中国空间科学技术

中国空间科学技术 ›› 2023, Vol. 43 ›› Issue (2): 81-92.doi: 10.16708/j.cnki.1000-758X.2023.0023

• 论文 • 上一篇    下一篇

异构多星编队的脉冲构型保持控制方法

杨盛庆，陈筠力，钟超，刘艳阳，王文妍   

  1. 1 上海航天控制技术研究所，上海201109
    2 上海市空间智能控制技术重点实验室，上海201109
    3 上海航天技术研究院，上海201109
    4 上海卫星工程研究所，上海201109
  • 出版日期:2023-04-25 发布日期:2023-03-13

Structure preserving method of isomerism multiple satellites formation under impulsive maneuver

YANG Shengqing，CHEN Junli，ZHONG Chao，LIU Yanyang，WANG Wenyan   

  1. 1 Shanghai Aerospace Control Technology Institute，Shanghai 201109，China
    2 Shanghai Key Laboratory of Aerospace Intelligent Control Technology，Shanghai 201109，China
    3 Shanghai Academy of Space Technology，Shanghai 201109，China
    4 Shanghai Institute of Satellite Engineering，Shanghai 201109，China
  • Published:2023-04-25 Online:2023-03-13

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摘要： 近地轨道的双星编队通常设计具有自稳定性的编队构型参数初值，通过保持编队构型参数形成长期稳定的相对周期运动。针对编队中卫星数量增多产生的相对运动耦合问题，提出了基于Hill坐标和三角函数公式的多星相对运动分析方法。基于SAR载荷测量基线定义，结合多星编队构型参数的相对运动特性，提出了编队构型参数的设计方法，能够实现多星编队的最大有效基线组合。通过分析J2项摄动和大气阻力摄动的长期影响，研究了异构多星编队的相对运动衍化规律，提出了主从形式的脉冲偏置控制，能够有效保持针对异构多星编队设计的编队构型。通过面质比异构的四星编队控制仿真，验证了脉冲偏置控制形式下异构多星编队构型保持控制方法的有效性。

关键词: 多星编队, 相对运动耦合, 构型参数, 载荷测量基线, 脉冲控制, 偏置控制, 面质比异构

Abstract:  In near earth orbit，the initial state of two satellites formation configuration parameters is usually designed to achieve a controlled long-term stable relative motion.Focusing on the coupling relative motion caused by multiple satellites formation，an analysis method of relative motion was proposed on the basis of the Hill coordinates and trigonometric function formulas.Based on the definition of sensing baseline of synthetic aperture radar (SAR) load，combining with the relative motion character of formation configuration parameters，a design method of configuration parameter was put forward to find the maximum effective baselines combination.The long term effect of J2 term and air drag perturbation was analyzed，based on which the relative motion of isomerism multiple satellites formation was studied and a leader-follower form of bias control was proposed under impulse maneuver to preserve the designed formation configuration.The control method was validated in a four satellites formation with isomerism area-mass ratios.

Key words: multiple satellites formation, coupling relative motion, configuration parameters, sensing baseline of load, impulsive maneuver, bias control, isomerism area-mass ratios