三组元高压推力室试验技术研究  

A Research on Test Technology of Three Component High Pressure Thrust Chamber

作　　者：王占林[1] 

机构地区：[1]北京丰云试验技术研究所

出　　处：《导弹与航天运载技术》1999年第4期14-22,共9页Missiles and Space Vehicles

摘　　要：通过对氧烃氢三组元推力室试验特点、技术关键的论述和分析，确定了正确的三组元推力室的试验启动程序，解决了高压低温条件下的系统密封、停车水击压力冲击、双燃料系统相互影响及氢组元流量测控等问题。由于这些技术关键的圆满解决，全部试验（４次）均为一次成功。本项试验的成功，验证了三组元发动机概念的可行性。By means of studying and analyzing the test characteristics and key technologies of the three component (oxygen,hydrocarbon and hydrogen) thrust chamber, these problems, such as the determination of the correct test starting procedure of the three component thrust chamber, the system sealing under the conditions of high pressure and low temperature, the impact of hydraulic shock during cutoff, the mutual influence of bifuel systems, and the measurement and control of hydrogen component flow,etc. are properly solved. As a result all the tests (four times) are successful.The successful test verifies that the concept of the three component engine is feasible.

关 键 词：三元推进剂 推力燃烧室 发动机试验 火箭 

分 类 号：V434.24[航空宇航科学与技术—航空宇航推进理论与工程]