Thermal balance testing needs to be performed on equipment for spacecrafts, payload modules or instruments. The requirements include two steady-state solar simulation tests: cold and hot worst cases to meet thermal equilibrium.
Solar environment has to be applied to simulate the real environment conditions.
Due to neonsee’s unrivaled steady-state sun simulation technology, we were elected to performing the thermal balance testing on the RIME antenna (Radar for Icy Moons Exploration) for the ESA JUICE (JUpiter ICy moons Explorer) mission.
| Spectrum (IEC 606904-3, ASTM G 173) | AM1.5D ??? |
| Spectral distribution (IEC 60904-9, ASTM E 927) | Class A |
| Range of light intensity | ??? |
| Collimation | ±0.3° |
| Illuminated area | ??? |
| Light source | Xenon Short Arc |
| Operating mode | Continuous |
| Lamp lifetime | > 1000 h |
| Short-term instability of irradiance (IEC 60904-9, ASTM E 927) | 0.5 % (Class A) |
| Long-term instability of irradiance (IEC 60904-9, ASTM E 927) | 0.5 % (Class A) |
| Non-uniformity of irradiance (IEC 60904-9, ASTM E 927) | 0.5 % (Class A) |
| Power supply | 1 Ph, 110/230VAC, 47-63Hz. ??? |
| Wattage | 2 kW ??? |
| Conformity | CE |
