19 October 1999 Sun sensor for orientation and navigation systems of the spacecraft
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Proceedings Volume 3901, Photonics for Transportation; (1999) https://doi.org/10.1117/12.365928
Event: Photonics for Transportation, 1999, Prague, Czech Republic
Abstract
A digital Sun Sensor autonomously provides two-axis measurement of Sun center angular coordinates. It makes use of the OPTECS latest achievements in optoelectronic design. The Sun Sensor comprises two identical, but electrically not connected Sun Sensor devices (first and second channels) housed in a single aluminum enclosure. Every channel includes the following parts: optical system, linear CCD array-based photodetector, cpuModule with AT-bus, per PC/104 specification and a digital interface governed by the MIL- STD-1553B date bus. Each channel provides measurement of Sun center angular coordinates with a maximum error not exceeding +/- 1.5 angular minutes at an angular velocity of a spacecraft up to 30 angular minutes per second. The field- of-view against the azimuth angle (alpha) is +/- 48 degree(s) and against the elevation angle (beta) is +/- 40 degree(s).
© (1999) COPYRIGHT Society of Photo-Optical Instrumentation Engineers (SPIE). Downloading of the abstract is permitted for personal use only.
Alexander S. Zabiyakin, Alexander S. Zabiyakin, Vachesluv O. Prasolov, Vachesluv O. Prasolov, Alexandre I. Baklanov, Alexandre I. Baklanov, Anatoli V. El'tsov, Anatoli V. El'tsov, Oleg V. Shalnev, Oleg V. Shalnev, } "Sun sensor for orientation and navigation systems of the spacecraft", Proc. SPIE 3901, Photonics for Transportation, (19 October 1999); doi: 10.1117/12.365928; https://doi.org/10.1117/12.365928
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