System Overview
The IRS-1C is a three axis body stabilised satellite. It will have an operational life of three years
in a polar sun synchronous orbit at a height of 817 km.
The satellite payload consists of three sensors.
- Panchromatic camera (PAN)
- The Panchromatic camera will provide data with a spatial resolution of 5.8 m and a
ground swath of 70 km. It will operate in the 0.50-0.75 microns spectral band. This
camera can be steered upto ±26 deg (steerable upto ±398 km across the
track from nadir) which in turn increases the revisit capability to 5 days.
- Linear Imaging and Self Scanning Sensor (LISS-III)
- The LISS-III sensor will provide multispectral data collected in
four bands of the visible, near infra-red (V, NIR) and short wave infra-red (SWIR) regions.
While the spectral resolution and swath in the case of visible (two bands) and NIR
(one band) regions will be 23.5 m and 141 km, respectively they will be 70.5 m and 148 km,
for the data collected in SWIR region.
- Wide Field Sensor (WiFS)
- WiFS will collect data in two spectral bands and will have a ground
swath of 810 km with a spatial resolution of 188.3 m.
The satellite will be equipped with an onboard tape recorder, capable of
recording limited amount of specified sensor data. Operation of each of the sensors can be
programmed. The payload operation sequence for the whole day can be loaded daily onto the
onboard command memory when the satellite is within the visibility range.
The ground segment will consist of:
- A Telemetry Tracking and Command (TTC) segment comprising of
a TTC network to provide optimum satellite operations and a Mission Control centre for
mission management, spacecraft operations and scheduling.
- An Image segment comprising of data reception, data processing,
product generation systems and data dissemination centre.
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