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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。
Taking the fault phenomenon of the aircraft control board in the vibration test as the research case, the experimental modal analysis system of the control board is set up, the whole process of measuring the frequency response function of the board is discussed, the modal parameters of the aircraft control board are extracted based on the PolyMAX algorithm, The dynamic characteristics of the control board are studied. The dynamic response of the control board under the action of the load is analyzed by modal superposition technique. The mechanism of the typical vibration fault in the middle of the control board is analyzed. The adaptability puts forward the improvement measure.