塞式喷管单元发动机实验与数值模拟研究  

EXPERIMENTAL AND NUMERICAL STUDIES ON A UNIT OF AEROSPIKE NOZZLE

作　　者：刘宇[1] 戴梧叶[1] 汤海滨[1] 程显辰[1] 马彬[1] 王一白[1] 覃粒子[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《宇航学报》2001年第4期27-33,共7页Journal of Astronautics

基　　金：国家 8 63-2高技术航天领域 [863-2 -3-4 -1 0 ];国家自然科学基金资助项目 [597860 0 1 ]

摘　　要：简要介绍了固体推进剂模拟塞式喷管单元发动机实验系统 ,给出了实验塞式喷管型面设计方法和特征线法在塞式喷管流场计算中的应用。总结了实验研究结果 ,并同数值模拟计算结果进行了比较 ,主要结果包括燃烧室压力、底部气锥流量、内膨胀比、侧喷管倾角、底部压缩角等对塞式喷管性能的影响 ,并得出了塞式喷管单元发动机推力方向与其轴线方向夹角的高度特性。It gives a brief introduction to the experimental system for the solid propellant simulated tests on a unit aerospike nozzle.The design method of the experimental aerospike nozzle contour and the applications of the Method Of Characteristics (MOC) to the flow flied of the aerospike nozzle are presented.The summarized experimental results are compared to the numerical simulated results consisting of the effects to the aerospike nozzle performances by the different combustor pressure,mass flow rate at base,internal expansion ratio,angle between side nozzle axis and the axis of the spike and compressing angle of the base.The altitude property of the angle between the thrust vector of the unit and the axis of the spike is given too.

关 键 词：火箭发动机 实验 数值模拟 塞式喷管 固体推进剂 

分 类 号：V435.6[航空宇航科学与技术—航空宇航推进理论与工程]