A. E. Solodukhin | AMiner学者主页

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20212023

论文（10）

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1About Development Feasibility of a High Specific Impulse Thruster with Closed Electron Drift

L. E. Zakharenkov,A. V. Semenkin,A. E. Solodukhin

2023AIP Conference Proceedings XLV ACADEMIC SPACE CONFERENCE, DEDICATED TO THE MEMORY OF ACADEMICIAN SP ...（2023）

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2Application of High Power Level Power and Propulsion Systems for Space Transportation

V.V. Koshlakov,N.I. Arkhangelsky,L.E. Zakharenkov, A.V. Karevskiy,E.Yu. Kuvshinova,E.I. Muzychenko,A.V. Semenkin,A.E. Solodukhin

The purpose of the research was to consider the application of high power level power and propulsion systems for different space missions. The paper gives the main components of high power level nuclear power and propulsion systems as well as their architecture options and integration solutions. Within the research, we set requirements to characteristics of high power level power and propulsion systems of advanced spacecraft aimed for different transport missions in near-Earth and deep space, analyzed efficiency of nuclear power and propulsion systems applied for transport missions in comparison with conventional chemical propulsion systems. Findings of the research show that high power level power and propulsion systems have the following advantages in comparison with conventional chemical propulsion systems: increase of payload mass; possibility of direct flights (without gravitational maneuvers) to deep space objects; ensuring power supply of target equipment and communication systems at a qualitatively higher level.

2022Engineering Journal Science and Innovation（2022）

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3Service Systems of Small Spacecrafts

A. A. Gafarov, A. Drondin,L. E. Zakharenkov, A. G. Klimenko,D. A. Kravchenko, A. S. Kudinov,A. S. Lovtsov, Yu M. Lukoyanov, I. S. Ogloblina, A. Semenkin, V. V. Sobolev,A. E. Solodukhin,

This paper considers specifics of small spacecrafts for multi-satellite orbital groups for communication and Earth remote sensing (ERS). The analysis of requirements to service systems of small spacecrafts, namely, propulsion systems, power systems, and thermal control systems, is conducted. The paper reviews the main components and high readiness technologies of service systems.

2021XLIV ACADEMIC SPACE CONFERENCE DEDICATED TO THE MEMORY OF ACADEMICIAN SP KOROLEV AND OTHER OUTSTANDI...（2021）引用：1

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4Some Radiation Safety and Insurance Issues for Nuclear Spacecraft

A. V. Semenkin, A. A. Gafarov,A. E. Solodukhin, A. A. Koroteeva

Some issues concerning the prevention of dangerous radiation exposure of the general public and providing insurance for spacecraft with next-generation nuclear reactors are examined. It is shown that the technical and organizational measures to meet the requirements of international and Russian documents will secure radiation safety for the general public when using spacecraft with nuclear reactors, including during emergency situations. Insurance companies that insure rocket and space as well as nuclear technology can insure all risks of space activity associated with nuclear-powered spacecraft.

2020Atomic Energy（2020）

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5Совместное Функционирование Электроракетных Двигателей И Системы Газотурбинного Преобразования Энергии В Составе Энергодвигательной Установки Космического Назначения

А. С. Коротеев, К. В. Готовцев,Л. Э. Захаренков, А. В. Каревский,А. С. Ловцов, Ю. А. Ошев, М. Ю. Селиванов,А. В. Семенкин,А. Е. Солодухин

2020Известия Российской академии наук Энергетика

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6Features of Construction and Possible Use of Powerful Nuclear Power Plants of Advanced Spacecraft

V.N. Akimov,L.E. Zakharenkov, A.V. Karevskiy,E.Yu. Kuvshinova,A.V. Semenkin,A.E. Solodukhin

The purpose of the study was to examine the use of spacecraft based on a nuclear power propulsion system in performing long-term tasks in space. The system uses a nuclear power plant to generate electrical energy, and electric propulsion engines to create thrust and control the apparatus. The study shows the advantages of using nuclear power plants when organizing missions in the near and outer space. First, we formulate the requirements for the characteristics of spacecraft with a nuclear power plant designed to perform various missions. Then, we consider the composition and principle of operation of a nuclear power plant and assess the effectiveness of the use of a space tug on the basis of a powerful nuclear power unit when solving problems of cargo transportation in space. Finally, we give recommendations for the construction, control algorithms and experimental development of a nuclear power plant.

2019Engineering Journal Science and Innovation（2019）引用：2

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7Space Power Propulsion Systems with Gas Turbine Power Conversion System of Closed Brayton Cycle of High Power and Characteristic Features of Their Experimental Testing

Д.И. Андрианов,Л.Э. Захаренков, А.В. Каревский, А.Вл. Попов, С.А. Попов, А.В. Семёнкин,А.Е. Солодухин, Д.Н. Терехов, С.Ю. Штонда

Приведены данные об актуальных в настоящее время проектах, ведущихся в мире в области мощных ядерных энергодвигательных установок (ЭДУ

2016Engineering Journal Science and Innovation（2016）引用：4

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8Concept of Electric Propulsion Realization for High Power Space Tug

L. E. Zakharenkov,A. V. Semenkin,A. E. Solodukhin

Popular at the beginning of the Space Age, ambitious projects aimed at Moon, Mars, and other space objects exploration, have returned with new technology and design level. High power space tug with electric propulsion system (EPS) is mainly considered as a transport vehicle for such missions. Modern high power space tugs projects as well as their spacecraft (SC) power and propulsion systems are reviewed in the paper. The main technologies and design solutions needed for high-power EPS realization are considered.

2016Progress in Propulsion Physics引用：7

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9Evaluation of Impurity Composition and Content in the TAL at Various Operating Regimes

G. F. Karabadzhak,A. V. Semenkin,A. E. Solodukhin,O. S. Tverdokhlebov

The paper is dedicated to development and validation of a real time optical diagnostic method for monitoring of the Hall effect thruster erosion rate variation from one operating regime to another. A convenient semi-empirical formula has been utilized for relation of the thruster erosion rate with intensities of the impurity and xenon emissions. The formula was verified in a number of dedicated experiments. In particular, the erosion rate predictions based on the optical diagnostic data were compared with results of the thruster ware tests. Good agreement has been found. Additional verification of the method was achieved through measurements of variation of the erosion rate coefficient of metallic samples placed inside the ionic beam in the Hall thruster plume. The method was found to be appropriate for measuring of the erosion rate variation in a wide range of the thruster operating parameters. However, some limitations of the method have been manifested. In particular, evaluation of the erosion rate variation becomes less accurate, when electron temperature in the thruster plasma varies from one operating regime to another. In this case formula for the erosion rate variation must be generalized to include dependence of the emission excitation functions on the electron temperature.

2005引用：27

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10Parameters of D80 Anode Layer Thruster in One-and Two-Stage Operation Modes

A. E. Solodukhin,A. V. Semenkin, S. O. Tverdohlebov, A. V. Kochergin

Oneand Two-stage modes of TAL D-80 are studied in detail. Optimal discharge (first stage) voltage from the thruster efficiency and the ion current fluctuation level point of view in Twostage mode has been determined. The thruster efficiency and ion current fluctuation level in Oneand Two-stage modes have been compared and the areas of preferable One-stage mode and Two-stage mode application have been found.

2001引用：4

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