中国空间科学技术

中国空间科学技术 ›› 2022, Vol. 42 ›› Issue (2): 71-81.doi: 10.16708/j.cnki.1000-758X.2022.0024

• 论文 • 上一篇    下一篇

微小推力下小卫星的轨道递推与推力标定

张军华，陈建林，孙冲，袁建平   

  1. 1西北工业大学 航天学院航天飞行动力学技术重点实验室，西安710072
    2西北工业大学 民航学院，西安710072
  • 出版日期:2022-04-25 发布日期:2022-03-30

Onboard orbit propagation and micro-thrust calibration for small satellites

ZHANG Junhua, CHEN Jianlin, SUN Chong, YUAN Jianping   

  1. 1National Key Laboratory of Aerospace Flight Dynamic, Northwestern Polytechnical University, Xi’an 710072, China
    2School of Civil aviation, Northwestern Polytechnical University, Xi’an 710072, China
  • Published:2022-04-25 Online:2022-03-30

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摘要： 针对采用微小推力进行轨道机动的小卫星，考虑复杂摄动力的基础设计了一种高精度轨道外推和推力在轨标定算法。首先，建立了考虑地球复杂摄动力和微小推力的小卫星轨道动力学模型；然后基于动力学模型，利用变步长龙格库塔算法，设计了对微小推力小卫星进行高精度轨道外推的方法。随后通过无迹卡尔曼滤波器(UKF)，设计在轨标定算法，对存在误差的微小推力实时标定进行了研究。最后，根据轨道外推仿真验证结果和STK软件结果进行对比，验证了轨道递推方法的有效性和精确性，通过推力标定的仿真结果，验证了推力在轨标定算法的精确性和可行性。

关键词: 微小推力, 复杂摄动, 轨道递推, 推力标定, 无迹卡尔曼滤波(UKF)

Abstract: To accurately address the orbit motion of small satellites in low Earth orbit, a kind of high-precision orbital propagation algorithm and on-orbit thrust calibration algorithm based on the consideration of complex perturbation forces were designed. Firstly, the dynamic model for small satellites was established considering the gravitational force of the sphere Earth and several perturbations. The variable-step Runge-Kutta integrator was employed in the orbit propagation. Then, using the unscented kalman filter (UKF), an on-orbit calibration algorithm was designed to calibrate the micro-thrust with errors in real time. To validate the effectiveness and accuracy of the proposed orbit prediction method, its results were compared with those of STK programs in a great number of simulation scenarios. The numerical simulation shows that the joint orbit determination and electric thrust calibration are quite precise.

Key words: microthrust, complex perturbation, orbital propagation, thrust calibration, unscented kalman filter (UKF)