Advancement and Key Technologies of Deployable Membrane Structure for Space Debris Removal

被引：0
|
作者：
Peng F. [1 ,2 ]
Yun W. [1 ,2 ]
Geng H. [1 ,2 ]
机构：
[1] Shanghai Institute of Aerospace System Engineering, Shanghai
[2] Shanghai Key Laboratory of Spacecraft Mechanism, Shanghai
来源：
Jixie Gongcheng Xuebao/Journal of Mechanical Engineering | 2020年 / 56卷 / 13期
关键词：
De-orbit removal; Membrane structure; Space debris;
D O I：
10.3901/JME.2020.13.156
中图分类号：
学科分类号：
摘要：
The status of space debris and removal technology were introduced at first. The development of small satellite constellation and study on de-orbit specification of satellite were summarized. The advancement of the space debris removal membrane structure was proposed due to its unique properties such as low cost, high degree of technological maturity and good applicability for all kinds of LEO satellites. Key technologies associated with the membrane structure were presented, such as structure configuration design technology, long life membrane technology, fold and deploy technology, low cost design technology, and the approaches to solve these key problems were introduced. The analysis showed that the status of space debris will be even more threatening due to the rapid development of small satellite constellation, new de-orbit specification of satellite will be promulgated soon, the application of space debris removal membrane structure was urgently demanded. The main technologies associated with the membrane structure had been studied and tested in space flight, the technique will be widely applied in the future. © 2020 Journal of Mechanical Engineering.
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页码：156 / 164
页数：8
相关论文
共 37 条
  • [1] NOCK K T, GATES K L, AARON K M., Gossamer orbit lowering device for safe and efficient de-orbit, American Institute of Aeronautics and Astronautics. AIAA/AAS Astrodynamics Specialist Conference, (2010)
  • [2] MINGHE S, GUO J, GILL E., Review and comparison of active space debris capturing and removal, Progress in Aerospace Sciences, 80, pp. 18-32, (2016)
  • [3] LU Zhen, Status and trends of the small satellite and micro-nano satellites, Journal of Weaponry and Equipment Engineering, 6, pp. 1-7, (2018)
  • [4] HE Huidong, FU Yu, 2017 year in review: World small satellites, Space International, 2018, 2, pp. 51-56
  • [5] HE Yizhou, Study on technology and industrialization of small satellites, Telecommunications Network Technology, 10, pp. 29-33, (2017)
  • [6] ADELI S N., Attitude control and deployment of nano-solar sail spacecraft, (2011)
  • [7] JOHNSON L, WHORTON M, HEATON A., NanoSail-D: A solar sail demonstration mission, International Academy of Astronautics, Sixth IAA Symposium on Realistic Near-Term Advanced Scientific Space Missions, (2009)
  • [8] ALHORN D C, CASAS J P., NanoSail-D: The small satellite that could, National Aeronautics and Space Administration, 25th Annual AIAA/USU Conference on Small Satellites, (2011)
  • [9] NEHRENZ M T., Initial design and simulation of the attitude determination and control system for LightSail-1, (2010)
  • [10] BIDDY C, SVITEK T., LightSail-1 solar sail design and qualification, Jet Propulsion Lab. Proceedings of the 41st Aerospace Mechanisms Symposium, (2012)
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