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基于一种主动关节机构,针对航天扰性结构的振动控制问题,提出了新的振动主动控制方法.分别对关节机构的变刚度阻尼特性以及基于关节机构和航天太阳能帆板组合振动控制系统的特性进行了理论建模与分析,在此基础上,搭建了实验测试平台并进行了振动控制实验.关节机构自测实验结果表明,在-15°~15°的范围内,关节机构的扭转刚度与励磁电流近似成线性关系;通过改变电流的大小,可以实现其刚度在0.391~1.362N·m/rad范围内的变化.另外,对航天太阳能帆板系统的振动测试实验表明,利用关节机构进行振动主动控制,可以提高系统的固有频率,使振幅衰减9.5dB,降低到原来的1/3,有效地对航天太阳能帆板的振动进行了主动控制.
Based on an active joint mechanism, a new active vibration control method is proposed for the vibration control of space-borne disturbance structures. The damping characteristics of variable stiffness of joint mechanism and the characteristics of joint vibration control system based on joint mechanism and spacecraft Based on this, the experimental test platform was set up and the vibration control experiment was carried out.The self-test results of the joint mechanism showed that the torsional stiffness of the joint mechanism in -15 ° ~ 15 ° The excitation current is approximately linear, and its stiffness can be varied within the range of 0.391 ~ 1.362N · m / rad by changing the current size.In addition, the vibration test of the aerospace solar windsurfing system shows that using the joint mechanism to vibrate Active control, can improve the natural frequency of the system, the amplitude attenuation 9.5dB, reduced to the original 1/3, the effective control of the vibration of the solar energy solar panel initiative.