Optimal control method for low thrust deorbit of the low earth orbit satellite based on ALPSO algorithm

被引：0
|
作者：
Li J. [1 ]
Hu M. [1 ]
Wang X. [1 ]
Xu J. [1 ]
Li F. [1 ]
机构：
[1] School of Space Command, Space Engineering University, Beijing
来源：
Xi Tong Gong Cheng Yu Dian Zi Ji Shu/Systems Engineering and Electronics | 2021年 / 43卷 / 01期
关键词：
Low earth orbit satellite; Low thrust deorbit; Optimal control; Particle swarm optimal algorithm;
D O I：
10.3969/j.issn.1001-506X.2021.01.24
中图分类号：
学科分类号：
摘要：
The low earth orbit satellite needs to deorbit within a certain period of time after reaching their lifetime, while satellite with orbit height above 800 km is difficult to deorbit under natural conditions. In order to make the satellite deorbit within a specified time, an optimal control algorithm for low thrust deorbit of the low earth orbit satellite based on the augmented Lagrangian particle swarm optimization (ALPSO) algorithm is proposed. Firstly, the perturbation equation is listed according to the characteristics of low thrust, and the Hamilton equation is used to acquire the optimal control rate with co-state parameters. Then, the particle swarm algorithm and the augmented Lagrangian method are expounded respectively, and the algorithm flow is obtained accordingly. Finally, it is compared with the optimization results of the genetic algorithm. The results show that the ALPSO algorithm has fewer iterations and higher convergence accuracy. The first disposal orbit with reduced orbit altitude is suitable for satellite deorbit with an orbit altitude of 821 km, and the deorbit time is 857 days. The algorithm can be applied to solve the low thrust deorbit problem of the low earth orbit satellite. © 2021, Editorial Office of Systems Engineering and Electronics. All right reserved.
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页码：199 / 207
页数：8
相关论文
共 32 条
  • [1] ZHANG G Y, FAN H H, CAI L F, Et al., Active deorbit disposal strategy for LEO satellite based on orbit elevation, Spacecraft Engineering, 27, 2, pp. 19-25, (2018)
  • [2] YAKOVLEV M., The IADC space debris mitigation guidelines and supporting documents, Proc.of the 4th European Conference on Space Debris, (2005)
  • [3] REID T G, NEISH A M, WALTER T F, Et al., Leveraging commercial broadband LEO constellations for navigation, Proc.of the ION GNSS, pp. 2300-2314, (2016)
  • [4] RADTKE J, KEBSCHULL C, STOLL E., Interactions of the space debris environment with mega constellations-using the example of the OneWeb constellation, Acta Astronautica, 131, 3, pp. 55-68, (2017)
  • [5] MCDOWELL J C., The low earth orbit satellite population and impacts of the SpaceX Starlink constellation, The Astrophysical Journal Letters, 892, 2, (2020)
  • [6] HUANG S, COLOMBO C, ALESSI E M., Trade-off study on large constellation deorbiting using low-thrust and deorbiting balloons, Proc.of the 10th International Workshop on Satellite Constellations and Formation Flying, (2019)
  • [7] GUGLIELMO D, OMAR S, BEVILACQUA R, Et al., Drag deorbit device: a new standard reentry actuator for CubeSats, Journal of Spacecraft and Rockets, 56, 1, pp. 129-145, (2019)
  • [8] PETERS T V, BRIZ V J F, ESCORIAL O D, Et al., Attitude control analysis of tethered de-orbiting, Acta Astronautica, 146, 5, pp. 316-331, (2018)
  • [9] HUANG G Q, LU Y P, NAN Y, Et al., Trajectory global optimization for multi-objective in space exploration by low-thrust control, Systems Engineering and Electronics, 34, 8, pp. 1652-1659, (2012)
  • [10] FROMM C M, HERBERTZ A., Using electric propulsion for the de-orbiting of satellites, Proc.of the 5th CEAS Air & Space Conference, (2015)
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