国外微纳卫星无推进离轨技术研究  

Typical De-orbit Concepts Adopted by Foreign Micro-satellites

作　　者：朱鲁青[1] 孙琳 范嵬娜[1] ZHU Lu-qing;SUN Lin;FAN Wei-na(Beijing Institute of Space Science and Technology Information, Beijing 100086, China)

机构地区：[1]北京空间科技信息研究所

出　　处：《空间碎片研究》2017年第3期35-39,共5页Space Debris Research

摘　　要：近年来由于微纳卫星发射数量急剧增加造成的空间碎片问题引起了广泛的关注。为满足微纳卫星任务结束后25年离轨的碎片减缓指南要求,必须采取必要的离轨措施。微纳卫星由于质量和成本限制,通常采用无动力被动离轨技术,包括电动系绳,太阳帆、机械增阻装置等。本文对国外微纳卫星采用的典型离轨方案进行了分析,以加拿大CanX-7纳卫星离轨任务、日本Tohoku大学开发的阻力帆离轨方案、美国CTD公司研发的卷出离轨系统(RODEO)为例进行了详细介绍,认为机械展开的阻力帆技术适用于快速响应、任务周期短的低轨微纳卫星。In recent years, the problem of space debris caused by the sharp increase in the number of microsatellite satellites has attracted wide attention. In order to meet the requirements of the debris mitigation guidelines, the necessary de-orbit measures must be taken for micro-nano satellites. Due to the quality and power constraints, the passive de-orbit technology are usually used for the micro-nano satellites, including electric tethers, solar sails, drag sail devices. In this paper, the typical de-orbit concepts adopted by foreign micro-satellites were introduced. It was concluded that a mechanically deployed drag sail is the most promising option for LEO micro-nano satellites.

关 键 词：离轨技术 阻力帆 被动离轨 无动力 微纳卫星 

分 类 号：V412[航空宇航科学与技术—航空宇航推进理论与工程]