THERMAL VACUUM LABORATORY

Our Space department’s Thermal Vacuum laboratory carries out research on aerospace-related thermal issues. The laboratory is equipped with various data acquisition /logging systems for different types of temperature and vacuum/
pressure sensors, and 50 Hz infrared camera.
Furthermore, single-phase and two-phase liquid/vapor heat transport systems can be developed and tested. To this
end, a range of Coriolis mass flow meters, pumps, tubing and fittings are available. Fluid properties such as contact
angle, surface tension and density can be measured with dedicated equipment.

Thermal Vacuum chamber (Space Simulator)
• Shroud temperature:
-- Range -150 to 150 ˚C
-- Max. rate of change:
-- 1.7 ˚C/min. upslope
-- 3.0 ˚C/min. downslope
-- Programmable temperature profiles

• Heat sink temperature (independent from shroud temperature):
-- Range -100 to 150 ˚C
-- Max. rate of change:
-- ≈7 ˚C/min. upslope
-- ≈10 ˚C/min. downslope (depending on test item and
interface plate thermal masses)
-- Programmable temperature profiles
-- Small and large heat sinks

• Pressure:
-- Ultimate vacuum: <1 x 10-5 Pa (depending on test item
outgassing)

• As altitude chamber: 1-950 mbar (>100.000 ft, 32 km); temperature depending on pressure

• Mechanical dimensions:
-- Useful dimensions: 150 x 90 cm (length x diameter)
-- Various feed-through flanges from 2 x 4” to 2 x 11”
-- One viewing glass for visible and infrared light

• Data acquisition:
-- Independent data acquisition/logging system

• Dry vacuum pump system, with a cryogenic pump for high vacuum

• Quartz crystal microbalance for cleanliness monitoring of the chamber and test item