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

doi:10.3901/JME.2020.13.156

Abstract

Abstract: 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.

Key words: space debris, de-orbit removal, membrane structure

CLC Number:

V423

PENG Fujun, YUN Weidong, GENG Haifeng. Advancement and Key Technologies of Deployable Membrane Structure for Space Debris Removal[J]. Journal of Mechanical Engineering, 2020, 56(13): 156-164.

References

[1] NOCK K T,GATES K L,AARON K M. Gossamer orbit lowering device for safe and efficient de-orbit[C]//American Institute of Aeronautics and Astronautics. AIAA/AAS Astrodynamics Specialist Conference,August 2-5,2010,Toronto,Ontario Canada. Washington:AIAA,2010:7824.
[2] MINGHE S,GUO J,GILL E. Review and comparison of active space debris capturing and removal[J]. Progress in Aerospace Sciences,2016,80:18-32.
[3] 陆震. 小卫星和微纳卫星应用现状与挑战[J]. 兵器装备工程学报,2018(6):1-7. LU Zhen. Status and trends of the small satellite and micro-nano satellites[J]. Journal of Weaponry and Equipment Engineering,2018(6):1-7.
[4] 何慧东,付郁. 2017年全球小卫星发展回顾[J]. 国际太空,2018(2):51-56. HE Huidong,FU Yu. 2017 year in review:World small satellites[J]. Space International,2018(2):51-56.
[5] 何异舟. 小卫星技术与产业发展研究[J]. 电信网技术,2017(10):29-33. HE Yizhou. Study on technology and industrialization of small satellites[J]. Telecommunications Network Technology,2017(10):29-33.
[6] ADELI S N. Attitude control and deployment of nano-solar sail spacecraft[D]. Guildford:University of Surrey,2011.
[7] JOHNSON L,WHORTON M,HEATON A. NanoSail-D:A solar sail demonstration mission[C]//International Academy of Astronautics,Sixth IAA Symposium on Realistic Near-Term Advanced Scientific Space Missions,July 6-9,2009,Aosta,Italy. Paris:IAA,2009:505.
[8] ALHORN D C,CASAS J P. NanoSail-D:The small satellite that could[C]//National Aeronautics and Space Administration,25th Annual AIAA/USU Conference on Small Satellites,Aug 82011,AMES Research Center,Huntsville:NASA,2011:27.
[9] NEHRENZ M T. Initial design and simulation of the attitude determination and control system for LightSail-1[R]. San Luis Obispo:CPSA,2010
[10] BIDDY C,SVITEK T. LightSail-1 solar sail design and qualification[C]//Jet Propulsion Lab. Proceedings of the 41st Aerospace Mechanisms Symposium,May 16-18,2012,Pasadena,Ca. Pasadena:JPL,2012:1319.
[11] HILLEBRANDT M,MEYER S,ZANDER M. Deployment testing of the de-orbit sail flight hardware[C]//American Institute of Aeronautics and Astronautics,2nd AIAA Spacecraft Structures Conference,January 5-9,2015,Kissimmee,Florida. Washington:AIAA,2015:0434.
[12] STOHLMAN O R,LAPPAS V. Deorbitsail:A deployable sail for de-orbiting[C]//American Institute of Aeronautics and Astronautics,54th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,April 8-11,2013,Boston,Massachusetts. Washington:AIAA,2013:1806.
[13] STOHLMAN O R,FERNANDEZY J M. Testing of the deorbitsail drag sail subsystem[C]//American Institute of Aeronautics and Astronautics,54th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,April 8-11,2013,Boston,Massachusetts. Washington:AIAA,2013:1807.
[14] STOHLMAN O R,SCHENK M,LAPPAS V. Development of the Deorbitsail flight model[C]//American Institute of Aeronautics and Astronautics,Spacecraft Structures Conference,January 13-17,2014,National Harbor,Maryland. Washington:AIAA,2014:1509.
[15] MIYAZAKI Y,KINOSHITA N. A deployable membrane structure for de-orbiting a nano satellite[C]//International Academy of Astronautics. 58th International Astronautical Congress,September 24-28,2007,Hyderabad,India. Paris:IAA,2007:4508.
[16] MAESSEN D C,BREUKELEN E D. Development of a generic inflatable de-orbit device for CUBESATS[C]//International Academy of Astronautics. 58th International Astronau-tical Congress,September 24-28,2007,Hyderabad,India. Paris:IAA,2007:6306.
[17] RYSZAWA E,ROSZKOWSKI D. PW-Sat2 preliminary design review[R]. Warsaw:WUT,2016.
[18] 谭惠丰,侯一心. 高性能主动离轨立方体卫星[R]. 哈尔滨:哈尔滨工业大学,2018. TAN Huifeng,HOU Yixin. High performance de-orbit cubesat[R]. Harbin:Harbin Institude of Technology,2018.
[19] 曾玉堂. 立方体卫星制动帆离轨装置的设计与研究[D]. 南京:南京理工大学,2017. ZENG Yutang. Design of drag sail for de-orbit of cubesat[D]. Nanjing:Nanjing University of Science and Technology,2017
