微小卫星可展式刚挠结合板太阳电池阵设计
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摘要
文章设计的可展式刚挠结合板太阳电池阵,将太阳电池阵电路与基板高度集成,省去电线、电缆连接,具有基板薄、质量小、电路连接简化及挠性可弯曲折叠等优点,可满足微小卫星太阳电池阵高质量比、高体积比功率的需求。以某卫星太阳电池阵为例,在185mm×420mm×20mm且收拢后板间距不大于5mm的包络内,采用刚挠结合板设计,可实现输出功率不小于60W,比使用传统太阳电池阵功率输出提高了1倍以上。其在轨应用结果表明,太阳电池阵功率输出稳定,可为微小卫星太阳电池阵设计提供参考。
The solar array is designed with rigid-flex plate,in which the solar cell circuit is integrated with the substrate,and the connection of wire and cable for solar array is eliminated.It has the advantages of thin panel,light weight,simplified circuit and flexible folding,etc which can meet the high weight specific power and the high volume specific power of the solar array for micro-satellite.Taking the design of a satellite solar array as an example,the output power of the solar array is not less than 60 W by using rigid-flex plate in the envelope of 85 mm×420 mm×20 mm,and the distance between the retracted rear panels is not more than 5 mm.The results of its on-orbit application show that the solar array power output is stable,and the design proposed in the paper can provide a reference for the design of micro-satellite solar array.
The solar array is designed with rigid-flex plate,in which the solar cell circuit is integrated with the substrate,and the connection of wire and cable for solar array is eliminated.It has the advantages of thin panel,light weight,simplified circuit and flexible folding,etc which can meet the high weight specific power and the high volume specific power of the solar array for micro-satellite.Taking the design of a satellite solar array as an example,the output power of the solar array is not less than 60 W by using rigid-flex plate in the envelope of 85 mm×420 mm×20 mm,and the distance between the retracted rear panels is not more than 5 mm.The results of its on-orbit application show that the solar array power output is stable,and the design proposed in the paper can provide a reference for the design of micro-satellite solar array.
引文
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[8]Patrick H.Design,construction and validation of an articulated solar panel for CubeSats[D].Lulea:Lulea University of Technology,2010
[9]李国欣.航天器电源系统技术概论[M].北京:中国宇航出版社,2008:744-745Li Guoxin.Introduction to spacecraft power supply system technology[M].Beijing:China Astronautics Press,2008:744-745(in Chinese)
[2]任守志,刘颖,王举,等.立方体卫星太阳翼综述[J].航天器工程,2015,24(2):109-117Ren Shouzhi,Liu Ying,Wang Ju,et al.Overview of solar wing for CubeSat[J].Spacecraft Engineering,2015,24(2):109-117(in Chinese)
[3]Alexander L Carrere.Solar panel design decision and general information sheet[EB/OL].[2018-04-20].http://browncubesat.org/wp-content/uploads/2013/01/Solar-panel Documentation.pdf
[4]Colorado Satellite Services,LLC.CSS bus for rampart(rapid prototyped microelectro mechanical system propulsion and radition test CUBE flow satellite)-the evolution of PCBSat for the RAMPART Cubesat[C]//Proceedings of the 7th Annual CubeSat Developers’Workshop.Luis Obispo:Cal Poly Campus,2010:1-4
[5]MMA.Innovative high specific performance(HaWK)solar array[EB/OL].[2018-04-20].http://www.mmadesignllc.com
[6]Adam Thurn,Steve Huynh.A nichrome burn wire release mechanism for CubeSats[C]//Proceedings of the41st Aerospace Mechanisms Symposium.Pasadena,California:NASA JPL,2012:1-3
[7]Clint Apland,David Persons.A novel release mechanism employing the principle of differential coefficients of thermal expansion[C]//Proceedings of the 41st Aerospace Mechanisms Symposium.Pasadena,California:NASA JPL,2012:1-4
[8]Patrick H.Design,construction and validation of an articulated solar panel for CubeSats[D].Lulea:Lulea University of Technology,2010
[9]李国欣.航天器电源系统技术概论[M].北京:中国宇航出版社,2008:744-745Li Guoxin.Introduction to spacecraft power supply system technology[M].Beijing:China Astronautics Press,2008:744-745(in Chinese)