ISRO Spacecraft Integration Test Establishment (ISITE)

ISRO Spacecraft Integration Test
Establishment (ISITE)
ISRO Satellite Centre
Bangalore, INDIA
January 2016
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1.
2.
3.
4.
Clean room Facility
Physical Parameters Measurement Facility
Spacecraft Checkout Laboratory
RF Shielded Anechoic Chamber for System Level
EMI/EMC Measurement
5. Compact Antenna Test Facility (CATF)
6. Mechanical Ground Support Equipment (MGSE)
7. Spacecraft Alignment Activity
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ISRO Satellite Centre, Bangalore is equipped with a worldclass Clean room Test Facility at ISITE, wherein the
Spacecraft Assembly Integration and Testing (AIT)
activities are carried out to realize satellites of different
capacity and for different mission requirements.
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• The salient features of the Clean room Facility at ISITE are:
1. The clean room facility is of 100,000 class, as per FED
standard 209E.
2. Temperature, RH and particle counts are maintained as FED
STD 209E.
3. The air flow inside Clean room is laminar.
4. Clean room environmental parameters are monitored by
particle counter, O2 monitor and data logger.
5. There are two entrances to the clean room with dress
change facility and two emergency exits are provided in
clean room.
6. Clean room dimensions are approx. 53m long and 33m
wide.
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7. The Clean room flooring is of ESD epoxy as per international
standard.
8. The clean room is provided with 1 number of 15t /5t capacity
EOT (Electric Overhead Travelling) crane.
9. For loading/unloading of items to clean room from outside,
two numbers of air lock rooms are available.
10. EOT cranes with 20 t / 5t capacity are installed in air lock
rooms for loading/unloading of spacecraft and other allied
equipment.
11. Dedicated grounding (9 numbers) for raw power and ESD
lines available inside clean room.
12. Laminar flow table (1000 class) is available inside clean
room for storing sensitive items.
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13. ESD garments of sufficient quantity are available for working
inside clean room.
14. ESD work tables along with ESD chairs of sufficient quantity
are available inside clean room for working persons.
15. Ultra-pure low pressure GN2 supply is available inside clean
room.
16. Compressed air supply inside clean room as well as in air
lock rooms is available.
17. Vertical Dynamic Balancing Machine (VDBM), CG, MI, POI
measurement machines are available inside clean room.
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January 2016
Spacecraft on VDBM
for CG Measurement
Spacecraft on Physical
Parameters Machine
(Mass, C.G, M.I, P.I
measurements all in one
machine)
18. Sufficient number of crane weighing scales, starting from
1000 kg. up to 10000 kg. are available inside clean room for
weighing the spacecraft.
19. Sufficient number man lifts are available inside clean room.
20. Sufficient number work platforms are available inside clean
room.
21. UPS power supply for spacecraft testing and computers
available.
22. Raw power supply (230V, 50Hz) for spacecraft testing and
computers available.
23. Sufficient number of power points, 5 Amp,15 Amp and
cutler hammer available inside clean room and in air lock
rooms.
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24. Special Purpose Fixture (SPF), 4-bar fixtures, Low level work
platforms of capacity to spacecraft lift off mass, 6000kg. can
be provided subject to verification of interface, mass and CG.
25. Internal movement transportation system of capacity to
spacecraft lift off mass, 6000kg. can be provided subject to
verification of interface, mass and CG.
26. '0' G facility available inside clean room for deployment of
solar panels.
27. Clean room is well connected to EMI/EMC Anechoic
Chamber, Vibration Test Facility, Compact Antenna Test
Facility (CATF) and Thermo vacuum Test facility.
28. Safety blast shields for propulsion activity are available.
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29. RF Shielded fixtures for Low power level Radiation or EMI / EMC
tests (if required to be carried out inside clean room) are available.
30. Necessary material movement and material handling equipment are
available.
31. UV garment storage system available for de-germification of clean
room garments.
32. Separate storage area attached with clean room available for storing
flight hardware.
33. CCTV cameras installed at nodal places inside clean room for
surveillance purpose.
34. Safety fire and smoke detection systems are installed inside clean
room.
35. Spacecraft Check out Lab. is attached with clean room for testing of
spacecraft.
36. Separate cooling system can be provided for cooling of battery,
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January 2016
Payload panels, RF load panels etc.
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Typically one Checkout lab at ISITE is about 10m X 12m.
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The lab is with air-conditioning.
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False flooring is provided. View glazing is available between checkout and
clean room.
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All RF cables / waveguides and DC cables that are required to be routed
between racks and to clean room, can be routed below the false floor.
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Two ducts ( 600mm X 250mm) are provided in the wall for cable routing
between Checkout and Clean room.
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Uninterrupted Power Supply (UPS) AC power distribution board is available
on the wall with a capacity to support up to 25KVA of power and Non-UPS up
to about 5KVA.
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Cutler-hammer extension boards are also provided to power the racks with
Cutler-hammer connectors.
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Working table available can house about 7-8 monitors.
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One Pass-box ( 500mm X 500mm) is provided to pass small items to clean
room.
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Storage cupboards to store documents and small items.
