УСТРОЙСТВО ОПРЕДЕЛЕНИЯ ТЕРМИЧЕСКОГО СОПРОТИВЛЕНИЯЭКРАННО-ВАКУУМНОЙ ТЕПЛОИЗОЛЯЦИИ СИСТЕМЫ ТЕРМОРЕГУЛИРОВАНИЯ КОСМИЧЕСКОГО АППАРАТА

摘要

FIELD: heating; transportation. ^ SUBSTANCE: device contains thermally anisotropic plate mounted on external screen of screen-vacuum heat insulation (SVHI). Temperature sensors are connected on internal surfaces of SVHI external screens opposite to each other and to centre of gravity of specified plate. Plate contains number of series thermal elements formed by pairs of dissimilar conductors equally spaced in continuous electrical insulating matrix phase. Heat conductivity coefficient of matrix phase is considerably less than that of specified conductors. "Hot" contacts of these conductors are brought out to heated surface of plate, and "cold" contacts of conductors are brought out to cooled surface of plate. Electrical insulating layer covered with enclosure from material and with optical characteristics similar to those of specified SVHI external screen. ^ EFFECT: possibility of screen-vacuum heat insulation local thermal resistance detection on curved surfaces of spacecraft both in land handling and orbit. ^ 2 cl, 5 dwg