AbstractThe paper presents the results of the first experiments on the implementation of the concept of electric propulsion thrusters that u'/> Development of the Radio-Frequency Ion Thruster on Atmospheric Gases
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Development of the Radio-Frequency Ion Thruster on Atmospheric Gases

机译：大气中射频离子推进器的研制

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AbstractThe paper presents the results of the first experiments on the implementation of the concept of electric propulsion thrusters that use atmospheric gases as propellant. Such thrusters can be used to create propulsion systems for small, low-orbit (180–240 km) spacecraft. For experimental studies, a radio-frequency ion thruster was selected, and a laboratory sample of the thruster with an output beam diameter ofd= 150 mm was developed. Experiments were carried out in which dependences of the propellant mass flow on the power delivered to the thruster’s inductor were obtained (for each dependence, the ion beam current was maintained at the same level). Dependences were obtained when the laboratory sample of the radio-frequency ion thruster operated on xenon, nitrogen, and oxygen. Characteristics and estimations of some integral parameters of the thruster are given.
机译： Abstract 本文介绍了首次实施以大气气体作为推进剂的电动推进器概念的实验结果。这种推进器可用于为小型低轨道（180-240 km）航天器建立推进系统。为了进行实验研究，选择了射频离子推进器，并开发了输出束直径 d = 150 mm的推进器实验室样品。进行了实验，获得了推进剂质量流量对传递到推进器感应器的功率的依赖性（对于每种依赖性，离子束电流都保持在同一水平）。当射频离子推进器的实验室样品在氙气，氮气和氧气上运行时，就具有依赖性。给出了推进器某些积分参数的特性和估计。

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