A mathematical model is developed for a radiant heat exchanger with a hybrid two-layer structure, used in thermal regulation of spacecraft. The results of the model calculations are compared with the ...results obtained using an analytical model.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
The outer loop structure of a thermal control system with heat stores is optimized for spacecraft use. The best criterion for assessing the system efficiency is discussed.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
The structure of the external loop in the heat management system of a spacecraft with heat stores is optimized. Criteria for assessing the system’s effectiveness are evaluated.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
Heat stores of different design are compared, with a view to identifying the maximum stored energy density and power 1, 2. The heat store selected has a melting working medium. This design is the ...most promising for the maintenance of acceptable thermal conditions in spacecraft 3, 4.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
A method is proposed for selecting the design parameters of heat stores used in spacecraft temperature maintenance. The position of the store in the system is chosen. The heat store’s design, ...geometric dimensions, thermal capacity, and working medium are determined.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
A mathematical model is proposed for a heat store with a melting working medium. The store takes the form of parallel plates of a material that undergoes phase transition. Coolant flows between the ...plates. The function describing the thermophysical properties of the working medium, which changes abruptly on phase transition, is smoothed within a certain temperature range.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
To deploy a lunar habitable base, a new elemental composition of the system for providing a thermal regime is being developed. To reduce the mass and increase the reliability of the operation of a ...radiation heat exchanger of the system of providing thermal regime under the conditions of the lunar surface, it is proposed to replace the radiant duralumin panel of the radiation heat exchanger with heat pipes by a highly conductive radiant panel of hybrid structure based on pyrolytic graphite. This paper is devoted to determining the thermophysical properties of an anisotropic hybrid structure based on graphite. The thermal diffusivity and thermal conductivity of samples were determined by the laser flash method. Approximations of the dependences of the in-plane and out-of-plane thermal diffusivities and thermal conductivity of the hybrid structure from pyrolytic graphite on temperature for the temperature range 256–372 K have been obtained.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
The outer loop in the thermal control system of a lunar base module is subjected to thermodynamic analysis. The conclusion is that the radiant heat exchanger operates in three modes on the lunar ...surface.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
A radiator with a two-layer hybrid structure is proposed for thermal control systems in spacecraft. Mathematical modeling confirms the efficiency of the emitting surface. On that basis, without loss ...of reliability, the heat pipes may be eliminated, and consequently the radiator mass is significantly decreased.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
In the present work, we consider the use of thermal stores in spacecraft heating systems. The advantages and disadvantages of various approaches to heat storage are compared. The use of heat stores ...with a melting working material is most promising and practicable at present.
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EMUNI, FIS, FZAB, GEOZS, GIS, IJS, IMTLJ, KILJ, KISLJ, MFDPS, NLZOH, NUK, OILJ, PNG, SAZU, SBCE, SBJE, SBMB, SBNM, UKNU, UL, UM, UPUK, VKSCE, ZAGLJ
