| 摘要 |
FIELD: space engineering; maintenance of temperature conditions of entire spacecraft and its components. ^ SUBSTANCE: proposed method includes measurement of temperature in areas of panel with the aid of temperature sensors and maintenance of required temperature within tolerable range. Temperature is changed at time intervals determined by orientation of spacecraft relative to Sun and planets. Every time after change of temperature, measurements shall be made in this area and in adjacent areas and difference in magnitudes shall be noted. Temperature dependences between zones shall be determined taking into account heat delivered from adjacent components. Further temperature control is carried out with dependences taken into account. In case present temperature is beyond permissible limits, it shall be increased or decreased by control of heat delivered to zones from adjacent components. In case of failure of temperature control system components, heat is delivered from adjacent zones with serviceable components adhering to the conditions under which temperature dependences were determined beforehand. ^ EFFECT: enhanced reliability of system due to experimental determination of temperature dependence. ^ 5 dwg |
