带挠性轴太阳帆板与航天器中心刚体耦合动力学研究

带挠性轴太阳帆板与航天器中心刚体耦合动力学研究

程绪铎^1,2

1. 南京经济学院食品科学与工程系, 南京 210003; 2. 安庆师范学院物理系, 安庆 246011

收稿日期:2002-11-21 修回日期:1900-01-01 出版日期:2003-07-26 发布日期:2003-07-26
通讯作者: 程绪铎

Couple Dynamics of Solar Wings and the Central Rigid Body on Spacecraft with Flexible Shaft

CHENG Xu-duo^1,2

1. Department of Science and Engineering of Food, Nanjing Economic University, Nanjing 210003, China；2. Department of Physics, Anqing Teachers College, Anqing 246011, China

Received:2002-11-21 Revised:1900-01-01 Online:2003-07-26 Published:2003-07-26
Contact: CHENG Xu-duo

摘要/Abstract

摘要： 建立了带挠性轴太阳帆板航天器的物理模型，利用保守系统的Lagrange方程，导出了带挠性轴太阳帆板航天器系统动力学方程. 通过变换，给出太阳帆板、航天器中心刚体耦合运动微分方程组. 应用Runge-Kutta积分法得出数值结果. 并分析了太阳帆板转动惯量、挠性轴的扭转刚度、太阳帆板的初始扰动对航天器姿势运动的影响.

关键词: 航天器, 挠性轴, 耦合动力学

Abstract: In this paper, the physical model of solar wings on a spacecraft with a flexible shaft is established. The dynamic equation of solar wings on the spacecraft with a flexible shaft is derived by using Lagrange equation. By transformation, the differential equation group of couple motions of solar wings and the central rigid body of the spacecraft is obtained. The influences of the torsional stiffness of a flexible shaft and rotational inertia of the solar wings on the attitude motion are analyzed. The influence of initial motions of the solar wings on the attitude motion is also analyzed.

Key words: spacecraft, flexible shaft, coupled dynamics

中图分类号:

O313.3

程绪铎. 带挠性轴太阳帆板与航天器中心刚体耦合动力学研究[J]. J4, 2003, 41(03): 342-346.

CHENG Xu-duo. Couple Dynamics of Solar Wings and the Central Rigid Body on Spacecraft with Flexible Shaft[J]. J4, 2003, 41(03): 342-346.