Home / Infrastructures / Infrastructures / I&T Facilities

InfrastructuresI&T Facilities

Satellite Integration & Testing Building

Satellite shall possess high reliability to ensure that the bus and its components can tolerate special environments during the launch and orbiting phase, and to maintain a long-term normal operation in the Space environments.

Satellite integration and testing program consists assembly and integration of satellite bus with payloads and various function and environmental "simulation tests" in order, to make certain that the satellite perform its functions in accordance with the specifications.

The Satellite Integration & Testing Building is located adjacent to the office of Taiwan Space Agency (TASA) in Hsinchu Science-based Park. The construction of the Satellite Integration & Test Building was commenced in September 1994, and in July 1997 the Vice President Lien officiated its opening ceremony. The Satellite Integration & Test Building has so far completed satellite tests for FORMOSAT-1, FORMOSAT-2, FORMOSAT-3, FORMOSAT-5 and FORMOSAT-7. 

E&C Engineering Corporation was contracted for the civil construction and related engineering designs of the Satellite Integration & Test Building; the required specification for all equipments and facilities, technical consultations and personnel training were undertaken by a French company, Intespace.



Base area: 3,963 ping ( 13,102 square meters )
Construction area: 1,864 pings ( 6,162 square meters )
Building dimensions: 115 meters x 53 meters x 17 meters ( height )
Floor area: 3,834 pings ( 12,676 square meters )
Floor level: 1 basement level and 2 above ground levels

Building completion and open for use: in July 1997
Building contractors:

Engineering designs: by E&C Engineering Corporation
Civil construction: by BES Engineering Corporation Water, electricity and fire control: by Luxe Electric Co. 
Air-conditioning, ventilation and public facility: by Ta Cheng Engineering Co.

Thermal Vacuum Test Facility

The thermal vacuum chambers are used for the purpose of simulating a satellite circling in orbit, in order to test a satellite's operating performance in the space environment, where highly vacuum and extreme 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, gaseous 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
 

Operation volume: 3 meters (diameter) x 3.5 meters (length)
Ultimate pressure: 10 -7 mbar
Temperature range: 77 º K ~ 400 º K
Air-pumping rate: 10 -5 mbar in 4 Hours
Maximum temperature adjustment rate: 1 K/min

Miniature Thermal Vacuum Chamber

 

Operation volume: 1.5 meters (diameter) x 1.5 meters (length)
Ultimate pressure: 10 -7 mbar
Temperature range: 77 º K ~ 400 º K
Air-pumping rate: 10 -5 mbar in 2 Hours
Substrate temperature control range: 213K~373K
Substrate adjustment rate: 80K/hr

Acoustic Test Facility

The acoustic chamber is used for simulating a satellite during the launch phase, where a vibration environment is created as a result of noises caused by the rocket being launched, to verify whether the satellite can function normally after bearing such acoustic vibrations, and whether the designs and analysis of the satellite structure meet the acoustic vibration requirements. To conduct the tests, a vaporizer is used to gasify liquid nitrogen which works as source of noise, by adjusting the flow speed with a control equipment, and by the use of a noise producer to transform the kinetic energy into acoustic vibration waves which are then directed into the chamber to test the satellite in the Acoustic Environment Condition.


 

Operation Space: 6.25 meters (length) x 5 meters (width) x 8.4 meters (height)
Frequency range: 45Hz ~ 11,200Hz
Total noise level: 155dB (may be amplified up to 156dB)
Drawbar carrying capacity: 5,000 kg

Vibration Test Facility

Vibration Test Facility is used for simulating the low frequency vibrations caused by a rocket in the process when the satellite is being launched, not only to verify whether the satellite can function normally after bearing such vibrations, but also the designs and analysis of the satellite structure meet the vibration requirements. To conduct the test, a vibration control equipment that is used for controlling a power amplifier would start a high input150KN vibration machine on which the satellite is placed upon, through the extension platform and the horizontal-slide bench of the vibration machine to carry out a three-axial vibration test in vertical and horizontal directions respectively.

 

Sine standard thrust: 240 KN
Random standard thrust: 240 KN
Maximum offset: 38mm (peak value-peak value), within 5Hz ~ 15Hz frequency range
Maximum speed: 2 m/s, within 15Hz ~ 88Hz frequency range
Maximum acceleration: 100g, within 88Hz ~ 2,000Hz frequency range

Mass Property Measurement Facility

Mass property measurement facility is used for precisely measuring the centroid of a satellite, moment of inertia and product of inertia, in order to provide for satellite positioning control during orbit insertion and attitude adjustments .

During a measurement, a motor is used to slowly move the satellite, with the use of air-bearings to reduce resistance of friction, to measure the signal created (due to the movements) by sensors. The data are then used to calculate the position of the satellite centroid and the moment of inertia by the integrated data processing system.


  

Maximum test weight: 3,175 kg
Maximum weight offset: less than 0.04 kg
Maximum centroid offset: less than 0.25%

Electromagnetic Compatibility and Antenna Test Facility

The electromagnetic interference and compatibility tests are used for assessing whether electromagnetic interference phenomena exist among various satellite subsystems (including payloads). The assessments include the use of satellite antenna and a probe reader to conduct radiation and transmission tests, in order to understand electromagnetic field response produced by the satellite itself under normal operation, and find out the electromagnetic wave interference limit for which the satellite can tolerate. Antenna Measurement System has seven-axial action abilities, and can automatically perform antenna property measurement.


 

Operation area: 10 meters (length) x 13 meters (width) x 8 meters (height)
Operation area of Power Augment Chamber: 3 meters (length) x 4 meters (width) x 3 meters (height)
Drawbar carrying capacity: 2,000 kg
Frequency range: 30Hz ~ 40GHz

Antenna Test System

Frequency range: 1GHz~6GHz
Measuring approaches:

- Frequency Domain

Measuring classes:

- Planar Near-Field
- Spherical Near-Field
- Far-field Scan