高度补偿喷管的氢氧热试研究  

Hydrogen/oxygen hot-firing tests of altitude compensating nozzles

作　　者：王一白[1] 覃粒子[1] 刘宇[1] 廖云飞[1] 王长辉[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》2007年第2期316-322,共7页Journal of Aerospace Power

基　　金：国家863-2高技术航天领域(2003AA722020)

摘　　要：采用气氧作氧化剂、气氢作燃料,对具有高度补偿特性的塞式喷管和双钟型喷管进行了点火热试.介绍了气氢/气氧试验系统,以及试验喷管的结构形式、设计参数和装配照片,喷管试验件采用耐烧蚀的钨渗铜材料加工,成功进行了多次短时间点火热试.给出了试验测量参数曲线、点火热试照片和数据结果,获得了不同高度下塞式喷管和双钟型喷管的热试性能数据,和当量钟型喷管相比两者都具有较好的高度补偿特性.以推力系数效率为例,塞式喷管在低空压强比下达到92%-95%,双钟型喷管低空下为96%-98%,高空下则都在95%左右.By employing the gaseous oxygen as oxidizer and gaseous hydrogen as fuel, hot-firing tests were performed for aerospike nozzle and dual-bell nozzle test engines with al- titude compensating features. The gaseous hydrogen/oxygen experimental system, the test nozzles＇ configuration, design parameters and assembly graphics were described. Made of the ablation-resistant tungsten-copper alloy, the test components of nozzles have successfully passed several short-period hot-firing tests. The measured parameter curves, test photo- graphs and results are obtained, thus obtaining the performance data of aerospike nozzle and dual-bell nozzle under different altitudes, both of which have good altitude compensation characteristic as compared with the conventional bell nozzle. For example, the thrust coefficient efficiency of aerospike nozzle is 92%-95% and dual-bell nozzle is 96 %-98% at low alti- tude, and about 95% at high altitude.

关 键 词：航空 航天推进系统 塞式喷管 双钟型喷管 点火热试 高度补偿特性 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]