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Project Management, Professor of Satellite Technology

Prof. Dr.-Ing. Sabine Klinkner

Secretary
Prof. Klinkner

Annegret Möller


Institut für Raumfahrtsysteme
Pfaffenwaldring 29
70569 Stuttgart


 

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Thermal-Vacuum-Chamber

thermal-vakuum-tank-500

The Institute of Space Systems has a vacuum chamber that is exclusively used for thermal-vacuum tests of satellite components. By means of the absence of convection, it is possible to simulate the conditions for satellite systems as they would be in Earth orbit.

turbopumpe-225

 

 

The low pressure in the chamber is generated by two different pumps. At first, a vane pump establishes a prevacuum, which is needed for the turbo pump.

 

During the tests, the satellite components are exposed to different temperatures while monitioring their functionality. This is mandatory since the temperature in a satellite can vary more than 100 K.  The temperature of the components can be adjusted by a circulator, which pumps silicon oil through a copper plate and thus cools or heats the plate.

 

schema-englisch-500

Measurements from temperature sensors, which are located on different areas of the component, can be compared with mathematical predictions. The image below shows a component populated with temperature sensors (red) during a test in the thermal-vacuum-chamber.

Testobjekt in Thermal-Vakuum-Kammer 

The specifications of the thermal-vacuum-chamber as an overview:

 

Diameter 1 m
Length 2 m
Temperature range -40°C to 115°C
Cooling plate 400 x 500 mm² (effective 350 x 400 mm²)