高度补偿喷管的氢氧热试研究

王一白; 覃粒子; 刘宇; 廖云飞; 王长辉

高度补偿喷管的氢氧热试研究

北京航空航天大学宇航学院, 北京 100083

基金项目: 国家863-2高技术航天领域(2003AA722020)

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出版历程
- 收稿日期: 2006-06-21
- 修回日期: 2006-10-17
- 刊出日期: 2007-02-28

Hydrogen/oxygen hot-firing tests of altitude compensating nozzles

School of Aerospace, Beijing University of Aeronautics and Astronautics, Beijing 100083, China

摘要

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.
- 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
Abstract: 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 altitude 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 photographs 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 altitude,and about 95% at high altitude.
- aerospace propulsion system /
- aerospike nozzle /
- dual-bell nozzle /
- hot-firing test /
- altitude compensating characteristic

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参考文献(12)

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