航天器工程2025，Vol.34Issue(1)：32-37,6.DOI:10.3969/j.issn.1673-8748.2025.01.006
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
彭坤 1魏强 1王敏 1熊晓将 1王珏 1梁新刚1
作者信息
- 1. 中国空间技术研究院通信与导航卫星总体部,北京 100094
- 折叠
摘要
Abstract
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 struc-tural 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 avoi-ded;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,lim-ited 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Key words
APSTAR-6E satellite/separable design/propulsion module分类
航空航天引用本文复制引用
彭坤,魏强,王敏,熊晓将,王珏,梁新刚..亚太6E卫星可分离独立推进舱设计[J].航天器工程,2025,34(1):32-37,6.
