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Information × Registration Number 0217U003418, 0116U002663 , R & D reports Title Study of features and mechanisms for the control of spacecraft orbital motion in a conducting medium. Stage 4 - "Analysis of the features of the methods proposed for control of spacecraft orbital motion in a conductive medium" popup.stage_title Head Shuvalov Valentyn Oleksievych; Alpatov Anatoliy Petrovych, Registration Date 11-04-2017 Organization The Institute of Technical Mechanics of the National Academy of Sciences of Ukraine and the State Space Agency of Ukraine popup.description2 The research subjects are a magnetized rigid body in a supersonic flow of a rarefied plasma (line 1) and the dynamics of electrodynamic space tether system (line 2). The research objectives are to validate the efficiency of magnetohydrodynamic systems for controlling dynamic interactions and the spacecraft motion in the Earth ionosphere and interplanetary space (line 1), and to determine a possibility of creating a high-efficient passive device with low mass and power, based on a electrodynamic space tether system, for resolving the problem of space debris removal from LEO (line 2). The research methods: experimental and theoretical ones (line1); information and analytical ones, theoretical mechanics, mechanics of space flight, physics of ionized plasma, theory of probability, mathematical modeling, and computer visualization, theory of heat conduction (line 2). The results obtained (line 1). The study shows that a magnetohydrodynamic interaction of magnetized spacecraft entering the Earth dense atmosphere by a magnetic parachute results in two effects:a decrease in a convective heat flow by 60% at a critical point of a blunted surface of the rigid body and more 80% in the periphery section of the rigid body; the body acceleration using its magnetic field. Basic regularities of a dynamic interaction between the magnetized spacecraft and a rarified plasma are first studied simulating the spacecraft motion in the ionosphere plasma at speeds from 800km to 1000km and in the solar wind plasma. It is demonstrated that the plasma injection into the cavity of the mini-magnetosphere can increase the resistance force (thrust) 2-3 times in comparison with the empty mini-magnetosphere. The use as a whole of the mini-magnetosphere can increase the spacecraft resistance force (thrust) 7-10 times in comparison with the unmagnetized spacecraft through flow of a rarified plasma. Line 2: mathematical models of the dynamics of an electrodynamic space tether system are analyzed, built, and in progress to determine a possibility of creating a high-efficient device for passive removal of space debris from LEO. Basic special features of the dynamics of the electrodynamic space tether system in LEO are analyzed, and recommendations are made to calculate force interactions between a small experimental space tether system and the environment and the dynamics of the system. The study shows that special features of interactions between the electrodynamic space tether system and the environment and its dynamics require full-scale testing. Recommendations for deploying a small experimental space tether system are made, and the results of studies in special factors of interactions between the system and the environment are generalized. Applications: fluid mechanics, plasma electrodynamics, spacecraft design (line 1); space studies, dynamics of space systems (line 2). Product Description popup.authors Алпатов А.П. Волошенюк О.Л. Кочубей Г.С. Кулагін С.М. Кучугурний Ю.П. Носіков С.В. Пироженко О.В. Письменний М.І. Пурцеладзе А.А. Різниченко М.П. Токмак М.А. Храмов Д.О. Шувалов В.О. Шупілова Л.М. popup.nrat_date 2020-04-02 Close