氢氧火箭发动机高空模拟试验推力测量装置研制  

Development of Thrust Measurement Device on Hydrogen Oxygen Rocket Engines in the High Altitude Simulation test for Orbit and Attitude Engine

作　　者：朱子环[1] 蔡睿[1] 

机构地区：[1]北京航天试验技术研究所,北京100074

出　　处：《宇航计测技术》2016年第6期50-55,共6页Journal of Astronautic Metrology and Measurement

摘　　要：为了保证氢氧火箭发动机高空环境下推力测量的准确性,针对氢氧发动机高空模拟试验的特点,结合推力测量装置的原理和实际布局的需求,开展了低温及真空环境影响下的推力测量装置结构设计研究。解决了小弹阻力的弹簧片设计技术、校准力与发动机推力轴线一致的控制技术、校准传力机构由动到静真空舱密封的实现技术以及管路约束力对推力测量影响的控制技术等难点,成功研制了一套推力测量装置,应用于某型火箭发动机试验中取得了较好的效果。To ensure accurate thrust measurement of hydrogen oxygen rocket engines under high altitude environment,according to the characteristics of high altitude simulation test on hydrogen oxygen rocket engine,the theory of thrust measurement and the actual layout requirements,the thrust measurement device design of cryogenic and vacuum environment was researched. The spring design technology of small elastic resistance was developed. A control technology to keep the calibration force and the thrust axis consistency was realized. The implementation technology on moving to static of the calibration mechanism for the seal about the vacuum cabin,and the control technology of pipeline constraint for thrust measurement influence were solved. A set of thrust measurement device was successful developed,and the application of a model of rocket engine test has achieved good results.

关 键 词：火箭发动机 高空模拟 推力测量 

分 类 号：V434[航空宇航科学与技术—航空宇航推进理论与工程]