一种直接入轨卫星变轨阶段的供电方案  

A Power Supply Scheme for Direct Injection Satellite at Orbital Transfer Phase

作　　者：张明[1] 曾毅[1] 刘奕宏[1] 鲍恩竹[1] 

机构地区：[1]北京空间飞行器总体设计部,北京100094

出　　处：《航天器工程》2014年第1期63-68,共6页Spacecraft Engineering

基　　金：国家重大航天工程

摘　　要：相比传统的卫星自身变轨方式,直接入轨方式下卫星的主动段时间将延长到4~5h。为解决卫星直接入轨过程中由于主动段时间大大加长,导致卫星电能需求的增加,以及电源系统配置不必要的质量增加的问题,文章提出了一种在发射和变轨阶段通过运载火箭上面级向卫星供电的方案,即在上面级上增加了一套独立的一次性电源系统。该系统与卫星自身电源系统相结合,在发射和变轨期间优先使用,卫星自身电源根据负载用电情况自主介入,能很好地解决卫星直接入轨方式下主动段的电能需求问题。Compared with the traditional self-maneuvering, the active-stage time for direct injec- tion will prolong about 4 to 5 hours, which will further burden on the satellite electrical power system. In order to solve the problem without increasing the system weight, this paper proposes a new design scheme, which supplies power for satellite by using the upper stage at launching and active-maneuvering phases. An independent power supply is added in upper stage rocket to sup- port satellite primary bus. Associated with the satellite self-power, the scheme can realize the mode-switch among the upper stage rocket supplying, the ground power system supplying and the satellite self-supplying. During the launching and active-maneuvering, the satellite is powered by the upper stage in preference, and the power of satellite intervenes autonomously accordance with the payload^s energy demand,so this scheme can solve the power problems effectively at the active-maneuvering when the satellites are directly injected.

关 键 词：直接入轨卫星 变轨阶段 供电方案 上面级 

分 类 号：V412.41[航空宇航科学与技术—航空宇航推进理论与工程] V442