亚太6E卫星可分离独立推进舱设计  

Design of Separable Independent Propulsion Module for APSTAR-6E Satellite

作　　者：彭坤[1] 魏强[1] 王敏[1] 熊晓将[1] 王珏[1] 梁新刚[1] PENG Kun;WEI Qiang;WANG Min;XIONG Xiaojiang;WANG Jue;LIANG Xin’gang(Institute of Telecommunication and Navigation Satellites,China Academy of Space Technology,Beijing 100094,China)

机构地区：[1]中国空间技术研究院通信与导航卫星总体部,北京100094

出　　处：《航天器工程》2025年第1期32-37,共6页Spacecraft Engineering

摘　　要：针对低成本发射GEO卫星的需求,开展了可分离独立推进舱的设计,包括功能配置和结构布局设计、连接与分离机构设计、化学推进设计、控制系统设计、供配电设计和热控设计。该设计通过共享卫星资源,采用简化配置,节省了成本;通过化学推进快速提升轨道,避免了与低轨飞行器的碰撞风险;通过自主姿轨控设计,降低了对测控资源的需求;通过推进舱助力变轨且可分离设计,减少了后续卫星变轨的负荷,提高了变轨效率。这种设计解决了由于采用小火箭入轨低带来的升轨过程中的碰撞风险高、地面测控覆盖少、卫星变轨时间长等难题,提供了一种低成本发射GEO卫星的成功案例。In response to the needs for low-cost launch of GEO satellites,the design of separable independent propulsion module has been carried out,including functional configuration and structural layout design,connection and separation mechanism design,chemical propulsion design,control system design,power supply and distribution design,and thermal design.This design saves costs by sharing satellite resources and adopting simplified configuration.By using chemical propulsion to rapid elevate the orbit,the risk of collision with low-orbit spacecraft has been avoided;By designing the autonomous attitude and orbit control,the demand for measurement and control resources has been reduced;By using a propulsion module to assist in orbit change and a separable design,the load of subsequent satellite orbit change has been reduced and the orbit change efficiency has been improved.This design solves the problems of high collision risk,limited ground TT&C coverage,and long satellite orbit transfer time caused by the use of small rockets for low orbit entry,and provides a successful case of low-cost launch of GEO satellites.

关 键 词：亚太6E卫星 可分离设计 推进舱 

分 类 号：V475[航空宇航科学与技术—飞行器设计]