Abstract
To study the thermal behaviour of satellite systems, measurements under simulated thermal space environment conditions are performed. These conditions are pressure below 10 −5 mbar, radiative heat sink and solar radiative input. The capabilities of IABG's space simulation and thermal vacuum facility WSA/TVA will be described. The vacuum chamber is a horizontal stainless steel cylinder of 6.8 m diameter and 13 m length resulting in a total chamber volume of approximately 500 m 3. The high vacuum pressure of < 2 × 10 −6 mbar for thermal testing is achieved by 6 helium refrigerator cryopumps of 150,000 I s −1 effective pumping speed. The operational characteristics as pump-down curve, residual gas analysis and repressurization procedure will be presented.
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