基于主动关节机构的航天扰性结构的振动控制  

Vibration Control of Flexible Spacecraft Panel Structures Based on an Active Joint

作　　者：何泉[1] 刘澜涛[1] 杨斌堂[1] HE Quan LIU Lantao YANG Bintang(School of Mechanical Engineering, Shanghai Jiaotong University, Shanghai 200240, Chin)

机构地区：[1]上海交通大学机械与动力工程学院,上海200240

出　　处：《上海交通大学学报》2016年第12期1809-1815,共7页Journal of Shanghai Jiaotong University

基　　金：国家自然科学基金(11172169);航天联合基金(13GFZJJ08010)资助项目

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．A novel method of vibration control for flexible spacecraft panel structures based on an active joint was studied in this paper. First, the variable stiffness and damping characteristics of the joint were presented. Then, the modeling and analysis were conducted of the combined system of the joint and the spacecraft solar panel structures. Finally, experiments were performed. The results of the experiment indicate that the torsional stiffness of the joint is linear to the excitation current from -15° to 15°. By changing the current, the stiffness could be changed from 0. 391 to 1. 362 N· m/rad. Besides, the vibration test of the combined system shows that by the active control of the joint, the nature frequency of the system has been increased and the amplitude of the vibration has been attenuated by 9.5 dB, down to 1/3 of its original value.

关 键 词：主动关节 变刚度阻尼特性 振动主动控制 太阳能帆板 

分 类 号：TP211[自动化与计算机技术—检测技术与自动化装置] TP27[自动化与计算机技术—控制科学与工程]