Vibration and loud noise occur in aircraft load calibration tests when using automatic hydraulic loading system, which will directly affect security of aircraft and the testing workers. The load data of the system vibration during six-point symmetrical coordinated loading process of a high aspect ratio flexible wing is analyzed in both time domain and frequency domain. And the vibration characteristics of the test system are summarized. The key factors affecting the coordination of test system, such as the rigidity of the tested components, PID parameters of auto-loading system and the loading time, are studied in detail. The range of the PID parameters is provided based on the engineering experience. The results show that when structural stiffness of the load calibration test components is low, the coordination among the actuators becomes poor and the low frequency vibration of the auto-loading system may appear very easily. This low-frequency vibration can be prevented effectively by prolonging loading time and reducing the loading rate.%采用液压自动协调加载系统,在飞机载荷校准试验中出现振动现象,并伴有较大声响,直接影响到人机安全.通过时域分析和频域分析方法,对大展弦比柔性机翼六点对称协调加载过程中的载荷数据进行分析,总结试验系统振动特点,重点研究试验件结构刚度、自动加载系统PID参数以及加载时间等影响试验系统协调性的关键因素,并根据工程经验给出PID参数取值范围.结果表明载荷校准试验件结构刚度较小时,作动器之间的协调性变差,自动加载系统容易发生低频振动,而适当延长加载时间,降低加载速率,能够安全有效地防止振动发生.
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