导弹挂飞应力天平测力系统设计  

Design and Development of System for the Measurement of Missile's Embarkation Flight Loads Based on Strain-gauge Balance

作　　者：胡凯征[1] 刘献伟[1] 黄帅军[1] 陈鑫[1] 姚利兵[1] 

机构地区：[1]中国空空导弹研究院,洛阳471009

出　　处：《科学技术与工程》2008年第20期5716-5719,5726,共5页Science Technology and Engineering

摘　　要：依据应变天平特点,从导弹挂飞特性出发,设计导弹挂飞测力系统并初步校验其准确性。试验数据证明系统准确、可靠,为实际挂飞状态下测量导弹载荷及舵面载荷的提供了物质条件。A system for the measurement of missile＇s embarkation flight loads based on strain-gauge balance is designed. The test result shows that the system scheme is right, the supporting stiffness is good and the measure precision is high. This system present a new method to measure embarkation flight loads and moment of flaps in real condition.

关 键 词：应变天平 测力 导弹 

分 类 号：V217.22[航空宇航科学与技术—航空宇航推进理论与工程]