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.
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)
