This paper introduces the structural filter design of a variable stability aircraft control system and the ground test of structural resonance.
本文介绍变稳飞机控制系统结构滤波器设计及结构谐振地面试验。
The test and analysis shows that this type of control system is capable of lessening structural vibration response efficiently.
试验与分析表明，所提出和研制的半主动控制系统能够有效地减小结构的振动反应。
Through ground test, suitable parameters of the structural filter are selected and the coupling between the flight control system and the aircraft elasticity structure is effectively restrained.
通过试验，选择了合适的结构滤波器参数，有效地抑制了飞行控制系统与飞机弹性结构之间的耦合。
In system identification procedure to structural damage, modeling error and test error are main reasons for.
在结构损伤的系统识别过程中，模型误差和测试误差是引起误判的主要原因。
Considering the structural characteristics of the intermittent chain drive system of die-cutting machine, a test rig was set up and a large number of experimental studies are performed.
针对模切机步进链传动系统的结构特点，建立了能够揭示该类系统动力学特性的实验台，并进行了大量的实验研究。
Considering the structural characteristics of the intermittent chain drive system of die-cutting machine, a test rig was set up and a large number of experimental studies are performed.
针对模切机步进链传动系统的结构特点，建立了能够揭示该类系统动力学特性的实验台，并进行了大量的实验研究。
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