气氢/气氧塞式喷管模型发动机实验

推进技术 ›› 2007, Vol. 28 ›› Issue (1): 73-77.

气氢/气氧塞式喷管模型发动机实验

王长辉,刘宇,王一白,廖云飞

北京航空航天大学宇航学院北京100083;北京航空航天大学宇航学院北京100084;北京航空航天大学宇航学院北京100085;北京航空航天大学宇航学院北京100086

发布日期:2021-08-15
基金资助:
国家“八六三”资助项目(863-2-1-3-1)

Tests on GH₂/GO₂ model engine with aerospike nozzle

School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100084,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100085,China;School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100086,China

Published:2021-08-15

摘要/Abstract

摘要： 以气氢/气氧为推进剂,对圆转方内喷管单元直排塞式喷管进行了热试实验研究。介绍了实验系统及实验发动机主要零部件的结构和设计参数,给出了实验参数测量结果、实验照片和数据分析。无再生冷却塞式喷管发动机采用耐烧蚀材料钨渗铜加工内喷管和燃烧室内衬,碳钢材料加工塞锥,成功进行了多次短时间热试实验。在三个压比下获得了塞式喷管性能数据,实验表明,塞式喷管具有良好的高度补偿能力和较高的效率。在CNPR=110附近,效率达到93%~95%;在CNPR=450附近,效率达到96%~98%;在CNPR=1000附近,效率达到93%~96%。预计在设计点的效率不低于98%。

关键词: 火箭发动机;塞式喷管;热试车;性能分析

Abstract: Hot-firing tests were carried out on a 1-cell GH2/GO2 linear aerospike nozzle engine with round-to-rectangle primary nozzle.Test apparatus,structures and design parameters of the main parts of the experimental engine are described.The primary nozzle and inner layer of the combustion chamber were made of ablation resistant W-Cu alloy and the aerospike ramp was made of steel.Five short duration hot firing tests on the aerospike engine without generation cooling were executed successfully.The aerospike nozzle performance was obtained under different C(NPR)(C(NPR) is the the ratio of combustion chamber pressure pc to ambient pressure pa).It is shown that good altitude compensation of thrust and high efficiencies were yielded in the tests.If C(NPR)=110,efficiency is from 93% to 95%.If C(NPR)=450,efficiency is from 96% to 98% and efficiency is from 93% to 96% if C(NPR)=1000.The promising efficiency of more than 98% at design point can be expected.

Key words: Rocket engine;Plug nozzle;Hot-firing test;Performance analysis

王长辉,刘宇,王一白,廖云飞. 气氢/气氧塞式喷管模型发动机实验[J]. 推进技术, 2007, 28(1): 73-77.