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LANDING LUNAR MODULE INSTRUMENT COMPARTMENT THERMAL CONTROL SYSTEM

机译:登陆月球模块仪表室热控制系统

摘要

FIELD: aircraft engineering.;SUBSTANCE: in compliance with first version, proposed system comprises radioisotope heat generator (HG), controlled contour heat tube (HT), radiative heat exchanger and three-way valve. HT condenser is built in radiative heat exchange disconnected by three-way valve with the help of bypass line at platform temperature dropped below preset magnitude. Platform is mounted parallel with lunar gravitation field vector. HTs are built in said platform so that their bottom zones have thermal contact with HG at platform bottom. Top zones of HTs have thermal contact with evaporator of controlled contour HT at platform top. In compliance with second version, built-in HTs are arranged also parallel with lunar gravitation field vector. Note here that, additionally, incorporated is uncontrolled contour HT with its evaporator having direct teat contact with HG while condenser stays in contact with bottom zones of built-in HTs. Top zones of said HTs are interconnected by, at least, one collector pipeline and with controlled contour HT evaporator.;EFFECT: maintenance of preset thermal mode without suing electric drives and extra electric power.;16 cl, 9 dwg
机译:领域:飞机工程;实质:与第一版一致,拟议的系统包括放射性同位素热发生器(HG),受控轮廓热管(HT),辐射热交换器和三通阀。 HT冷凝器内置辐射热交换装置,在平台温度降至预设值以下时,借助旁通管路借助三通阀将其断开。平台与月球重力场矢量平行安装。 HT内置在所述平台中,因此它们的底部区域与平台底部的HG热接触。 HT的顶部区域与平台顶部受控轮廓HT的蒸发器热接触。根据第二个版本,内置的HT也与月球引力场矢量平行排列。在此请注意,此外,还结合了不受控制的轮廓HT,其蒸发器与HG直接接触,而冷凝器则与内置HT的底部区域保持接触。所述HT的顶部区域至少通过一根收集器管线和可控轮廓HT蒸发器互连;效果:维持预设的热模式而无需使用电力驱动器和额外的电力; 16 cl,9 dwg

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