基于有效比冲的小卫星冷气推进系统设计  

Design of the Cold Gas Propulsion System for a Small Satellite Based on Effective Specific Impulse

作　　者：周伟勇[1] 张育林[1] 

机构地区：[1]国防科学技术大学航天与材料工程学院,长沙410073

出　　处：《宇航学报》2010年第1期173-178,共6页Journal of Astronautics

摘　　要：提出了面向目标任务的小卫星冷气推进系统设计方法。应用有效比冲作为小卫星推进系统的评价指标,将贮箱质量引入到常用冷气推进剂选择标准中,建立了面向目标任务的冷气推进方案设计方法;推导了冷气微推力器的一般设计流程;最后,对某目标任务,设计了推力为20mN的氮气推进系统。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 20raN was designed by the proposed methods.

关 键 词：小卫星 冷气推进 推进剂 有效比冲 微推力器 

分 类 号：V434.1[航空宇航科学与技术—航空宇航推进理论与工程]