Integral Mission Summary
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Objectives Gamma-ray astronomy 15 keV - 10 MeV using
high-resolution spectroscopy and fine imaging.
Concurrent monitoring in X-ray (3-35 keV) and
optical (500-600 nm) bands.
International collaboration: ESA, Russia, NASA
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Scientific Payload Main instruments:
Spectrometer (SPI)
Imager (IBIS)
Monitors:
X-Ray Monitor (JEM-X)
Optical Monitoring Camera (OMC)
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Orbit and launcher Highly eccentric orbit (HEO)
Launcher: PROTON
Period: 72h
Inclination: 51.6 deg
Perigee: 9 000 km
Apogee: 155 000 km
Ground stations Redu (B) & Goldstone (USA)
Time above 40 000 km ~90 %
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Spacecraft Three-axis stabilised bus common with XMM
Absolute pointing error <=5' (Y, Z axes), <=15' (X axis (roll) )
Launch dry mass 3600 kg
Science instruments mass 2087 kg
Science instruments power 721 W
Telemetry rate 113 kbps (science payload: 108 kbps)
Dimensions (satellite) LxWxH: 4x4x6 m (solar arrays undeployed)
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Operational mode Observatory
Nominal mission lifetime 2 years
Design lifetime 5 years
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