摘要
借助于Kane方法建立了充液中心刚体上带有挠性附件的航天器的开链多体动力学模型 .采用了混合坐标法和弹簧 质量块液体晃动等效力学模型 ,所得方程形式简洁 .由于引入了 2级附件 ,该模型具有更强的通用性 .以跟踪与数据中继卫星为例 ,给出了数值仿真结果 .
This paper deals with the modeling problem of a spacecraft consisting of a liquid-filled rigid platform and some flexible appendages. The spacecraft is modeled by using the Kane's equations. Hybrid-coordinate and spring-mass equivalent model for liquid sloshing are adopted in the modeling. With two-class appendages, the multi-body open-chain dynamic model can be applied more universally. Simulation results on a sample of tracking and data relay satellite were given to show the validity of the proposed model.
出处
《北京航空航天大学学报》
EI
CAS
CSCD
北大核心
2003年第1期35-38,共4页
Journal of Beijing University of Aeronautics and Astronautics
基金
国家自然科学基金资助项目 (19872 0 0 2 )
关键词
挠性
航天器
动力学
充液
KANE方法
Aircraft models
Computer simulation
Flexible structures
