The Experts below are selected from a list of 261 Experts worldwide ranked by ideXlab platform
Marianne Balatpichelin - One of the best experts on this subject based on the ideXlab platform.
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thermal radiative properties of carbon materials under high temperature and vacuum ultra violet vuv radiation for the Heat Shield of the solar probe plus mission
Applied Surface Science, 2012Co-Authors: Marianne Balatpichelin, J Eck, Jeanlouis SansAbstract:Abstract The Solar Probe Plus (SP+) mission will approach the Sun as close as 9.5 solar radii in order to understand the origin of the solar corona Heating and the acceleration of the solar wind. Submitted to such extreme environmental conditions, a thermal protection system is considered to protect the payload of the SP+ spacecraft. Carbon-based materials are good candidate to fulfill this role and critical point remains the equilibrium temperature reached at perihelion by the Heat Shield. In this paper, experimental results obtained for the solar absorptivity α, the total hemispherical emissivity ɛ and its ratio α/ɛ, conditioning the equilibrium temperature of the thermal protection system, are presented for different kinds of carbon materials Heated at high temperatures with or without vacuum-UV (100
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experimental study of carbon materials behavior under high temperature and vuv radiation application to solar probe Heat Shield
Applied Surface Science, 2011Co-Authors: J Eck, Jeanlouis Sans, Marianne BalatpichelinAbstract:Abstract The aim of the Solar Probe Plus (SP+) mission is to understand how the solar corona is Heated and how the solar wind is accelerated. To achieve these goals, in situ measurements are necessary and the spacecraft has to approach the Sun as close as 9.5 solar radii. This trajectory induces extreme environmental conditions such as high temperatures and intense Vacuum Ultraviolet radiation (VUV). To protect the measurement and communication instruments, a Heat Shield constituted of a carbon material is placed on the top of the probe. In this study, the physical and chemical behavior of carbon materials is experimentally investigated under high temperatures (1600–2100 K), high vacuum (10−4 Pa) and VUV radiation in conditions near those at perihelion for SP+. Thanks to several in situ and ex situ characterizations, it was found that VUV radiation induced modification of outgassing and of mass loss rate together with alteration of microstructure and morphology.
Jeanlouis Sans - One of the best experts on this subject based on the ideXlab platform.
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thermal radiative properties of carbon materials under high temperature and vacuum ultra violet vuv radiation for the Heat Shield of the solar probe plus mission
Applied Surface Science, 2012Co-Authors: Marianne Balatpichelin, J Eck, Jeanlouis SansAbstract:Abstract The Solar Probe Plus (SP+) mission will approach the Sun as close as 9.5 solar radii in order to understand the origin of the solar corona Heating and the acceleration of the solar wind. Submitted to such extreme environmental conditions, a thermal protection system is considered to protect the payload of the SP+ spacecraft. Carbon-based materials are good candidate to fulfill this role and critical point remains the equilibrium temperature reached at perihelion by the Heat Shield. In this paper, experimental results obtained for the solar absorptivity α, the total hemispherical emissivity ɛ and its ratio α/ɛ, conditioning the equilibrium temperature of the thermal protection system, are presented for different kinds of carbon materials Heated at high temperatures with or without vacuum-UV (100
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experimental study of carbon materials behavior under high temperature and vuv radiation application to solar probe Heat Shield
Applied Surface Science, 2011Co-Authors: J Eck, Jeanlouis Sans, Marianne BalatpichelinAbstract:Abstract The aim of the Solar Probe Plus (SP+) mission is to understand how the solar corona is Heated and how the solar wind is accelerated. To achieve these goals, in situ measurements are necessary and the spacecraft has to approach the Sun as close as 9.5 solar radii. This trajectory induces extreme environmental conditions such as high temperatures and intense Vacuum Ultraviolet radiation (VUV). To protect the measurement and communication instruments, a Heat Shield constituted of a carbon material is placed on the top of the probe. In this study, the physical and chemical behavior of carbon materials is experimentally investigated under high temperatures (1600–2100 K), high vacuum (10−4 Pa) and VUV radiation in conditions near those at perihelion for SP+. Thanks to several in situ and ex situ characterizations, it was found that VUV radiation induced modification of outgassing and of mass loss rate together with alteration of microstructure and morphology.
J Eck - One of the best experts on this subject based on the ideXlab platform.
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thermal radiative properties of carbon materials under high temperature and vacuum ultra violet vuv radiation for the Heat Shield of the solar probe plus mission
Applied Surface Science, 2012Co-Authors: Marianne Balatpichelin, J Eck, Jeanlouis SansAbstract:Abstract The Solar Probe Plus (SP+) mission will approach the Sun as close as 9.5 solar radii in order to understand the origin of the solar corona Heating and the acceleration of the solar wind. Submitted to such extreme environmental conditions, a thermal protection system is considered to protect the payload of the SP+ spacecraft. Carbon-based materials are good candidate to fulfill this role and critical point remains the equilibrium temperature reached at perihelion by the Heat Shield. In this paper, experimental results obtained for the solar absorptivity α, the total hemispherical emissivity ɛ and its ratio α/ɛ, conditioning the equilibrium temperature of the thermal protection system, are presented for different kinds of carbon materials Heated at high temperatures with or without vacuum-UV (100
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experimental study of carbon materials behavior under high temperature and vuv radiation application to solar probe Heat Shield
Applied Surface Science, 2011Co-Authors: J Eck, Jeanlouis Sans, Marianne BalatpichelinAbstract:Abstract The aim of the Solar Probe Plus (SP+) mission is to understand how the solar corona is Heated and how the solar wind is accelerated. To achieve these goals, in situ measurements are necessary and the spacecraft has to approach the Sun as close as 9.5 solar radii. This trajectory induces extreme environmental conditions such as high temperatures and intense Vacuum Ultraviolet radiation (VUV). To protect the measurement and communication instruments, a Heat Shield constituted of a carbon material is placed on the top of the probe. In this study, the physical and chemical behavior of carbon materials is experimentally investigated under high temperatures (1600–2100 K), high vacuum (10−4 Pa) and VUV radiation in conditions near those at perihelion for SP+. Thanks to several in situ and ex situ characterizations, it was found that VUV radiation induced modification of outgassing and of mass loss rate together with alteration of microstructure and morphology.
