| 大角速度柔性航天器动力学模型修正 |
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| 引用本文： | 罗婧,陈士明,董云峰.大角速度柔性航天器动力学模型修正[J].上海航天,2013(6):32-34,39. |
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| 作者姓名： | 罗婧 陈士明 董云峰 |
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| 作者单位： | 北京航空航天大学宇航学院,北京100191 |
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| 摘 要： | 将拉格朗日方程及其准坐标形式用于中心刚体加柔性附件航天器的拉格朗日函数，推导了中心刚体加柔性附件航天器动力学模型。针对航天器大角速度，分析中心刚体角速度对角动量方程的影响，对传统动力学模型进行修正。航天器绕惯量主轴大角速度自旋仿真结果验证了修正后的动力学模型对于大角速度航天器的有效性。
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| 关 键 词： | 柔性结构 姿态控制 动力学模型 航天器 大角速度 |
Dynamic Model Modification of Flexible Spacecraft with Large Angular Velocity |
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| LUO Jing,CHEN Shi-ming,DONG Yun-feng.Dynamic Model Modification of Flexible Spacecraft with Large Angular Velocity[J].Aerospace Shanghai,2013(6):32-34,39. |
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| Authors: | LUO Jing CHEN Shi-ming DONG Yun-feng |
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| Institution: | (School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China) |
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| Abstract: | The Lagrange equation and its quasi-coordinate form were applied into the Lagrange function of dynamic model of spacecraft with and central rigid body and flexible appendages, the dynamic model for spacecraft with relatively large angular velocity was derived in this paper. Aim to the spacecrafts with large angular velocity, the impact of the central rigid body＇s angular velocity on the flexible appendages＇ angular momentum was analyzed, and the conventional dynamic model was modified. The numerical simulation and theoretical analysis showed that the modified dynamic model was valid for spacecrafts with relatively big angular velocity. |
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| Keywords: | Flexible structure Attitude control Dynamic model Spacecraft Large angular velocity |
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