In this paper we present the design of a cryogenic platform for new space borne communication payloads. This platform is dedicated to service the operation of a communication payload in a cryogenic environment. In addition, an easy adaptation to any kind of available satellite buses must be reflected by the design of all interfaces. A first experimental demonstrator of this cryogenic platform with HTSC-components is foreseen to be operated on board the International Space Station (ISS) .The paper will present such a new kind of cryogenic platform. The thermal requirements and boundary conditions for the platform development are summarized. A comparison of the typical thermal environment of a communication satellite with the environment of the ISS and is performed. Two different concepts for the design of a cryogenic platform will be presented. A redundancy concept for the provision of cooling power and the thermal control of the cryogenic platform is discussed. Also, results of FEM-calculations of the two concepts done with the ANSYS 5.5 software will be reported. Finally, Data acquired during an intensive test campaign performed on a thermal dummy platform at Bosch Telecom will be compared to FE-results for the thermal dummy set-up.