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Advancements in the Demonstration of High Thrust to Power Ion Engine Technology

机译：动力离子发动机技术高推力演示的进展

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摘要

Gridded ion thrusters provide excellent thruster performance and have successfully been implemented on both geocentric and heliocentric missions. While ion thrusters have a substantial number of attractive technological attributes, they are often classified as inherently low thrust density devices. This manuscript details an ongoing collaborative effort among the NASA Glenn Research Center, the University of Michigan, and The Aerospace Corporation investigating ion engine design modifications for high thrust-density/high thrust-to-power operation. Measurements were performed at The Aerospace Corporation in a 2.4-m diameter × 9.8-m long cryopumped vacuum chamber on an engineering model NEXT engine with a reduced interelectrode gap. The perveance, discharge losses, and far-field current density were characterized at operating conditions consistent with high thrust-to-power operation. The total voltage needed to achieve a given beam current was reduced by a factor of 10% with the reduced grid-gap optics, which is in close agreement with the Child Lang-muir equation. The thrust loss correction factor ranged from 0.961 to 0.979 and was consistently higher than the predicted values. The discharge losses decreased with increasing beam current, with a minimum value of 150 W/A at a beam current of 5.50 A.
机译：网格离子推进器具有出色的推进器性能，并已成功用于地心和日心任务。尽管离子推进器具有大量吸引人的技术属性，但它们通常被归类为固有的低推力密度设备。该手稿详细介绍了美国宇航局格伦研究中心，密歇根大学和航空航天公司之间正在进行的合作努力，该研究正在研究用于高推力密度/高推力动力运行的离子发动机设计修改。测量是在The Aerospace Corporation在直径为2.4 m×9.8 m长的低温泵真空室中使用工程模型NEXT发动机进行的，电极间间隙减小了。在与高推力运行相符的运行条件下表征了导通，放电损耗和远场电流密度。减小的栅隙光学器件可以使达到给定束电流所需的总电压降低10％，这与Child Lang-muir方程非常吻合。推力损失校正系数在0.961至0.979的范围内，始终高于预测值。放电损耗随着束电流的增加而降低，在束电流为5.50 A时最小值为150 W / A。

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