中国空间科学技术

中国空间科学技术 ›› 2022, Vol. 42 ›› Issue (6): 54-63.doi: 10.16708/j.cnki.1000-758X.2022.0083

• 论文 • 上一篇    下一篇

面向立方星变轨任务的机动控制策略

张科文，潘柏松   

  1. 1 浙江工业大学 机械工程学院，杭州310023
    2 浙江工业大学 特种装备制造与先进加工技术教育部重点实验室，杭州310023
  • 出版日期:2022-12-25 发布日期:2022-11-09

Maneuver control strategy for CubeSat′s orbit change mission

ZHANG Kewen，PAN Baisong   

  1. 1 College of Mechanical Engineering,Zhejiang University of Technology,Hangzhou 310023,China
    2 Key Laboratory of Special Purpose Equipment and Advanced Processing Technology,Ministry of Education,
    Zhejiang University of Technology,Hangzhou 310023,China
  • Published:2022-12-25 Online:2022-11-09

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摘要： 为了实现立方星在轨飞行与变轨，基于模块化推进器系统提出混合控制策略实现微小卫星轨道持续变化任务需求。首先，针对多单元立方星单一主推进器的结构部署，基于高斯变分方程采用连续低推进力实现轨道机动变化。为了实现对立方星主推进器的指向调整，基于姿态动力学模型利用PD连续姿态控制求得所需扭矩，实现对立方星的指向角和指向角速度调节。针对配置的微脉冲等离子推进器(μ-PPT)不连续的特点，通过搜寻μPPT最优脉冲序列组合获得实际扭矩，满足对外部干扰的持续补偿以及立方星的姿态稳定和指向调整操作需求。此外，引入姿态误差敏感度阈值，使姿态控制器在能够提高系统鲁棒性的同时减少μ-PPT消耗。最后，通过对3U立方星在轨飞行与变轨的具体案例分析，表明所提出的基于微推进器系统的混合控制策略能够实现立方星轨道机动变化需求。

关键词: 立方星, 轨道变换, 微脉冲等离子推进器, 姿态调整, 控制设计

Abstract: For the realization of CubeSat orbit change and flying,a hybrid control method was proposed to realize the mission requirements of the continuous orbit change of CubeSat based on the modular thruster system.The multiunit CubeSat has one single main thruster,and the orbital change maneuver was based on the Gauss′ variational equations using continuous low thrust.In order to realize the pointing adjustment of CubeSat thruster,the PD controller was utilized based on the attitude dynamics model,to calculate the required torque to control the pointing angle and the angular velocity.For the discontinuous feature of the micro-pulse plasma thruster(μ-PPT),the required torque was obtained by searching for the optimal pulse sequence combination of μ-PPT allocation,which was used for continuous compensation of the external disturbances,as well as stabilizing and pointing the main thruster.In addition,the sensitivity threshold of attitude error was introduced to improve the robustness of the control system while reducing the consumption of μ-PPT.Finally,the specific mission analysis of a 3U CubeSat′s orbital flying and transferring was presented,which shows that the proposed hybrid control strategy can meet the mission requirement based on the micro propulsion system.

Key words: CubeSat, orbit change, micro-pulse plasma thruster, attitude adjustment, control design