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EROS C Satellite Program

Follow-on spacecraft in the EROS family will be based on the Eros C, utilizing a new multipurpose platform developed at IAI's space systems group. EROS C, expected to be operational by 2009 will weigh less than 350 kg at launch and orbit at an altitude of 480 - 600 km, flown in sun-synchronous orbit. This satellite will be deployed  satellites will be crossing the equator at different times providing the EROS constellation with a daily revisit feature for any point over the globe. They will carry a camera with Charge Coupled Device/Time Delay Integration (CCD/TDI) focal plane that enables imaging even under weak lighting conditions. The camera system will provide 20,000 pixels per line (compared with 7,000 pixels/line on the current version) and produces an image resolution of 0.70 m for pan chromatic and 2.8 meters for multi-spectral (color) images with a swath of 11 km at nadir. The data transmission rate will be 455 Mbit/s. The expected lifetime of EROS C satellites is at least ten years.

Each of the EROS C-type satellites will repeat its ground track once every 15 days; however, because the camera can be pointed to the side (off-nadir), the ability to image a particular area on Earth in successive passes is substantially increased, enabling a revisit every 3 days at the equator for each one of the satellites. The satellite’s ability to point its camera also allows stereo imaging during the same pass.

Eros B specifications:
Launch weight: <350 kg
Orbit: 600 km Sun Synchronous
Ground sampling: 0.9 m
Over-sampling: 1.0 m
Swath width: 11 km
Scanning: Synch and Asynchronous push broom
Sensor type: CCD / TDI (selectable) with multi-spectral capability
Spectral band: 0.5 - 0.9μ
Sampling depth: 10 bits
Datalink rate: 455 MBit/sec




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  Updated: April 26, 2006




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