上面级直接入轨卫星星箭供电接口设计与验证
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摘要
针对上面级直接入轨卫星转移轨道阶段用电需求如何解决的问题,文章根据上面级供电接口通用设计原则,从电源拓扑、箭内星用电池、供电安全等3个方面提出"一箭双星"上面级直接入轨卫星星箭电接口具体设计方法,并对其发射应用情况进行了总结。应用结果表明,该设计可以满足卫星与上面级分离前5h以上的用电需求,可以为各类型的上面级直接入轨卫星星箭供电接口设计提供参考,解决转移轨道段用电难题,提高卫星用电效率和可靠性。
In order to meet the demand of the energy consumption of direct injection satellites on the upper stages,this paper presents the restraint of the common design of power interface.The design of the power interface between two satellites and the upper stage has been presented according to power topological structure,batteries and the safety of power supply,then the conclusion of the practical appearance has been made.The design meets the energy demand of the satellite which is more than 5 hours before separation between satellites and upper stage.The conclusion provide the reference to all kinds of power interfaces between direct injection satellites and upper stages,solving the problem of power using on the transfer orbit and also improving efficiency and reliability.
In order to meet the demand of the energy consumption of direct injection satellites on the upper stages,this paper presents the restraint of the common design of power interface.The design of the power interface between two satellites and the upper stage has been presented according to power topological structure,batteries and the safety of power supply,then the conclusion of the practical appearance has been made.The design meets the energy demand of the satellite which is more than 5 hours before separation between satellites and upper stage.The conclusion provide the reference to all kinds of power interfaces between direct injection satellites and upper stages,solving the problem of power using on the transfer orbit and also improving efficiency and reliability.
引文
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[2]Kerslake W R,Ignaczak L R.Development and flight history of the SERT II spacecraft[J].Journal of Spacecraft and Rockets,1993,30(3):258-290
[3]Caveny L H,Geisler R L,Ellis R A,et al.Solid rocket enabling technologies and milestones in the united states[J].Journal of Propulsion and Power,2003,19(6):1038-1066
[4]崔波,曾毅,张晓峰.Galileo导航卫星电源技术概述[J].航天器工程,2011,19(6):115-120Cui Bo,Zeng Yi,Zhang Xiaofeng.Overview of Galileo navigation satellite power system[J].Spacecraft Engineering,2011,19(6):115-120(in Chinese)
[5]Mukund R Patel.航天器电源系统[M].韩波,陈琦,崔晓婷,译.北京:中国宇航出版社,2010:177-178Mukund R Patel.Spacecraft power systems[M].Han Bo,Chen Qi,Cui Xiaoting,translated.Beijing:China Astronautics Press,2010:177-178(in Chinese)
[6]Marco Manfreda,Stefano Costantini.Cosmoskymed electrical power system in flight performances[C]//Proceedings of the 8th European Space Power Conference.Paris:ESA,2008:1-7
[7]Gilles Bouhours,Remi Asplanato,Christophe Rebuffel,et al.A new generation of electrical power supply for telecom satellites[C]//Proceedings of the 10th European Space Power Conference.Paris:ESA,2014
[8]曾毅,崔波.一种新的航天器电源系统拓扑[J].航天器工程,2009,18(5):95-100Zeng Yi,Cui Bo.A novel topology of spacecraft electric power system[J].Spacecraft Engineering,2009,18(5):95-100(in Chinese)
[9]Soubrier L,Trehet E.High power PCU for alphabus:PSR100V[C]//9th European Space Power Conference.Paris:ESA,2014