太阳帆航天器展开机构柔性动力学建模  

Dynamic Modeling of Solar Sail Spacecraft Deployment Mechanism

作　　者：胡洁[1] 杨萱[1] 

机构地区：[1]中国科学院空间科学与应用研究中心,北京100190

出　　处：《微计算机信息》2012年第4期155-156,71,共3页Control & Automation

摘　　要：研究了大型太阳帆航天器展开机构的柔性动力学建模问题。首先对结合模态综合法和混合坐标法介绍了太阳帆展开机构柔性动力学一般模型建立过程。根据工程需要对展开机构进行模态分析,给出了工程实用的各耦合系数的计算表达式,并计算出各耦合系数。A dynamic modeling of solar sail spacecraft deployment mechanism is investigated in this paper. Firstly, a general dynamic model for solar sail spacecraft deployment mechanism is derived by using the hybrid coordinate and component modal synthesis. The model and flexible coupling coefficients developed can be used for analysis and simulation of many Solar Sail Spacecraft deployment mechanism. Finally, the effectiveness of the proposed method is demonstrated by an example.

关 键 词：太阳帆 可展开机构 动力学模型 混合坐标法 耦合系数 

分 类 号：V476.2[航空宇航科学与技术—飞行器设计]