The thermal vacuum chambers are used for the purpose of simulating a satellite circling in an orbit, in order to test a satellite's operating performance in the space environment, where near vacuum and great temperature fluctuation conditions are present. When a test is conducted, satellite is securely placed in the chamber, where a pump is used to draw out all the air, while liquid nitrogen, gas nitrogen and a heater are used for temperature control. Tests carried out generally include thermal vacuum, thermal circulation and thermal balance, to check whether the satellite can operate normally under a vacuum environment and whether the thermal control analysis performed during the design phase was accurate.
• Giant Thermal Vacuum Chamber • Small Thermal Vacuum Chamber • Micro Thermal Vacuum Chamber • Thermal Data Handling System amp; Heater Control System (TDHS/HCS) • Temperature / Humidity Test Chamber I • Temperature / Humidity Test Chamber II
• Satellite and space component thermal vacuum / thermal balance test • Test thermocouple fabrication and installation / removal • Test heater fabrication and installation / removal • Multi-Layer Insulation (MLI fabrication and installation) • Thermal data acquisition
• Giant Thermal Vacuum Chamber
| Giant Thermal Vacuum Chamber | |
Weight Capacity |
800 kg |
Operation volume |
3m (D)×3.5m (L) |
Ultimate pressure |
10-7 mbar |
Shroud Temperature Range |
-196℃(77K) in LN2 mode |
Shroud Maximum Temperature adjustment rate |
1℃(K) /min |
Baseplate Temperature Range |
NA |
Baseplate Maximum temperature adjustment rate |
NA |
Air-pumping rate |
10-5 mbar in 4 Hours |
• Small Thermal Vacuum Chamber
| Small Thermal Vacuum Chamber | |
Weight Capacity |
100 kg |
Operation volume |
1.5m (D)×1.5m (L) |
Ultimate pressure |
10-7 mbar |
Shroud Temperature Range |
-196℃(77K) in LN2 mode |
Shroud Maximum Temperature adjustment rate |
1.3℃(K) /min |
Baseplate Temperature Range |
-60℃(213K) ~ 100℃(373K) in GN2 mode |
Baseplate Maximum temperature adjustment rate |
1.3℃(K)/min |
Air-pumping rate |
10-5 mbar in 4 Hours |
• Micro Thermal Vacuum Chamber
| Micro Thermal Vacuum Chamber | |
Weight Capacity |
30 kg |
Operation volume |
0.7m (D )×0.7m (L) |
Ultimate pressure |
10-5 mbar |
Shroud Temperature Range |
NA |
Shroud Maximum Temperature adjustment rate |
NA |
Baseplate Temperature Range |
-60℃(213K) ~ 100℃(373K) |
Baseplate Maximum temperature adjustment rate |
1℃(K)/min |
Air-pumping rate |
10-5 mbar in 4 Hours |
• TDHS/HCS
| Thermal Data Handling System amp; Heater Control System | |
Temperature data acquisition channels |
280 ch |
Test thermocouple type |
T-Type |
Test heater channels |
300W*60 ch |
Heater Control System Operation Modes |
Constant Voltage Mode Constant Power Mode Constant Temperature Mode Constant Temperature Rate Mode |
• Temperature / Humidity Test Chamber I
| Temperature / Humidity Test Chamber I | |
Operation volume |
102 cm (W) × 100 cm (D) × 97 cm (H) |
Temperature Range |
180℃ ~ -70℃ |
Temperature Uniformity |
±0.5℃ |
Temperature Stability |
±0.3℃ |
Humidity Range |
20 ~ 98% RH |
Temperature Rate (up) |
5℃/min |
Temperature Rate (down) |
3℃/minn |
• Temperature / Humidity Test Chamber II
| Temperature / Humidity Test Chamber II | |
Operation volume |
60 cm (W) × 85 cm (D) × 80 cm (H) |
Temperature Range |
100℃ ~ -40℃ |
Temperature Uniformity |
±0.5℃ |
Temperature Stability |
±0.3℃ |
Humidity Range |
20 ~ 98% RH |
Temperature Rate (up) |
2℃/min |
Temperature Rate (down) |
1℃/minn |
• MIL-STD-1540 • SMC-S-016 • ECSS-E-ST-10-03C
A. Thermal Vacuum Chamber • FORMOSAT Series 1, 2, 3, 5, and 7 Satellite and Component Thermal Vacuum Test • FORMOSAT-5 Remote Sensing Instrument Thermal Vacuum Test • FORMOSAT-5 Remote Sensing Instrument Corrector Lens Thermal Vacuum Test • FORMOSAT-5 Remote Sensing Instrument Electronic Unit(EU) Thermal Vacuum Test • FORMOSAT-5 Remote Sensing Instrument Focal Plan Assembly(FPA) Thermal Vacuum Test • Anti-Material Spectrum, AMS-02, Project J/JT/JPD Crates Thermal Vacuum Test • Space-grade Gyro Thermal Vacuum validation Test • Ultra-Fast Flash Observation(UFFO) Project Thermal Vacuum Test(NTU) • Focal Plan Assembly(FPA) CMOS sensor Thermal Vacuum Test(CMOS Sensor Inc.) • Self-development GPSR Component Thermal Vacuum Test • Multi-Layer Insulator(MLI) and Flight Harness Thermal Vacuum Back-Out B. Temperature / Humidity Test Chamber • Micro Satellite Electronic Board Thermal Cycling Test • TUUSAT-1A Experimental Satellite Project DC/DC Converter and Charger Thermal cycling Test(NCKU) • Space-grade Gyro Thermal Cycling and Burn-In Test • Compton Spectrum Data Acquisition System Thermal Cycling Test(NCT) • FORMOSAT-5 Remote Sensing Instrument Electronic Unit(EU) Thermal Cycling Test • FORMOSAT-5 Remote Sensing Instrument Focal Plan Assembly(FPA) Thermal Cycling Test • FORMOSAT-5 Remote Sensing Instrument FPA and EU Engineering Model High/Low Temperature anomaly Trouble Shooting and De-Bug • Self-development GPSR Component Thermal Cycling Test • Eletro-Magnetic Valve Thermal Cycling Test • Lithium Battery Thermal Cycling Test • FORMOSAT-7 AU Antenna Thermal Cycling Test • FORMOSAT-7 GPSR Component Development and High/Low Temperature Cycling Performance Test • FORMOSAT-7 RF Beacon Electronics Unit (BEU, SN: 006) Component Thermal Cycling Test • FORMOSAT-7 Reflectometry Satellite Reaction Control System Module Thermal Cycling Test • Assemblage Multi-Spectrum Filter High/Low Temperature Cycling Test
