摘要
对卫星本体附带3个太阳帆板的展开,基于柔性多体动力学理论,用有限元法离散化物理模型,由Kane方程建立了柔性多体展开附件可展开动力学的模型。
Aim to the deployment of the three solar panels of the satellite,the spacecraft accessories dynamics modeling using Kane method was studied based on flexible multibody dynamics theory in this paper,which the physic model was discrete by finite element method.
出处
《上海航天》
2015年第1期1-4,35,共5页
Aerospace Shanghai
关键词
航天器
多柔性系统
展开动力学
KANE方程
Spacecraft
Flexibility multibody system
Deployment dynamics
Kane method
