北京航空航天大学学报 ›› 2003, Vol. 29 ›› Issue (1): 35-38.

• 论文 • 上一篇    下一篇

充液挠性航天器的建模与动力学分析

贾英宏1, 徐世杰2, 聂润兔3   

  1. 1. 哈尔滨工业大学 航天工程与力学系;
    2. 北京航空航天大学 宇航学院;
    3. 天津民航学院
  • 收稿日期:2001-07-06 出版日期:2003-01-31 发布日期:2010-09-27
  • 作者简介:贾英宏(1976-),男,内蒙古赤峰人,博士生,150001,哈尔滨.
  • 基金资助:

    国家自然科学基金资助项目(19872002)

Modeling and Dynamics Analysis of LiquidFilled Flexible Spacecraft

Jia Yinghong1, Xu Shijie2, Nie Runtu3   

  1. 1. Dept. of Astronautic Engineering and Mechanics, Harbin Institute of Technology;
    2. School of Astronautics, Beijing University of Aeronautics and Astronautics;
    3. Tianjin Institute of Civil Aviation
  • Received:2001-07-06 Online:2003-01-31 Published:2010-09-27

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.

Abstract: 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.

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