火箭发动机推力矢量测量平台的原理与结构  

Principle and Structure of the Rocket Motor Thrust Vector Measuring System

作　　者：高长银[1] 孙宝元[2] 

机构地区：[1]郑州航空工业管理学院机电工程学院,河南郑州450015 [2]大连理工大学机械工程学院,辽宁大连116024

出　　处：《压电与声光》2010年第3期480-482,共3页Piezoelectrics & Acoustooptics

基　　金：重大国防专项基金资助项目

摘　　要：介绍了一种新型压电式火箭发动机推力矢量测试方法,该测试系统的测力平台由4个3维压电石英力传感器构成,利用每个传感器获得的3个分力信号,将其带入推力矢量反求公式,即可获得各推力矢量偏心参数。通过空间加载试验可知,该压电推力矢量测量系统的推力测量误差不大于0.3%,同时能准确测量出偏移量δ和偏斜角α等参数。理论分析和空间加载试验结果均表明,该推力矢量测量平台结构合理,方法可行。A new type of piezoelectric measuring system for the motor thrust vector was introduced,which was made up of four three-component piezoelectric force transducers.Substituting the three force signals obtained from each of the piezoelectric force transducers into the thrust vector reverse formula,all the eccentricity parameters could be calculated.The dimensional loading experiment was carried out on the static calibration platform.The results showed that the measuring relative error of the thrust is less than 0.3%,and the thrust offset δ and misalignment angle α can be accurately measured.Both the theoretical analysis and dimensional loading experiment proved that the structure of the piezoelectric thrust vector measuring system is rational,and the piezoelectric thrust vector measuring system for rocket motor is feasible.

关 键 词：火箭发动机 压电石英 推力矢量 推力偏斜角 

分 类 号：TN384[电子电信—物理电子学] TH701[机械工程—仪器科学与技术]