中国空间科学技术Issue(5)：49-55,7.DOI:10.3780/j.issn.1000-758X.2014.05.007
基于偏置角动量的欠驱动航天器姿态保持控制
Underactuated Spacecraft Attitude Hold Control Based on Bias Momentum Wheel
郭朝礼 1王淑一 1张笃周2
作者信息
- 1. 北京控制工程研究所，北京 100190
- 2. 空间智能控制技术重点实验室，北京 100190
- 折叠
摘要
Abstract
To maintain the three-axis attitude of the underactuated nadir-pointing spacecraft,an attitude hold control method based on the pitch-axis bias momentum wheel and roll-axis thruster was proposed.The method was based on coupling between the roll and yaw axes of biased-momentum spacecraft, and could avoid the problem that zero momentum spacecraft′s underactuated axis and actuated axis were almost decoupled. Spacecraft attitude dynamics was divided into long-period dynamics and short-period dynamics, and the control laws were designed by the pole-assignment method. The scale of control parameters was confirmed, and the stable state error of the control system was obtained. The simulation results show that the designed controller can eliminate initial attitude error of the spacecraft and resist the external disturbance,and the spacecraft attitude is maintained at the equilibrium point.关键词
偏置动量轮/推力器/欠驱动/姿态保持控制/航天器Key words
Bias momentum wheel/Thruster/Underactuated/Attitude hold control/Spacecraft引用本文复制引用
郭朝礼,王淑一,张笃周..基于偏置角动量的欠驱动航天器姿态保持控制[J].中国空间科学技术,2014,(5):49-55,7.
