基于主动关节机构的航天扰性结构的振动控制

发布时间：2017-12-31 13:11

本文关键词：基于主动关节机构的航天扰性结构的振动控制　出处：《上海交通大学学报》2016年12期 　论文类型：期刊论文

【摘要】：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.
[Abstract]:Based on an active joint mechanism, the vibration control problem of spaceflight disturbed structures is studied. A new active vibration control method is proposed. The variable stiffness damping characteristics of the joint mechanism and the characteristics of the combined vibration control system based on the joint mechanism and the space solar panel are modeled and analyzed respectively. On this basis, the experimental platform is built and vibration control experiment is carried out. The self-test results of joint mechanism show that it is in the range of -15 掳~ 15 掳. The torsional stiffness of the joint mechanism is approximately linear with the excitation current. By changing the current, the stiffness can be changed in the range of 0.391N 路mrrad. In addition, the vibration test of space solar panel system shows that the stiffness can be changed in the range of 0.391N 路mrrad. The vibration active control of joint mechanism can increase the natural frequency of the system, attenuate the amplitude by 9.5 dB, and reduce the vibration to 1 / 3 of the original. The active control of the vibration of space solar panels is carried out effectively.
【作者单位】：上海交通大学机械与动力工程学院;
【基金】：国家自然科学基金(11172169) 航天联合基金(13GFZJJ08010)资助项目
【分类号】：V414;V442
【正文快照】： 太阳能帆板是航天器上最典型、最常见的扰性结构[1].更大的太阳能帆板阵列可以为空间结构提供更加充足的能源,所以大型化、扰性化航天结构件是新型航天器发展的一个重要趋势[2].这类大型结构件由于质量轻、刚度低、模态阻尼较小,一旦在太空中运行受到某种激振力的作用,其大幅

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