CAJ | 학술논문

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.
제출료면향목표임무적소위성랭기추진계통설계방법.응용유효비충작위소위성추진계통적평개지표,장저상질량인입도상용랭기추진제선택표준중,건립료면향목표임무적랭기추진방안설계방법;추도료랭기미추력기적일반설계류정;최후,대모목표임무,설계료추력위20mN적담기추진계통.
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 20mN was designed by the proposed methods.