中国航天科技集团公司支撑项目(2009JY01)

摘　　要：随着快速、准确等控制要求的提高,越来越多的飞行器采用了直接侧向力控制技术,这对飞行器本体及喷流装置均提出了更高要求,是先进飞行器气动设计中的关键技术之一。参考美国NCADE方案中的塞式喷管控制发动机结构进行了侧向喷流干扰流场的数值仿真研究,并与常规拉瓦尔喷管进行了对比,分析了两种喷管干扰流场结构及性能的异同,为相关研究提供借鉴。With the development of quick and accurate control technology, the lateral jet control technology is adopted in more and more missiles and other air vehicles to meet this trend, which has become a key technology in the vehicle design. This presents more strict requirements to the vehicles and the jet devices also. According to the plug control engine used in American＇s NCADE design, the numerical simulation was implemented for the flow field of the lateral jet of the plug nozzle, and the flow field was compared with the flow field of the conventional Laval nozzle. The difference of the flow field structures of the two nozzles are analyzed in this paper. The analysis result provides some help for the related researches.

关 键 词：塞式喷管 拉瓦尔喷管 侧向喷流 N-S方程 

分 类 号：V434.34[航空宇航科学与技术—航空宇航推进理论与工程]