[20] FITIÉ A,BREUKELEN E,ROTTEVEEL J. Inflatable aerobrake for end-of-life de-orbit of nanosatellites performance evaluation and collision risk assessment[C]//Interna-tional Astronautical Federation,59th International Astronautical Congress,September 29-October 3,2008,Glasgow,United kingdom. Paris:IAF,2008:2398-3406.
[21] TSUDA Y,SAIKI T,FUNASE R. Generalized attitude model for spinning solar sail spacecraft[J]. Journal of Guidance,Control,and Dynamics,2013,36(4):1.
[22] SECHELI G,VIQUERAT A,AGLIETTI G. Mechanical development of a novel inflatable and rigidizable structure[C]//American Institute of Aeronautics and Astronautics,3rd AIAA Spacecraft Structures Conference,January 4-8,2016,San Diego,California,USA. Washington:AIAA,2016:1220.
[23] SATOU Y,MORI O,OKUIZUMI N. Deformation properties of solar sail IKAROS membrane with nonlinear finite element analyses[C]//American Institute of Aeron-autics and Astronautics,2nd AIAA Spacecraft Structures Conference,January 5-9,2015,Kissimmee,Florida. Washington:AIAA,2015:0436.
[24] ONO G,MATSUMOTO J,MIMASU Y. Development of mission devices and sub-systems on sail for world's first solar power sail IKAROS[J]. Japanese Rocket Society,2012,27(1):38-53.
[25] 沈自才,张帆,赵春晴. IKAROS太阳帆的关键技术分析与启示[J]. 航天器工程,2012(4):101-107. SHEN Zicai,ZHANG Fan,ZHAO Chunqing. Key technology analysis and enlightenment of IKAROS solar sail[J]. Spacecraft Engineering,2012(4):101-107.
[26] 陈罗婧,王沫,吕秋杰. 国外太阳帆薄膜材料选择及帆面展开方式研究进展[J]. 空间电子技术,2015(3):18-26. CHEN Luojing,WANG Mo,LÜ Qiujie. Recent progress on solar sail membrane materials and deployment technology[J]. Space Electronic Technology,2015(3):18-26.
[27] ARYA M,PELLEGRINO S. Deployment mechanics of highly compacted thin membrane structure[C]//Ameri-can Institute of Aeronautics and Astronautics,Spacecraft Structures Conference,January 13-17,2014,National Harbor,Maryland. Washington:AIAA,2014:1038.
[28] SHIRASAWA Y,MORI O,SAWADA H. A study on membrane dynamics and deformation of solar power sail demenstrator IKAROS[C]//American Institute of Aeronautics and Astronautics. 53rd AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,April 23-26,2012,Honolulu,Hawaii. Washington:AIAA,2012:1747.
[29] TSUDA Y,MORI O,FUNASE R. Achievement of IKAROS-Japanese deep space solar sail demonstration mission[J]. Acta Astronautica,2013,82:183-188.
[30] SAWADA H,SHIRASAWA Y,MORI O. On-orbit result and analysis of sail deployment of world's first solar power sail IKAROS[J]. Japanese Rocket Society,2012,27(1):54-68.
[31] SHIRASAWA Y,MORI O,MIYAZAKI Y. Analysis of membrane dynamics using multi-particle model for solar sail demonstrator IKAROS[C]//American Institute of Aeronautics and Astronautics. 52nd AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,April 4-7,2011,Denver,Colorado. Washington:AIAA,2011:1890.
[32] TORISAKA A,SATOH Y,AKITA T. Membrane space structure with sterical support of booms and cables[C]//American Institute of Aeronautics and Astronautics,3rd AIAA Spacecraft Structures Conference,January 4-8,2016,San Diego,California,USA. Washington:AIAA,2016:1217.
[33] ARYA M,LEE N,PELLEGRINO S. Wrapping thick membranes with slipping folds[C]//American Institute of Aeronautics and Astronautics,2nd AIAA Spacecraft Structures Conference,January 5-9,2015,Kissimmee,Florida. Washington:AIAA,2015:0682.
[34] BOUSQUET P,DUPUY C,BONNEFOND T. De-orbiting microscope spacecraft by drag enhancement[C]//International Academy of Astronautics. 57th Interna-tional Astronautical Congress,October 2-6,2006,Valencia,Spain. Paris:IAA,2006:6405.
[35] THOMAS G M. Prototype development and dynamic charac-terization of deployable cubesat booms[C]//American Institute of Aeronautics and Astronautics. 51st AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics and Materials Conference,April 12-15,2010,Orlando,FL,United States,Washington:AIAA,2010:2907.
[36] ROYBAL F A,BANIK J A,MURPHEY T W. Develop-ment of an elastically deployable room for tensioned planar structures[C]//American Institute of Aeronautics and Astronautics,48th AIAA/ASME/ASCE/AHS/ASC Structures,Structural Dynamics,and Materials Conference,April 23-26,2007,Honolulu,Hawaii. Washington:AIAA,2007:1838.
[37] SOBEY A R. Design and development of NEA scout solar sail deployer mechanism[C]//National Aeronautics and Space Administration,43rd Aerospace Mechanisms Symposium,May 4-6,2016,AMES Research Center. Huntsville:NASA,2016:14.