| 摘要 |
FIELD: spacecraft temperature control systems. ^ SUBSTANCE: proposed method includes measurement of temperature of spacecraft structural members and onboard equipment and components of rocket propellant, heating them by celestial body heat and conversion of electrical energy into thermal energy as measured temperatures reach low limits of thermostatting range. In flight, intervals of thermal energy accumulation in propellant components (at excess of thermal energy and electric power on board) and intervals of its free liberation are determined. In case expected magnitude of accumulated energy during predetermined interval exceeds upper level for preset volume of propellant, heat of celestial bodies is accumulated till the end of this interval. Otherwise, excess of electric power generated on board is converted into heat which is delivered to propellant components. In predicting release of thermal energy from propellant components, its residual amount required for maintaining the propellant component temperature within required ranges is determined; temperature of structural members and onboard equipment is also measured. In case this temperature exceeds permissible levels, delivery of heat is discontinued. When temperature of propellant component gets beyond threshold magnitudes, removal of heat from propellant components is discontinued. Otherwise, delivery of heat to thermostattable elements and onboard equipment and/or to points of accumulation of heat for subsequent useful conversion is continued till beginning of next interval of accumulation of thermal energy. Then, thermal energy accumulation cycle is repeated. ^ EFFECT: enhanced efficiency of accumulation and release of thermal energy; reduced mass and overall dimensions; enhanced heat removal. ^ 5 dwg |
