摘要
根据某型号大推力火箭发动机试验推力测量系统的工作原理和组成、计量标准量值传递关系和系统低温调试结果,确定推力测量系统的不确定度来源,通过进一步的误差分析并应用误差计算理论对系统不确定度进行评定,得出该系统测量不确定度作为推力测量准确性依据。
The uncertainty source of the thrust measure system was determined on the basis of the working principle, composition, metrological standard value transitive relation and low temperature debugging result of thrust measurement system for a large thrust rocket engine. The test uncertainty of the thrust measurement system was assessed by error analysis and theory of error calculation. The test uncertainty of the system was obtained, which is taken as an evidence for accuracy of thrust measure- ment. The method can be taken as a reference for thrust measurement assessment for other types of rocket engines.
出处
《火箭推进》
CAS
2012年第5期81-85,共5页
Journal of Rocket Propulsion
基金
国家863项目(2008AA702303)
关键词
火箭发动机
推力测量
测量不确定度
rocket engine
thrust measurement
measurement uncertainty
