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The thermal behaviour of spacecraft especially of manned ones is governed by various thermophysical effects. Heat transfer by radiation, conduction and convection influence the overall behaviour of the spacecraft. Energy production, distribution and consumption have also strong impacts on the temperature field prevailing in the spaceplane. Moreover, chemical reactions, metabolic rates of the crew and external heat loads determine the thermal behaviour of the spacecraft. For design and optimisation of the system and its subsystems a mathematical model is required which describes these effects. There are many tools available with which parts of the above mentioned aspects can be covered. However, a comprehensive model of a spacecraft reflecting all aspects can only be established with a combination of different simulation tools. In the present paper methods are described, how different simulation tools can be used to set up such a model.

The Mini Pressurized Logistics Module (MPLM) is being developed as the Italian contribution to the International Space Station (ISS) Programme. To improve the efficiency of European space programmes, the Italian Space Agency (ASI) and the European Space Agency (ESA) have decided to increase the commonality between the MPLM and the Columbus Orbital Facility (COF), the European laboratory contribution to the ISS. As a result ASI will provide to ESA a primary structure of the MPLM to be used as the primary structure for COF; in return ESA will provide to ASI the ECLS subsystem for the MPLM, which is a subset of the COF ECLS subsystem. This paper describes the functions of the MPLM ECLS subsystem, the analytical and developmental activities performed by the ECLS Contractor, Daimler-Benz Aerospace Dornier GmbH, and the development status of the various ECLS equipment.