摘要
针对空间飞行器柔性附件低频振动衰减缓慢降低系统稳定性和可靠性的问题,以带有驱动机构的太阳能电池翼为例,不增加额外机构,提出了以驱动机构为作动器、电池翼与驱动机构约束扭矩为目标的振动控制方法。推导了模态坐标表示的电池翼振动的状态方程,选择第一阶模态描述电池翼弯曲振动并设计反馈控制律。以钢质弹性直尺为模型,通过数值仿真验证了该方法的有效性。
The flexible appendage of a spacecraft usually has the feature of low rigidity and damping,and the slow attenuation of the low-frequency vibration may reduce the stability and reliability of the aircraft system.To solve the vibration problem of the spacecraft flexible appendage,the solar battery wings with driving mechanism was taken as an example and a vibration control method was proposed without adding any additional mechanism.The driving mechanism was used as the actuator and the constraint moment of the wings and driving mechanism was controlled.The state equation of the vibra-tion of the battery wings was derived by the modal coordinates.The first order mode was used to de-scribe the vibration of the battery wings and the feedback control law was developed.The effectiveness of the method was verified by numerical simulation with the steel elastic ruler as the model.
作者
李涛
陈必发
吕亮亮
唐国安
LI Tao;CHEN Bifa;LV Liangliang;TANG Guoan(Department of Aeronautics and Astronautics Fudan University, Shanghai 200433, China;Shanghai Institute of Aerospace System Engineering, Shanghai 201108, China)
出处
《载人航天》
CSCD
2017年第4期482-486,共5页
Manned Spaceflight
基金
国家自然科学基金(11572089)
关键词
振动控制
电池翼
模态坐标
反馈控制
vibration control
battery wings
modal coordinates
feedback control
