全电推卫星用可分离推进舱设计及应用  

Design and Application of Separate Propulsion System for Full Electric Propulsion Satellite

作　　者：李巍[1] 梁新刚[2] 黎飞[1] 马雪[1] LI Wei;LIANG Xingang;LI Fei;MA Xue(Beijing Institute of Control Engineering,Beijing 100094,China;China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]北京控制工程研究所,北京100094 [2]中国空间技术研究院,北京100094

出　　处：《空间控制技术与应用》2024年第5期55-61,共7页Aerospace Control and Application

基　　金：民用航天技术预先研究项目(D030301)。

摘　　要：亚太6E卫星是我国第一颗全电推卫星,卫星采用低成本火箭发射,星箭分离轨道为近地轨道.针对全电推卫星电推轨控推力小和入轨时间长的特点,卫星设计采用可分离推进舱进行快速轨道提升的方案,完成任务后可抛离.由于在轨工作时间短,可分离推进舱采用低成本设计,轨道控制方面,设计采用可分离推进舱进行轨道控制以及与卫星分离后自主离轨方法.可分离推进舱轨控任务完成后与卫星分离,减少了卫星的质量,进而减少后续电推变轨时间,降低电推进剂氙气的消耗,对提升卫星承载能力以及提高卫星寿命有较大优势.APSTAR-6E satellite is the first full electric propulsion satellite in China.It is launched by a low-cost rocket,and the separation orbit is LEO.In response to the characteristics of small thruster and long orbit transition,in order to shorten the orbit transition,the satellite to use the Separate Propulsion System for orbit raising,after completing the task,it can be thrown away.Due to the short working time in orbit,the Separate Propulsion System adopts a low-cost design.This scheme presents a scheme of using Separate Propulsion System for orbit control and an autonomous departure after separation from satellite.This scheme reduces the dead weight brought by the Separate Propulsion System,reduces the time of orbit raising by electric propulsion,and reduces the consumption of xenon propellant,it has great advantages in improving the capacity and the service life of satellite.

关 键 词：全电推进 可分离推进舱 轨道控制 

分 类 号：V44[航空宇航科学与技术—飞行器设计]