Spacecraft correcting propulsion system has a solid working medium, two working channels, cathodes and anodes, an end insulator
	ISAEV V I; GLUKHOV V I; LAZAREV A N; SOLOVYOV M M
	2024-03-19
专利权人	ELECTROMECHANICS SCI RES INST (ELEC-Non-standard)
申请日期	2024-03-19
专利号	RU2830581-C1
成果简介	NOVELTY - Invention relates to space engineering, particularly to low-thrust plasma engines. Correcting ablation propulsion system of the spacecraft comprises a solid working medium, two working channels, cathodes and anodes, an end insulator, dielectric blocks, an energy accumulation unit and two electric discharge initiation units, a control system and a voltage converter. Electric discharge initiation units consist of a resistor, a capacitor, a controlled switch and a pulse transformer. USE - Cosmonautics. ADVANTAGE - Increasing the reliability of the plasma correcting propulsion system of a spacecraft. 1 cl, 2 dwg
IPC 分类号	B64G-001/26 ; F03H-001/00
国家	俄罗斯
专业领域	信息技术
语种	英语
成果类型	专利
文献类型	科技成果
条目标识符	http://119.78.100.226:8889/handle/3KE4DYBR/17647
专题	中国科学院新疆生态与地理研究所
作者单位	ELECTROMECHANICS SCI RES INST (ELEC-Non-standard)
推荐引用方式 GB/T 7714	ISAEV V I,GLUKHOV V I,LAZAREV A N,et al. Spacecraft correcting propulsion system has a solid working medium, two working channels, cathodes and anodes, an end insulator. RU2830581-C1[P]. 2024.

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