Design of the cold gas propulsion system for a small satellite based on effective specific impulse

被引：0

作者：

Zhou W.-Y. ^{[1
]}

Zhang Y.-L. ^{[1
]}

机构：

[1] Inst. of Aerospace and Material Engineering, National Univ. of Defense Technology

来源：

Yuhang Xuebao/Journal of Astronautics | 2010年 / 31卷 / 01期

关键词：

Cold gas propulsion system; Effective specific impulse; Micro thruster; Propellant; Small satellite;

D O I：

10.3873/j.issn.1000-1328.2010.01.028

中图分类号：

学科分类号：

摘要：

This paper presents the design of the cold gas propulsion system for a small satellite. The suitable propellant for a certain mission was selected from the commonly used cold gas propellants, using the estimate target of effective specific impulse, in which the mass of the tank was considered. Then, the basic design of the micro thruster was conducted. In the end, a cold nitrogen gas propulsion system with the micro thruster of 20 mN was designed by the proposed methods.

引用

页码：173 / 178

页数：5

共 7 条

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