任琼英, 葛丽丽, 郑慧奇, 等. 超低轨吸气式螺旋波电推进概念研究[J]. 航天器环境工程, 2020, 37(1): 17-24 DOI: 10.12126/see.2020.01.003
引用本文: 任琼英, 葛丽丽, 郑慧奇, 等. 超低轨吸气式螺旋波电推进概念研究[J]. 航天器环境工程, 2020, 37(1): 17-24 DOI: 10.12126/see.2020.01.003
REN Q Y, GE L L, ZHENG H Q, et al. The concept study of an air-breathing helicon thruster used in ultra-low orbit flight[J]. Spacecraft Environment Engineering, 2020, 37(1): 17-24 DOI: 10.12126/see.2020.01.003
Citation: REN Q Y, GE L L, ZHENG H Q, et al. The concept study of an air-breathing helicon thruster used in ultra-low orbit flight[J]. Spacecraft Environment Engineering, 2020, 37(1): 17-24 DOI: 10.12126/see.2020.01.003

超低轨吸气式螺旋波电推进概念研究

The concept study of air-breathing helicon thruster used in ultra-low orbit flight

  • 摘要: 文章提出一种超低轨卫星飞行轨道维持新概念——吸气式螺旋波电推进技术,将轨道残余大气作为螺旋波电离的工质,通过螺旋波加速电子形成的电双层加速离子产生推力,维持卫星在超低(180~260 km)轨道的长时间运行。吸气式螺旋波电推进的核心技术是采用收缩进气道与螺旋波电推进一体化结构,利用螺旋波电离产生的前向逃逸等离子体在进气道中形成预电离鞘层区,部分电离气体的密度扰动以离子声速向下游传播,导致进气道内不再出现激波界间断面,进入收缩进气道的气体被高效收集到螺旋波电离放电管,电离加速形成推力,来维持超低轨卫星的长时间在轨运行。

     

    Abstract: The atmospheric air drag in an ultra-low orbit (180-260 km) is one of the main factors that might shorten the life of a spacecraft in the orbit. A concept of the air-breathing helicon thruster (ABHT) onboard of a spacecraft for the ultra-low orbit long term maintenance is reviewed in this study. A contractive-shaped air inlet channel compacts well directly with an electrodeless helicon wave discharge tube. The inlet air blows onto the front window of the channel with an initial velocity of 7800 ms-1 relative to the spacecraft, and the inlet air is compressed as the flow moving into the rear port of the contractive-shaped channel, and the flow velocity is decelerated, due to the collisions of the inlet particles with the channel wall. A pre-discharge sheath is set up in the rear port of the channel, with the upward leakage of the plasma generated in the discharge tube by helicon waves. The discharge rate of the pre-discharge sheath is assumed to be about 10%, and the electron temperature is about 10 eV, and the ion temperature, 0.2-0.3 eV. The existence of a pre-discharge sheath in the rear port of the channel makes the air density disturbance propagating downstream the channel with the velocity of the ion acoustic speed. The ion acoustic velocity in the pre-discharge sheath is larger than that of the gas flow velocity in the inlet channel, which is assumed to be 2000 ms-1, and the inlet air will not be choked in the rear port of the contractive-shaped channel. The subsequent inlet gas molecules will not be reflected back from the channel to the atmosphere surround the spacecraft. Almost all molecules in the inlet go into the contractive-shaped channel, and then the tube, and are discharged and accelerated backward by the helicon plasma thruster at a larger directional velocity, a propulsion is thus generated enough to maintain the long-term operation of an ultra-low-orbit satellite.

     

/

返回文章
返回