P V Prosuntsov - One of the best experts on this subject based on the ideXlab platform.
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Heat and mass transfer in the chemical vapor deposition of silicon carbide in a porous carbon carbon composite material for a Heat Shield
Journal of Engineering Physics, 2017Co-Authors: S V Reznik, K. V. Mikhailovskii, P V ProsuntsovAbstract:Physical and mathematical simulations of the chemical vapor deposition of silicon carbide in a porous carbon–carbon composite material in a chemical vapor deposition reactor for formation of a matrix of a carbon–ceramic composite material for a Heat Shield of an aerospace aircraft have been performed. Results of parametric calculations of the Heat and mass transfer at the macro- and microlevels in representative elements of the microstructure of carbon–carbon composite materials different in residual porosity at different temperatures in the reaction zone of the reactor are presented. Features of compaction of the pore space of a carbon–carbon composite material by a silicon-carbide matrix depending on the technological parameters of the reaction medium were analyzed.
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Heat and Mass Transfer in the Chemical Vapor Deposition of Silicon Carbide in a Porous Carbon–Carbon Composite Material for a Heat Shield
Journal of Engineering Physics and Thermophysics, 2017Co-Authors: S V Reznik, K. V. Mikhailovskii, P V ProsuntsovAbstract:Physical and mathematical simulations of the chemical vapor deposition of silicon carbide in a porous carbon–carbon composite material in a chemical vapor deposition reactor for formation of a matrix of a carbon–ceramic composite material for a Heat Shield of an aerospace aircraft have been performed. Results of parametric calculations of the Heat and mass transfer at the macro- and microlevels in representative elements of the microstructure of carbon–carbon composite materials different in residual porosity at different temperatures in the reaction zone of the reactor are presented. Features of compaction of the pore space of a carbon–carbon composite material by a silicon-carbide matrix depending on the technological parameters of the reaction medium were analyzed.
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prediction of thermophysical and thermomechanical characteristics of porous carbon ceramic composite materials of the Heat Shield of aerospace craft
Journal of Engineering Physics, 2015Co-Authors: S V Reznik, P V Prosuntsov, K. V. MikhailovskiiAbstract:A procedure for predicting thermophysical and thermomechanical characteristics of porous carbon–ceramic composite materials of the Heat Shield of aerospace craft as functions of the type of reinforcement, porosity of the structure, and the characteristics of the material′s components has been developed. Results of mathematical modeling of the temperature and stressed-strained states of representative volume elements for determining the characteristics of a carbon–ceramic composite material with account taken of its anisotropy have been given.
S V Reznik - One of the best experts on this subject based on the ideXlab platform.
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Heat and mass transfer in the chemical vapor deposition of silicon carbide in a porous carbon carbon composite material for a Heat Shield
Journal of Engineering Physics, 2017Co-Authors: S V Reznik, K. V. Mikhailovskii, P V ProsuntsovAbstract:Physical and mathematical simulations of the chemical vapor deposition of silicon carbide in a porous carbon–carbon composite material in a chemical vapor deposition reactor for formation of a matrix of a carbon–ceramic composite material for a Heat Shield of an aerospace aircraft have been performed. Results of parametric calculations of the Heat and mass transfer at the macro- and microlevels in representative elements of the microstructure of carbon–carbon composite materials different in residual porosity at different temperatures in the reaction zone of the reactor are presented. Features of compaction of the pore space of a carbon–carbon composite material by a silicon-carbide matrix depending on the technological parameters of the reaction medium were analyzed.
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Heat and Mass Transfer in the Chemical Vapor Deposition of Silicon Carbide in a Porous Carbon–Carbon Composite Material for a Heat Shield
Journal of Engineering Physics and Thermophysics, 2017Co-Authors: S V Reznik, K. V. Mikhailovskii, P V ProsuntsovAbstract:Physical and mathematical simulations of the chemical vapor deposition of silicon carbide in a porous carbon–carbon composite material in a chemical vapor deposition reactor for formation of a matrix of a carbon–ceramic composite material for a Heat Shield of an aerospace aircraft have been performed. Results of parametric calculations of the Heat and mass transfer at the macro- and microlevels in representative elements of the microstructure of carbon–carbon composite materials different in residual porosity at different temperatures in the reaction zone of the reactor are presented. Features of compaction of the pore space of a carbon–carbon composite material by a silicon-carbide matrix depending on the technological parameters of the reaction medium were analyzed.
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prediction of thermophysical and thermomechanical characteristics of porous carbon ceramic composite materials of the Heat Shield of aerospace craft
Journal of Engineering Physics, 2015Co-Authors: S V Reznik, P V Prosuntsov, K. V. MikhailovskiiAbstract:A procedure for predicting thermophysical and thermomechanical characteristics of porous carbon–ceramic composite materials of the Heat Shield of aerospace craft as functions of the type of reinforcement, porosity of the structure, and the characteristics of the material′s components has been developed. Results of mathematical modeling of the temperature and stressed-strained states of representative volume elements for determining the characteristics of a carbon–ceramic composite material with account taken of its anisotropy have been given.