基于分布式激励的多激励源联合控制试验方法  

Multi-excitation source united controlling test method based on distributed actuation

作　　者：姚军[1] 吴雁飞[1] 姚义红[1] 

机构地区：[1]北京航空航天大学可靠性与系统工程学院,北京100191

出　　处：《北京航空航天大学学报》2012年第4期529-534,共6页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家863计划资助项目(2007AA04Z413)

摘　　要：针对高速飞行器运行过程中经受的振动环境复杂而现有的振动试验技术无法对其进行充分的振动耐久性考核的问题,提出了一种压电元件、振动台、激振器联合控制的振动试验技术.该方法将激振器、振动台安放在结构刚性较大的骨架位置以提供集中力,压电元件则分布黏贴于结构刚性较小的柔性部位以提供分布式激振力.分析了高速飞行器运行过程中的振动环境特点以及这些环境对高速飞行器产生失效的影响,并基于对压电元件材料以及激励特性的研究,分析了压电元件作为耐久性振动试验分布式激励源的可行性,最后组建完成一套集成压电元件、振动台、激振器三种激励源的试验演示系统并开展试验研究.试验结果显示,应用该方法可控制结构柔性部位上一点的振动量级达到20.8 g,表明了该技术的科学性以及巨大的工程应用潜力.In view of the questions of high-speed aircraft withstanding complicated vibration environment,their vibration durability could not being plenary examined by existing vibration test technology,a vibration test technique integrating piezoelectric element,vibration table,exciter was proposed,the vibration table and exciter placed on the large-stiffness part of the structure to provide concentration force and piezoelectric elements on the small-stiffness part to provide distributed force.The vibration environment dimension of high-speed aircraft and its influence to the failures of high-speed aircraft were analysed.Based on the research on the material and actuation dimension of the piezoelectric element,the feasibility of piezoelectric element used as the distributed excitation source in vibration test was analysed.Last,a test demonstration system was constituted and a serial of test items were carried out.Using this method,the RMS magnitude of one point on the flexible part of the structure can be controlled to 20.8 g.The rationality and the extensive engineering application potential of this technique are verified by the test results.

关 键 词：压电元件 分布式激励 振动试验 联合加载 

分 类 号：V216.5[航空宇航科学与技术—航空宇航推进理论与工程]