Only one of the three mechanisms of heat transfer (heat conductivity, convection, and radiation), namely, radiation is possible for space vehicles (SV), since they have contact neither with a solid body (there is no contact with other objects), nor with a gas (they operate in deep vacuum). To maintain the thermal mode, active and passive heatregulating systems are used. Passive systems are heat-regulating coatings (HRC) put on heat-regulating radiators or separate units and devices. According to the law of heat emission, the SV temperature is determined by the fourth root of the ratio of the integral solar radiation absorption coefficient (аs) to the emissivity (e): Т ~ (аs /e). During orbital flights, the absorption coefficient аs of the reflecting HRC increases due to the formation of photo-induced and radiative defects that absorb light in the solar range of the spectrum [1–3]. Since the emissivity of all known HRC either remains unchanged or decreases insignificantly (by 5%), the SV temperature increases in flight, which can cause overheating of the equipment and even its failure. This calls for the development of methods of temperature stabilization, one of which can be based on the emissivity increase with the absorption coefficient аs. Another situation in which the emissivity must be changed during an orbital flight is observed for the absorbing coatings. When the SV are in the Earth’s shadow zone or are rotated about their axes even in the zone illuminated by the sun, a fragment of their surface is screened by the airframe and is in the shadow zone, and the surface temperature here decreases because of the lack of the heat source – electromagnetic solar radiation. One of the methods of temperature stabilization at a preset level can be the emissivity decrease with the absorption coefficient аs remaining unchanged. To solve these problems of space materials science, compounds with phase transitions (PT) and general formula A(1-x)BxC(1-y)DyOz in which cations A and (or) C are partly substituted by ions B and D can be used as pigments of reflecting and absorbing coatings. These compounds without substitutes have phase transitions in the temperature dependences of the electric, dielectric, thermophysical, and other properties; after incorporation of substitutes, the phase transitions are displaced along the temperature scale. The displacement magnitude and rate, as well as some other PT characteristics, are determined by the type and concentration of substituting ions and conditions of their incorporation. Works studying the phase transitions in the temperature dependence of the emissivity are few in number, though the importance and practical necessity of such results are obvious. Works with ceramic samples [4] and powders of manganites of rare earth elements [5] should be mentioned here. The present work studies phase transitions in the temperature dependence of the emissivity of synthesized BaTi(1-y)SnyO3 powders to estimate the possibility of their application as pigments of heat-regulating coatings of space vehicles and household and technological enamels. To prepare solid solutions of barium titanate, BaCO3, SnO2, and TiO2 compounds were mixed by a magnetic mixer in bidistilled water; the mixture was evaporated for 1 h at a temperature of 100°C and put in a heat-treatment furnace for synthesis. The compounds with stannum cation concentrations of 10, 15, and 20 mass% were synthesized. The powder so obtained was then mixed with KO-596 lacquer in the 0.4 : 0.6 ratio, and the mixture was put on metal substrates. The