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The article is devoted to the problems of joint optimization of mass, power and reliability characteristics of the thermal control system and radio electronic instruments for long term mission spacecraft of high reliability requirements. The instrument operation reliability depending mainly on cooling medium temperature, the problem of optimum temperature level choice in the thermal control system taking into account the maintenance of the reliability required is of great interest. The technique developed allows to choose the optimum instrument redundancy rate as well as the optimum temperature level in the thermal control system at minimum values of mass and power characteristics.