瓦"状塞式喷管的实验研究  

Experimental Research on Tile-Shaped Aerospike Nozzles

作　　者：马彬[1] 刘宇[1] 戴梧叶[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100083

出　　处：《航空动力学报》2003年第2期248-252,共5页Journal of Aerospace Power

基　　金：国家863-2高技术航天领域(863-2-3-4-10);国防科学技术二等奖(2000GFJ2203)

摘　　要：为了了解塞式喷管的性能特征和更好地设计塞式喷管,本文对两种不同结构的"瓦"状塞式喷管进行了试验研究。实验采用气氧/酒精作为推进剂。实验发动机是一个四单元和一个十四单元的"瓦"状塞式喷管。文中介绍了实验系统和实验发动机的主要结构。给出了典型的试验曲线,并分析了"瓦"状塞式喷管的高度特性和底部二次流对性能的影响情况。结果显示,该种喷管具有很好的高度补偿特性,在底部加入适当的二次流能使喷管性能稍有提高。To understand the performance of aerospike nozzles and to design aerospike nozzle with higher efficientcy,the experimental research on two tileshaped aerospike nozzles has been conducted.The gaseous oxygen and alcohol were used as propellants in the experimental study.The engines researched here include a fourunit tileshaped aerospike nozzle and a fourteenunit tileshaped aerospike nozzle.The experimental setup and the geometry of the two tileshaped aerospike nozzles are presented.The typical experimental curves are showed.The altitude characteristic and the effect of base bleed on aerospike nozzles are analyzed too.The experimental results indicate that the tileshaped aerospike nozzle has good altitude compensation ability,and that the proper base bleed can promote the nozzle performance.

关 键 词：“瓦”状塞式喷管 实验研究 火箭发动机 设计 

分 类 号：V433.9[航空宇航科学与技术—航空宇航推进理论与工程] V432