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基于FRA精细模型的航天器三轴姿态稳定控制

关宏 徐世杰

关宏, 徐世杰. 基于FRA精细模型的航天器三轴姿态稳定控制[J]. 北京航空航天大学学报, 2014, 40(4): 479-485. doi: 10.13700/j.bh.1001-5965.2013.0316
引用本文: 关宏, 徐世杰. 基于FRA精细模型的航天器三轴姿态稳定控制[J]. 北京航空航天大学学报, 2014, 40(4): 479-485. doi: 10.13700/j.bh.1001-5965.2013.0316
Guan Hong, Xu Shijie. Attitude dynamics and control of spacecraft with fluidic ring actuator based on the refined model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(4): 479-485. doi: 10.13700/j.bh.1001-5965.2013.0316(in Chinese)
Citation: Guan Hong, Xu Shijie. Attitude dynamics and control of spacecraft with fluidic ring actuator based on the refined model[J]. Journal of Beijing University of Aeronautics and Astronautics, 2014, 40(4): 479-485. doi: 10.13700/j.bh.1001-5965.2013.0316(in Chinese)

基于FRA精细模型的航天器三轴姿态稳定控制

doi: 10.13700/j.bh.1001-5965.2013.0316
详细信息
    作者简介:

    关 宏(1985- ),女,北京人,博士生,grace.guan4664@gmail.com.

  • 中图分类号: V448.22

Attitude dynamics and control of spacecraft with fluidic ring actuator based on the refined model

  • 摘要: 针对非线性影响因素对FRA控制精度的影响,分析了黏性对射流动量控制(FRA,Fluidic Ring Actuator)模型精度的影响以及摩擦对压力泵控制精度的影响.对前者,推导出黏性对FRA角动量传递的影响方程,得到附面层动量损失厚度模型以及管流动量损失模型;对后者,设计了摩擦补偿控制律,以改善指令跟踪精度.将上述两部分模型组合到FRA动力学模型中,得到了适用于高精度姿态控制的精细FRA动力学与控制模型.设计了姿态控制律并进行了稳定性证明.仿真结果验证了FRA精细模型对提高姿态控制精度的有效性.

     

  • [1] Wallsgrove R J, Akella M R.Globally stabilizing saturated attitude control in the presence of bounded unknown disturbances[J].Journal of Guidance, Control and Dynamics, 2005, 28(5):957-963
    [2] Jing W X, Xia X W, Gao C S, et al.Attitude control for spacecraft with swinging large scale payload[J].Chinese Journal of Aeronautics, 2011, 24(3):309-317
    [3] Wang W, Li J F, Wang T S.Study on sloshing damping in a container of spacecraft(part 1):theory[J].Journal of Astronautics, 2005, 26(6):687-692
    [4] Wang W, Li J F, Wang T S.Study on sloshing damping in a container of spacecraft(part 2):numerical method[J].Journal of Astronautics, 2006, 27(2):177-180
    [5] Zhang J R, Rachid A, Zhang Y.Attitude control for part actuator failure of agile small satellite[J].Acta Mechanica Sinica, 2008, 24(4):463-468
    [6] 卢松涛, 王磊, 赵育善.双框架控制力矩陀螺奇异性分析[J].北京航空航天大学学报, 2008, 34(9):1096-1100 Lu Songtao, Wang Lei, Zhao Yushan.Double gimbal control moment gyroscopes singularity analysis[J].Journal of Beijing University of Aeronautics and Astronautics, 2008, 34(9):1096-1100(in Chinese)
    [7] Bryce A R, Jeffrey W K, Thomas B A, et al.Three-axis attitude control with two reaction wheels and magnetic torquer bars[R].AIAA 2004-5245, 2004
    [8] 张尧, 黄庭轩, 徐世杰.星上控制力矩陀螺群隔振平台的动力学特性[J].北京航空航天大学学报, 2012, 38(1):80-85 Zhang Yao, Huang Tingxuan, Xu Shijie.Dynamic characteristic of vibration isolation platform of control moment gyroscopes on satellites[J].Journal of Beijing University of Aeronautics and Astronautics, 2012, 38(1):80-85(in Chinese)
    [9] Kelly A, McChesney C, Smith P, et al.A performance test of fluidic momentum controller in three axes[D].Texas:The University of Texas, 2004
    [10] Kumar K D.Satellite attitude stabilization using fluid rings[J].Acta Mechanic, 2009, 208(1/2):117-131
    [11] Nobari N A, Misra A.Satellite attitude stabilization using four fluid rings in a pyramidal configuration[C]//AIAA/AAS Astrodynamics Conference.Reston, VA:AIAA, 2010:7652-1-7652-13
    [12] 田林.考虑执行机构非线性的航天器姿态控制研究[D].北京:北京航空航天大学, 2012 Tian Lin.Study on spacecraft attitude control considering the nonlinearity of actuator[D].Beijing:Beijing University of Aeronautics and Astronautics, 2012(in Chinese)
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出版历程
  • 收稿日期:  2013-05-31
  • 网络出版日期:  2014-04-20

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