带挠性伸展太阳帆板航天器的姿态动力学

带挠性伸展太阳帆板航天器的姿态动力学

程绪铎^1,2

1. 南京财经大学食品科学与工程学院，南京 210003; 2. 安庆师范学院物理系, 安庆 246011

收稿日期:2003-11-11 修回日期:1900-01-01 出版日期:2004-07-26 发布日期:2004-07-26
通讯作者: 程绪铎

Attitude dyanmics of a spacecraft with deploying flexible plates

CHENG Xu-duo^1,2

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

Received:2003-11-11 Revised:1900-01-01 Online:2004-07-26 Published:2004-07-26
Contact: CHENG Xu-duo

摘要/Abstract

摘要： 利用动量矩定理推导出带挠性伸展太阳帆板航天器的姿态动力学方程，利用牛顿第二定理推导出挠性板上质量微元的动力学方程. 在板等速伸展的情况下对系统动力学方程进行变换，得到板伸展运动、振动与航天器姿态运动的耦合微分方程. 用Runge-Kutta积分法对方程进行积分，给出了板等速伸展时板振动振幅、航天器姿态角速率对时间的响应.

关键词: 航天器, 姿态动力学, 挠性伸展板

Abstract: The attitude dynamic equations of a spacecraft with deploying flexible plates are derived by means of the momentum theorem. The dynamic equations by differentiation with respect the mass of the flexible plates are derived with the aid of Newtons second law. When the flexible plates deploying at a uniform velocity the dynamic equations of the system are alternated. By using Runge-Kutta method the numerical results are obtained. The responses of amplitudes of the vibration of the flexible plates to time are given. The responses of attitude angular velocity of the spacecraft to time are given.

Key words: spacecraft, attitudedynamic, flexible deploying plate

中图分类号:

O313.7

程绪铎. 带挠性伸展太阳帆板航天器的姿态动力学[J]. J4, 2004, 42(03): 427-432.

CHENG Xu-duo. Attitude dyanmics of a spacecraft with deploying flexible plates[J]. J4, 2004, 42(03): 427-432.