基于环境工质的超低轨吸气式螺旋波电推进器仿真分析  

Numerical simulation of air-breathing helicon plasma thruster based on propellant in ultra-low orbit

作　　者：丁亮[1] 彭毓川 郑慧奇[1] 唐振宇[1] 任琼英[1] 赵华[1] 秦玮[1] DING Liang;PENG Yuchuan;ZHENG Huiqi;TANG Zhenyu;REN Qiongying;ZHAO Hua;QIN Wei(Beijing Institute of Spacecraft Environment Engineering,Beijing 100094,China)

机构地区：[1]北京卫星环境工程研究所,北京100094

出　　处：《航天器环境工程》2020年第4期330-335,共6页Spacecraft Environment Engineering

基　　金：装备预研领域基金项目(编号:61402060501);载人航天领域第四批技术预先研究项目(编号:010202)。

摘　　要：为考察超低轨道高度环境下吸气式螺旋波电推进的可行性,基于180 km超低轨道高度环境工质,开展吸气式螺旋波电推进器的仿真模拟。进行以原子氧为工质,综合考虑碰撞、激发、电离等过程,通过13.56 MHz射频加热,由磁喷口完成推力输出全流程的仿真模拟。建立特定形态吸气式螺旋波电推进结构模型,结合不同功率的输入,分析功率沉积、等离子体参数分布和推力输出。结果表明,输入功率从200 W增加至2000 W的过程中,推力从6.00 mN增加至13.23 mN,能够满足0.226 mN的阻力补偿要求,可为超低轨吸气式电推进航天器设计提供参考。To investigate the feasibility of the air-breathing helicon plasma thruster,such a thruster is numerically simulated based on the propellant in the 180 km ultra-low orbit,with consideration of the collision,the excitation and the ionization processes.The propellant,composed mostly of atom oxygen,is absorbed and heated by the electromagnetic wave with a radio frequency of 13.56 MHz,and eventually ejected from the magnetic nozzle.A structure model of the air-breathing helicon plasma thruster is established.The deposited power,the distributed plasma parameters and the thrust output are calculated for various input powers.It is shown that with the input power increased from 200 W to 2000 W,the thrust increases from 6.00 mN to 13.23 mN,enough to compensate the atmospheric resistance.The result can be used in the design of this kind of thrusters.

关 键 词：吸气式螺旋波推力器 电推进 超低轨 仿真分析 

分 类 号：V439.3[航空宇航科学与技术—航空宇航推进理论与工程] V237