宇航学报 ›› 2020, Vol. 41 ›› Issue (1): 19-26.doi: 10.3873/j.issn.1000-1328.2020.01.003

• 飞行器设计与力学 • 上一篇    下一篇

多充液贮腔航天器耦合动力学与姿态控制

刘峰,岳宝增,唐勇   

  1. 北京理工大学宇航学院,北京 100081
  • 收稿日期:2018-11-08 修回日期:2019-04-23 出版日期:2020-01-15 发布日期:2020-01-25
  • 基金资助:
    国家自然科学基金(11472041,11772049,11532002,11802320)

Dynamics Modeling and Attitude Control of Spacecraft with Multiple Propellant Tanks

LIU Feng, YUE Bao zeng, TANG Yong   

  1. School of Aerospace Engineering, Beijing Institute of Technology, Beijing 100081, China
  • Received:2018-11-08 Revised:2019-04-23 Online:2020-01-15 Published:2020-01-25

摘要: 基于已有的质心面液体大幅晃动等效力学模型,采用拉格朗日方法,系统地建立了任意复杂激励下四贮腔航天器刚-液耦合动力学精确模型。由本文方法所得到的等效晃动力及晃动力矩与通过Flow3D计算出的相应结果吻合良好,验证了所建模型的可靠性。根据所建立的大幅晃动类充液航天器耦合系统动力学模型进一步研究了该类航天器在进行三轴稳定姿态机动时的主要动力学耦合特性,并设计了一类抑制姿态振荡的补偿控 制器。

关键词: 质心面模型, 液体大幅晃动, 多贮腔航天器, 三轴稳定姿态机动, 补偿控制

Abstract: This paper is focused on the accurate dynamics modeling of a multi-tank spacecraft through the Lagrangian approach. The sloshing liquid in the tanks is represented by a constraint surface model for liquid sloshing. The equivalent slosh forces and torques acted on the spacecraft hub, when the spacecraft is excited by a set of arbitrary complex excitations in zero-g environment, are compared with the Flow3D results, and the results show good agreements. Based on the derived mathematical model, a kind of compensation controller is developed for jitter-suppressing in attitude motion of this liquid-filled spacecraft, when the spacecraft executes three-axial-stabilized attitude maneuvers.

Key words: Constraint surface model for liquid sloshing, Large amplitude liquid slosh, Multi-tank spacecraft, Three-axis-stabilized attitude maneuver, Compensation control

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