小型气氢气氧火箭发动机试验系统设计研究  

Test system design for small H_2/O_2 rocket engine

作　　者：刘万龙[1] 刁鹏[1] 王翀[1] 梁国柱[1] 张学军[2] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]中国航天科技集团公司航天推进技术研究院北京航天试验技术研究所,北京100074

出　　处：《航空动力学报》2010年第7期1646-1652,共7页Journal of Aerospace Power

摘　　要：根据小型气氢气氧火箭发动机试验工况的要求设计完成1 000 N级的气氢气氧火箭发动机试验系统.介绍了供气系统的设计过程,详细讨论了气氢气氧流量与管径的选取过程,完成了比对式推力测量装置和计算机测量与控制系统的设计,并进行系统标定及冷流验证试验.该试验系统能在不同工况下开展小型火箭发动机冷热试验研究,同时实现远程计算机监控,具有较高精度.The H2/O2 rocket engine test system has been designed based on general test requirements of small 1000N H2/O2 rocket engine.The design of gas feed system was introduced.The choice of the mass velocity and pipe diameter was discussed particularly.The comparison type thrust-measuring device and the computer measurement control system have been designed.The scaling and confirmatory tests have been carried out.The test system can be used for cold flow tests and firing tests of small H2/O2 rocket engine under different work conditions,and can also be supervised and controlled remotely by computer with high accuracy.

关 键 词：氢氧火箭发动机 试验系统 比对式推力测量 测控 管路设计 

分 类 号：V434.3[航空宇航科学与技术—航空宇航推进理论与工程]