1.1.Introduction on Satellite Assembly, Integration and Test Facility (AIT)

In any spacecraft development, be it a manned or unmanned mission, for scientific research or as a space transportation, a spacecraft with its payload must be able to withstand the rigors of the lift-off and ascent environment occur during the launch phase, and, the extreme thermal conditions and operational environment experienced by the spacecraft and its payload once it is in orbit. This include the effects of intense acoustic and vibration generated by engine ignitions during lift-off, shocks generated during separation of stages and fairing, shocks during deployment of solar panels, temperature variation between extreme hot temperature to extreme cold temperature, vacuum condition, solar radiation and many other effects experienced by the spacecraft. Both mechanical and thermal effects introduced a lot of constraints on the structure design of a spacecraft and therefore, it must be thoroughly tested up to the system components to ensure the survivability of the spacecraft and its payload in space. And the testing conditions on Earth should simulate as close to as what will be experience by the spacecraft and its payload upon lift-off and while in space.

The Satellite Assembly, Integration and Test Centre (AITC) completed in 2011, is a facility that will provide those testing conditions as what will be experience by the spacecraft and its payload. The cost of a building a spacecraft is never cheap, thus, making it even more important to have it thoroughly tested on ground to ensure survivability of the spacecraft exceeds what it has been design for.  Therefore, the AITC facility is constructed to accommodate the testing requirements of both ground-based instruments and fully qualified space-flight hardware.

Environmental Conditions of the Facility:

Temperature                   :               22 ± 3°C

Humidity                           :               55 ± 10% RH

Particle (<0.5 µm)         :               100,000 unit / ft3

Ground Connection     :               < 1.0 Ω

√ Device under test (DUT) Receiving Airlock

√ Spacious high bay for integration works

√ Mechanical ground support equipment such crane, forklift, etc., are available

1.2.Main function of Satellite Assembly, Integration and Test Facility (AIT)

The AIT Facility is a cleanroom of class ISO 8 (or class 100,000 according to Federal Standard 209E) with a controlled environment and equipped with a large integration hall and variety of mechanical ground support equipment. The facility is able to simulate the actual launch and space environment as experienced by a satellite and its components during lift-off, separation and in orbit as well as able to be used to conduct testing and measurement for other field such as electronics, automotive, etc. The facility is able to provide a wide spectrum of test services, all under one roof, as well as providing managerial and technical competences needed to operate the environmental test facility.

1.3 Testing and Measurement Services offered at this facility

a)Vibration Test

Vibration Test is a test to simulate the vibration induced by rocket or spaceship to ensure that the satellite can withstand the maximum expected flight environment. It can also be used to conduct vibration tests for other non-space product.

Main Specification	Model V994	Model V9
Max Sine Thrust	289 kN	105 kN
Max Random Thrust	267 kN	105 kN
Max Velocity	2.0 m/s	3.0 m/s
Useful Frequency	5 -1700 Hz	5 – 2700 Hz
Max Load (10g Vector)	2693 kg	1070 kg

b) Reverberation Acoustic Test

Reverberation acoustic simulates vibration caused by the sound coming from the exhaust of the flight or rocket. This test facility simulates high intensity acoustic noise environment experience by satellite or spacecraft structures and components during launch.

Reverberation Acoustic Test Main Specification
Chamber volume	︡= 999.5 m3
Overall Sound Pressure Level (OSPL)	155 dB
Frequency Range	20 – 10,000 Hz
Sound Generation System	Gaseous Nitrogen (GN2)

c)Thermal Vacuum Test

Thermal vacuum test is a test that simulates extreme temperature and condition in space to ensure the satellite is able to operate within the range of temperature and vacuum condition in space.

Thermal Vacuum Test Main Specification
Operational Volume	3.7 m (ɸ)
Ultimate Pressure	10-7 mbar
Temperature Range	-180°C – 150°C

d)Electromagnetic Compatibility Test

Electromagnetic compatibility test is a test to ensure that there is no component or subsystem in the satellite that will emit interference with the operation of other components or subsystems through emission or susceptibility.

Electromagnetic Compatibility Test Main Specification
Operational Area	5m Compliance Full Anechoic Chamber
Temperature Range	20 Hz – 40 GHz

e)Mass Properties Measurement

Mass properties measurement is performed on a satellite to measure and determine the exact physical properties of a satellite, its subsystems and components to ensure the navigation and control of satellite is as per designed.

Mass Properties Measurement Main Specification
Max Test Weight: - Static - Dynamic	1300 kg 1000 kg
Max Moment of Inertia	1463 kgm2
Range of Spin Speed	30 – 300 rpm
Min Achievable Readout at 100 rpm	44 kgmm2

f)Alignment Measurement

Alignment measurement is performed to measure the exact geometrical alignment of the components on the satellite.

Alignment Measurement Main Specification
Theodolite System Accuracy	0.5 arcsecond
Rotary Table: - Indexing Accuracy - Repeatability	± 5 arcsecond ± 1 arcsecond