Proba, an ESA technology demonstration mission, results after 3 years in orbit

Details Proba, an ESA technology demonstration mission, results after 3 years in orbit Proba, an ESA technology demonstration mission, results after 3 years in orbit

Nov 2004

adsabs.harvard.edu/cgi-bin/nph-data_query?bibcode=2004esasp.571e...7t&link_type=abstract

Proceedings of The 4S Symposium: Small Satellites, Systems and Services (ESA SP-571). 20 - 24 September 2004, La Rochelle, Franc

Computer Science

Performance

Scientific paper

PROBA (Project for On Board Autonomy) is a technology demonstration mission of the European Space Agency's General Support Technology Programme. PROBA was launched on October, 22nd , 2001 on a LEO Sun-synchronous 681x561 km orbit. The spacecraft mass is 94 kg, with 25 kg dedicated to scientific and Earth observation instruments, in addition to the technology demonstration payloads. PROBA principal objectives are in-orbit evaluation of new spacecraft technologies. PROBA, however, has also been intended as a flight opportunity for Earth observation instruments which can benefit from the pointing and agility capabilities of the satellite. PROBA onboard automatic functions include all payload operations scheduling and execution, target fly-by prediction and control of cameras pointing and scanning from raw inputs from users (target latitude, longitude and altitude). The point and stare requirements of the High Resolution Camera (HRC), as well as the multiple images scan requirement to support Bi-directional Reflectance Distribution Function (BRDF) measurements with the Compact High Resolution Imaging Spectrometer (CHRIS) are satisfied with the specified accuracy, by this small and agile gyro-less platform, whose attitude determination is based on autonomous star trackers only. PROBA main Earth imaging payload, CHRIS, weighting only 14 kg, is used to measure directional spectral reflectance. The instrument is capable of imaging (with multiple imaging of same target area under different viewing and illumination geometries) up to 200 spectral bands simultaneously at full resolution with a spatial resolution of 20 m at nadir and swath width of 15 km. The paper will cover, the spacecraft design and in-flight performances, as well as a description of the enabling technologies.

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