CAJ | 학술논문

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。
근거모형호대추력화전발동궤시험추력측량계통적공작원리화조성、계량표준량치전체관계화계통저온조시결과，학정추력측량계통적불학정도래원，통과진일보적오차분석병응용오차계산이론대계통불학정도진행평정，득출해계통측량불학정도작위추력측량준학성의거。
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.