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首页> 外文期刊>Journal of Spacecraft and Rockets >Atmospheric Electric Propulsion Mission Performance Tool
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Atmospheric Electric Propulsion Mission Performance Tool

机译：大气电动推进任务执行工具

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摘要

The amount of available propellant limits low-Earth orbit satellite lifetime due to the necessity of drag makeup. An electric propulsion device that uses in situ ions as propellants is considered as an alternative method for satellite drag makeup. This work presents a tool that consists of a one-dimensional thruster mathematical model integrated with the NASA International Reference Ionosphere to provide ion and neutral species densities for an electrostatic electric propulsion approach. This mathematical model predicts thrust, drag, and thruster power. The thrust-to-drag ratio and thruster power are averaged over the entire mission duration of one year and compared with various circular orbits and satellite configurations: 300-1000 km orbit altitude, 0-60 deg orbit inclination, low to high solar activity, 0.1-5.0 m~2 satellite frontal area, 1-10 kV acceleration voltage, and 1-10 m~2 total grid area. The Satellite Tool Kit provides orbit propagation. An average thrust-to-drag ratio greater than one is achievable for many thruster and orbit configurations considered in this analysis, at power levels less than 90 W. Most satellite missions at altitudes of less than 400 km may fall into the region in which the thrust-to-drag ratio is less than one. Thrust-to-drag ratio values of less than one will still benefit satellites by extending mission lifetimes for months or years with average power requirements less than 100 W.
机译：由于必须进行补给，可利用的推进剂数量限制了低地球轨道卫星的寿命。使用原位离子作为推进剂的电动推进装置被认为是卫星阻力补给的替代方法。这项工作提出了一种工具，该工具由与NASA国际参考电离层集成的一维推进器数学模型组成，可为静电推进方法提供离子和中性物质密度。该数学模型可预测推力，阻力和推力。在一年的整个任务期间，将推力比和推力功率进行平均，并与各种圆形轨道和卫星配置进行比较：300-1000公里的轨道高度，0-60度的轨道倾角，低到高太阳活动，卫星正面面积为0.1-5.0 m〜2，加速电压为1-10 kV，网格总面积为1-10 m〜2。卫星工具套件提供轨道传播。在此分析中考虑的许多推进器和轨道配置​​中，功率水平小于90 W时，平均推力/阻力比可以达到大于1的水平。大多数低于400 km的卫星任务可能会落入该区域。推力/阻力比小于1。推力/拖曳比值小于1仍将通过使任务寿命延长数月或数年（平均功率要求小于100 W）使卫星受​​益。

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  • 来源
    《Journal of Spacecraft and Rockets》 |2014年第3期|931-937|共7页
  • 作者

    Scott T. King; Mitchell L. R. Walker; Silvio G. Chianese;

  • 作者单位

    Georgia Institute of Technology, Atlanta, Georgia 30332;

    Georgia Institute of Technology, Atlanta, Georgia 30332;

    Northrop Grumman Corporation, Redondo Beach, California 90278;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
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