10M
DUCT-1
DUCT-2
PASS BOX
VERTICAL AIR DUCT
SCC & PCOS PCs
Storage Area
12M
CHECKOUT RACKS
1. Launcher and Co-passenger Compatibility Test –
Radiated emission measurements and Radiated
Susceptibility test
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To demonstrate the functional performance of the Integrated Satellite in
the Launch Vehicle and Co-Passenger Electromagnetic Environment.
2. RF Radiation and Antenna Polarization Verification
Tests
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To demonstrate the functional performance of the RF Components (like
Antennas) that have not been tested in assembly level qualification
testing.
3. Auto-compatibility Test
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To demonstrate the total functional performance for self compatibility of
Integrated Satellite.
Parameter
Details
Frequency Range
30 MHz to 40GHz
Chamber dimensions
(LxWxH)
19.5 x 14.6 x16 m3
Shielding Effectiveness
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Quiet Zone
5m x 5m x 5m at height of 1.5m from floor
Reflectivity Levels in QZ: : -10 dB at 80 MHz,
-20 dB at 200 MHz and -40 dB at 1 GHz and above up to 40GHz.
RF Absorbers
Power Handling of Normal Absorbers : 0.2 W/cm2
Power Handling of High Power Absorbers : 2 W/cm2
Four power line EMI filter
(3 phase + 1 neutral) ,
230 / 440 VAC, 50 Hz frequency with 64 A current capacity
Antenna Mast system
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Magnetic Field: > 35 dB @ 20 MHz;
Electric Field: > 80 dB at 200 kHz up to 1 GHz
Plane Wave: > 100 dB from 1 GHz and above up to 40 GHz
Fully automatic , controllable locally and through fiber optic link
from control room ,
Range of scanning (Height): 0.9 to 6 m with ± 1 mm resolution
and ± 2 mm accuracy
Supports antennas up to 10 Kg.
EMC TESTS ON GSAT – 16
COMMUNICATION SPACECRAFT
EMC TESTS ON MARS ORBITER
MISSION (MOM) SPACECRAFT
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Dimension: 30mx20mx16m
Quite Zone:
Centre 5.5 m above floor
5.5(W)x5.0(H)x8.0(D)
DUT Positioner System:
• 5 Axis Heavy duty Positioner
• Can Handle up to 5000Kgf &
7500kgf-m Bending Moment
Feeds : Freq. 1 – 40 GHz
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Polarization Verification, Radiation
Pattern
EIRP,SFD,G/T and Other P/L
Parameters
PIM
Auto Compatibility
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Freq: 1-40 GHz
Agilent Microwave receiver
Synthesized Signal generator
Multi channel controller
Mixers, PIN Switches
Data Acquisition, Data
Processing, Data Presentation
Software
Spacecraft
undergoing Test
in CATF
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MGSEs are used to handle and support the spacecraft and
its sub systems during various phases of AIT.
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MGSEs enable access to various locations on the
spacecraft and its subsystems ensuring safe operations.
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MGSEs are also required to move and transport the
spacecraft to different places for carrying out various
activities like conducting vibration test, acoustic test, thermo
vacuum test, physical parameters measurement etc.,
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Several MGSEs have been designed, fabricated, tested
and qualified to use during various phases of AIT of
spacecraft.
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MGSEs are custom designed to suit particular class of
spacecraft.
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
The following MGSEs are custom built for use during AIT
operations:
• Spacecraft Transportation Container
• Spacecraft Transportation and Storage System
• Panel Transportation System
• Special Purpose Fixture
• S/c Integration 4-bar fixture
• Equipment Panel Integration Fixture
• Panel Handling System
• Spacecraft Handling system
• Physical Parameters Measurement System
• Clamp band, Mounting Adaptors etc.
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• Spacecraft and its subsystems / flight components require stringent
orientation and position requirement to meet its in-orbit functional
objectives.
• The subsystems/system undergo a number of alignment operations to
meet the specified accuracy.
• Alignment Measurement and Development section (AMDS) is
responsible for conducting alignment measurements and corrections for
all kind of Communication, Remote sensing and scientific spacecraft.
• The alignment activity on spacecraft is carried out at various levels viz.
subsystem level e.g. wheels, reflectors, LAM etc. and at spacecraft level
starting with master reference establishment.
• Further the spacecraft level alignment is also carried out in four phases:
Pre-thermo vacuum test , Post-thermo vacuum test , Post Dynamic test
and Pre-launch phases of spacecraft building.
• The AMDS team is also involved in developing new technology/ methods
to meet critical/stringent measurement requirements of payload and
spacecraft projects.
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January 2016
• AMDS is equipped with state of the art high accuracy class alignment
instruments and software, which are being used for Spacecraft alignment
activity.
Sl.
No.
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Optics Based Theodolite Instruments
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Close Range Photogrammetry (CRP)
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Shape Analysis Software
3D Coordinate Measurement and Analysis software
Auxiliary Test Support Facilities such as Alignment
fixtures, Surface Tables, Targets, Scale Bars, Coded
targets and accessories used for various alignment
instruments.
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Facility Description
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Target Projection System
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Multiple Camera System
Make
Lieca 5100A
Gedetic Systems
Inc., USA
Polyworks
VSTARS
Lieca, Brunson,
Hubbs
Gedetic Systems
Inc., USA
Procurement Under
Progress
January 2016
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Thank You