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.
出处
《宇航学报》
EI
CAS
CSCD
北大核心
2010年第1期173-178,共6页
Journal of Astronautics
关键词
小卫星
冷气推进
推进剂
有效比冲
微推力器
Small satellite
Cold gas propulsion system
Propellant
Effective specific impulse
Micro thruster
