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Ionic Liquid Dual-Mode Spacecraft Propulsion Assessment

机译：离子液体双模式航天器推进力评估

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摘要

Analytical and numerical investigations of the performance of a series of potential dual-mode propulsion systems using ionic liquids are presented. A comparison of the predicted specific impulse of ionic liquids with hydrazine and unsymmetrical dimethylhydrazine shows that ionic liquid fuels have a 3-12% lower specific impulse when paired with a nitrogen tetroxide oxidizer. However, when paired with hydroxylammonium nitrate oxidizer, the specific impulse of the ionic liquids is 1-4% lower than that of hydrazine and unsymmetrical dimethylhydrazine paired with nitrogen tetroxide. Analytical investigation of an electrospray electric propulsion system shows that ion extraction in the pure ion regime provides a very high specific impulse, outside the optimum range for potential missions. Results suggest a deceleration grid, a lower ion fraction, or emission of higher solvated states is required. Analysis of a dual-mode ionic-liquid-propelled spacecraft shows that the electric propulsion component determines the overall feasibility compared with current technology. Results indicate that the specific power for an ionic liquid electrospray system must be at least 15 W/kg in order for a dual-mode ionic liquid system to compete with traditional hydrazine and Hall thruster technology.
机译：提出了一系列使用离子液体的潜在双模推进系统性能的分析和数值研究。预测的离子液体与肼和不对称的二甲基肼的比冲的比较表明，与四氧化氮氧化剂配对时，离子液体燃料的比冲降低了3-12％。但是，与硝酸羟铵氧化剂配对时，离子液体的比冲比与四氧化二氮配对的肼和不对称二甲基肼的比冲低1-4％。对电喷雾电推进系统的分析研究表明，纯离子状态下的离子提取提供了非常高的比冲，超出了潜在任务的最佳范围。结果表明需要减速栅，较低的离子分数或较高的溶剂化态发射。对双模离子液体推进航天器的分析表明，与现有技术相比，电推进组件决定了总体可行性。结果表明，离子液体电喷雾系统的比功率必须至少为15 W / kg，才能使双模离子液体系统与传统的肼和霍尔推力器技术竞争。

著录项

  • 来源
    《Journal of Spacecraft and Rockets》 |2011年第1期|p.110-123|共14页
  • 作者

    Brian R. Donius; Joshua L. Rovey;

  • 作者单位

    Missouri University of Science and Technology, Rolla, Missouri 65409;

    Missouri University of Science and Technology, Rolla, Missouri 65409;

  • 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
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