上海航天2018，Vol.35Issue(3)：48-53,6.DOI:10.19328/j.cnki.1006-1630.2018.03.008
基于驱动机构作动的太阳翼振动控制原理与实验研究
Principle and Experiment Study of Vibration Control in Solar Array Based on Actuating Mechanism
摘要
Abstract
For the problem that spacecraft system cannot work normally caused by long time low-frequency vibration in solar array during the process of spacecraft attitude adjustment or orbital maneuver, the driving mechanism is taken as the actuator, providing feedback control force to suppress the vibration. Based on the principle study, the real-size solar array finite element model is established. By improving the original algorithm, the solar array can return to target position after vibration control. In addition, the effectiveness of the low-frequency vibration suppression method of the solar array is verified experimentally by dynamic scaled model. The result shows that without introducing extra load, the control method can ensure that the solar array does not deviate from target position and can suppress the vibration effectively.关键词
太阳翼/低频振动/反馈控制/有限元仿真/缩比实验Key words
solar array/low-frequency vibration/feedback control/finite element simulation/scaled model experiment分类
数理科学引用本文复制引用
李涛,朱春艳,陈必发,张美艳,唐国安..基于驱动机构作动的太阳翼振动控制原理与实验研究[J].上海航天,2018,35(3):48-53,6.基金项目
国家自然科学基金(11572089) （11572089）
上海市科学技术委员会扬帆计划(15YF1411900) （15YF1411900）
