亚太6E卫星独立推进舱化学推进分系统设计与验证  

Design and Verification of Chemical Propulsion Subsystem for Independent Propellant Module of APSTAR-6E Satellite

作　　者：郭蕾 李文[1] 陈上通 GUO Lei;LI Wen;CHEN Shangtong(Beijing Institute of Control Engineering,Beijing 100094,China)

机构地区：[1]北京控制工程研究所,北京100094

出　　处：《航天器工程》2025年第1期101-104,共4页Spacecraft Engineering

摘　　要：亚太6E卫星独立推进舱采用双组元推进系统,用于完成亚太6E卫星由星箭分离轨道至中间轨道的轨道转移。文章介绍了独立推进舱化学推进分系统在配置、工作方式、平衡排放等方面的设计。针对亚太6E卫星化学推进分系统任务特点,在传统化学推进分系统配置的基础上进行简化,同时考虑整星姿态稳定及独立推进舱与主星分离的安全性,进行并联贮箱的平衡排放设计与控制。最后,通过在轨应用验证了设计的可行性和正确性。The independent propellant module of the APSTAR-6E satellite adopts a dual-component propulsion system,which is used to complete the orbital transfer of the satellite from the separation orbit to the intermediate orbit.The configuration,working mode and balanced discharge designs of chemical propulsion subsystem for independent propellant module are introduced in the paper.In view of the mission characteristics of the satellite chemical propulsion subsystem,the simplification is considered based on the traditional configuration of the chemical propulsion subsystem,the balanced emission design and the control of the parallel tanks are carried out in order to maintain the attitude of the whole satellite and the safety of the separation of the independent propellant module and the main satellite.Finally,the feasibility and correctness of the design are verified by the in-orbit application.

关 键 词：亚太6E卫星 独立推进舱 化学推进分系统 

分 类 号：V43[航空宇航科学与技术—航空宇航推进理论与工程]