Abstract. A technique is proposed for calculations of non-stationary temperature of an isothermal space object of a cylindrical form with the axis stabilized in world system of coordinates, moving on a circular solarsynchronized orbit in the terminator plane. The class of objects under consideration includes a tubulardesign telescope body with axis fixed in the direction to a remote object, e. g. a star. Temperature fluctuations for objects of the class are subject to periodic changes of effective irradiance coefficient reproduced in each cycle of the object revolution around the Earth. For a great value of fixed thermal inertia realized in the case of thick enough wall of the cylinder, the fluctuations may occur with a temporary delay relative to external thermal impacts determined by fluctuations of irradiance coefficient. Average values of the effective irradiation coefficient decrease significantly as the orbit height increases: from a few tenths for an orbit height of 600 km to hundredths at the orbit height of 10000 km, and to several thousandths for a geostationary orbit. At the same time, the fluctuations of the effective irradiance coefficients are diminished, and contribution caused by the power of absorbed solar radiation to the energy balance of the space object increases. When the height changes from 600 to 40 000 km, the temperature level of the object with a completely black surface is lowered by 35 K, while the oscillation amplitude decreases from 5.6 to 0.4 K.

Keywords: space object, solar-synchronized orbit, non-stationary thermal balance of a space object, thermal radiation of Earth, effective irradiance coefficient

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