北京航空航天大学学报 ›› 2016, Vol. 42 ›› Issue (8): 1715-1723.doi: 10.13700/j.bh.1001-5965.2015.0535

• 论文 • 上一篇    下一篇

基于极点配置的空间站角动量管理

党庆庆, 金磊, 徐世杰   

  1. 北京航空航天大学 宇航学院, 北京 100083
  • 收稿日期:2015-08-24 出版日期:2016-08-20 发布日期:2015-12-08
  • 通讯作者: 金磊,Tel.:010-82339750,E-mail:jinleibuaa@163.com E-mail:jinleibuaa@163.com
  • 作者简介:党庆庆,男,硕士研究生。主要研究方向:导航制导与控制。Tel.:010-82339750。E-mail:dangqingqingbuaa@163.com;金磊,女,博士,副教授,硕士生导师。主要研究方向:航天器姿态动力学与控制。Tel.:010-82339750。E-mail:jinleibuaa@163.com
  • 基金资助:
    国家自然科学基金(11272027)

Angular momentum management of space station based on pole placement

DANG Qingqing, JIN Lei, XU Shijie   

  1. School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
  • Received:2015-08-24 Online:2016-08-20 Published:2015-12-08

摘要: 针对惯性系下引力梯度力矩及其他干扰力矩引起控制力矩陀螺(CMG)角动量积累的问题,采用引力梯度力矩来平衡姿态,设计了基于极点配置的空间站角动量管理控制器。首先在惯性系下建立了空间站线性化模型,并分析了俯仰轴方向在惯性系角动量管理的不可行性。由此,将俯仰轴与滚动/偏航轴解耦,不约束俯仰轴方向的CMG角动量,将常值、1倍和2倍于轨道频率的扰动纳入状态方程以抑制其对俯仰轴姿态的影响。在滚动/偏航轴方向将常值扰动纳入状态方程中以抑制其对CMG角动量的影响;将1倍、2倍于轨道频率的扰动纳入到状态方程中以抑制其对姿态的影响。然后采用带极点配置的线性二次型(LQR)算法求解出反馈增益矩阵,该算法可以避免选取权重矩阵,并且根据系统性能要求即能将闭环极点配置到复平面虚轴左侧指定的区域。最后仿真结果验证了该算法的可行性。

关键词: 空间站, 姿态控制/角动量管理(ACMM), 极点配置, 引力梯度力矩, 惯性系

Abstract: For the problem that gravity-gradient torque and other disturbance torques can cause the accumulation of control momentum gyros (CMG) angular momentum when space station operates in inertial frame. Gravity-gradient torque is used for torque equilibrium attitude. An angular momentum management controller based on pole placement is proposed. First, the linearized model of space station in inertia frame is established and the infeasibility of the pitch axis direction of angular momentum management is proved. So we decouple the pitch axis and the roll/yaw axis, and do not constrain the angular momentum of CMG in pitch axis. The disturbance rejection filters are introduced to suppress the disturbance's impact on attitude in pitch axis. In orbit plane, to limit the cyclic disturbance's impact on roll/yaw axis and the secular disturbance's impact on the angular momentum of CMG, other disturbance rejection filters are introduced. Then, feedback controllers in pitch and row/yaw axis are developed based on linear quadratic regulators (LQR) with pole placement respectively. This algorithm is developed to place the closed-loop poles to the left side of complex plane imaginary axis based on the system performance requirements without choosing weight matrix. Finally, the simulation results demonstrate the validity of the proposed algorithm.

Key words: space station, attitude control/momentum management (ACMM), pole placement, gravity-gradient torque, inertial frame

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