Space Simulation

Satellites, space probes, landers and rovers are complex systems. They consist of various subsystems and components. External influences such as solar radiation, the albedo radiation of the Earth and the planets, the cold background of space or the heat generated by the system itself affect the satellite and can cause satellite components to become too cold or too hot. Calculating and optimizing the satellite's heat balance is therefore a challenging task and ensures that all systems installed in the satellite function optimally.

Such extreme environmental conditions can be simulated in IABG's WSA/TVA space simulation facility. The built-in solar simulator adequately reproduces solar radiation with the help of xenon lamps. A motion simulator allows the test specimen to rotate during the test. Additional thermal plates (active or passive) and infrared radiation equipment can be added to the test facility as required. We also have other facilities of different sizes and with different performance capabilities at our disposal

The CryoSat satellite in IABG's space simulation facility (WSA)

Thermal Vacuum Chambers

Performance Spectrum of Our Thermal Vacuum Chambers
(WSA, 5 m TVA, 3 m TVA, 2.5 m HeTVA, 2 m TVA)

Simulation of space conditions: High vacuum, low background temperature (LN2)
Clean room standards ISO 8 and ISO 5 (5m TVA & 2.5m HeTVA)
Artificial solar radiation generation with xenon lamps (WSA)
Free movement of the test object relative to the solar radiation using a motion simulator (WSA)
Micro-vibration decoupling (5m TVA)
High-temperature (up to 700 K) and low-temperature (down to 10 K) simulations in 2.5m HeTVA
Customized solutions and services available upon request
Chamber diameters from approx. 2 m to over 6 m, chamber lengths from approx. 2 m to 14 m.

Tests in the Thermal Vacuum Chamber (TV)

Thermal Vacuum Test (TV)

Thermal functional testing of both complete systems and individual control system components in high vacuum under varying temperatures.

Thermal Equilibrium Test (TB)

Testing at thermal equilibrium in a vacuum at different temperature levels to validate thermal model calculations.

Thermal Vacuum Cycle Test (TC)

Test in which the test specimen is subjected to a certain number of temperature cycles with specified minimum and maximum temperatures as well as defined holding times and temperature ramps.

Bake-out Test

Test in which the test specimen is exposed to a high temperature in a vacuum for a defined period of time. This removes outgassing products, such as silicones, which are present in the structure or adhesives due to the manufacturing process.

Low Temperature Test at Cryogenic Temperatures

The thermal walls of the test chambers are typically cooled using liquid or gaseous nitrogen, achieving minimum temperatures of approximately 90 Kelvin, sufficient for most test campaigns. However, for specific requirements, such as cooled optical instruments, significantly lower temperatures are necessary. IABG operates a specialized test chamber equipped with a helium cooling system, allowing temperatures as low as 10 Kelvin (near absolute zero) to be reached.

High temperature tests

More and more space missions are aiming to explore the sun and Mercury, the planet closest to the sun. The extreme temperatures prevailing there require the development of new materials and optimization of the satellite design.

We have further developed our test facilities and test methods for these new missions. The focus here is on generating temperatures of up to 450 °C, correctly measuring the temperatures and, if necessary, measuring deformations on the test specimen. In pioneering work, we have developed methods that enable the European space industry to test its products for missions such as Bepi Colombo or SolO.

Infrared tests (IR / OSTC)

When a geostationary satellite enters the sunlight from the Earth's shadow, high temperature gradients occur, particularly on large-area components such as solar panels, yokes or antenna reflectors. These extreme and constantly recurring thermal loads (thermal stress) can be simulated with the aid of infrared radiation fields. While the chamber wall continuously reflects the cold space background, the IR system takes over the temperature control of the test specimen.

Two standard thermal walls (3.8 m x 2.6 m and 5.1 m x 2.4 m) with infrared (IR) emitters are available to carry out tests in the temperature range from 98 K to 470 K and changeover ramps of up to 40 K/min.

Solar simulation for satellites, space probes and spacecraft

IABG's space simulation facility (WSA) is equipped with a solar simulation system that enables both circular and rectangular uniform irradiation. The maximum output is 1,950 W/m² with an illumination of approx. 3.6 m in diameter or 3 m x 4.5 m in a rectangle. Our motion simulator can be used to simulate customer-specific orbit scenarios for the test specimen. The chamber walls simulate the space background via the nitrogen cooling system (LN2).