飞行器控制板动力学特性试验分析  

Experimental modal analysis on dynamic characteristics of aircraft control circuit board

作　　者：周林[1] 方勃[1] 周凌[2] 王朔[1] 范欣欣[1] 张业伟[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学部(院),沈阳110136 [2]中国科学院长春光学精密机械与物理研究所无人飞行器部,长春130033

出　　处：《沈阳航空航天大学学报》2017年第3期37-42,共6页Journal of Shenyang Aerospace University

基　　金：国家自然科学基金(项目编号:11402151);辽宁省自然科学基金(项目编号:2015020106;2013024005)

摘　　要：以飞行器控制板在振动试验中的故障现象为研究案例,搭建了控制板的试验模态分析系统,论述了测量该板频响函数的全过程,基于PolyMAX算法提取了飞行器控制板模态参数,研究了控制板的动态特性;采用模态振型叠加技术,定性控制板在载荷作用下的动态响应,分析了控制板中间位置产生典型振动故障的机理,并且对提高飞行器控制板在振动环境下的适应性提出了改进措施。An experimental modal analysis system of aircraft control circuit board was built based on its fail- ures in a vibration test. The FRF were identified by the PolyMAX method. The dynamic characteristics of the control board were studied. The modal superposition technique was used to determine the dynamic response of the control board and analyze the mechanism of typical vibration failure in the middle position of the con- trol board. Finally, the measures were proposed to improve the vibration resistance of the aircraft control board.

关 键 词：飞行器控制板 模态分析 Poly MAX MAC 

分 类 号：V414.33[航空宇航科学与技术—航空宇航推进理论与工程] V416.5