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Mechanism controller system for the optical spectroscopic and infrared remote imaging system instrument on board the Rosetta space mission

AuthorsRodrigo Montero, Rafael CSIC ORCID; Castro Marín, J. M. CSIC ORCID; Brown, V. J. G.; López Jiménez, A. C. CSIC ORCID; Rodríguez Gómez, Julio CSIC ORCID
KeywordsSpace vehicle electronics
Aerospace control
Infrared imaging
Field programmable gate arrays
Optical control
Issue Date22-Feb-2001
PublisherAmerican Institute of Physics
CitationReview of scientific instruments 72, 2423 (2001)
AbstractThe optical, spectroscopic infrared remote imaging system (OSIRIS) is an instrument carried on board the European Space Agency spacecraft Rosetta that will be launched in January 2003 to study in situ the comet Wirtanen. The electronic design of the mechanism controller board (MCB) system of the two OSIRIS optical cameras, the narrow angle camera, and the wide angle camera, is described here. The system is comprised of two boards mounted on an aluminum frame as part of an electronics box that contains the power supply and the digital processor unit of the instrument. The mechanisms controlled by the MCB for each camera are the front door assembly and a filter wheel assembly. The front door assembly for each camera is driven by a four phase, permanent magnet stepper motor. Each filter wheel assembly consists of two, eight filter wheels. Each wheel is driven by a four phase, variable reluctance stepper motor. Each motor, for all the assemblies, also contains a redundant set of four stator phase windings that can be energized separately or in parallel with the main windings. All stepper motors are driven in both directions using the full step unipolar mode of operation. The MCB also performs general housekeeping data acquisition of the OSIRIS instrument, i.e., mechanism position encoders and temperature measurements. The electronic design application used is quite new due to use of a field programmable gate array electronic devices that avoid the use of the now traditional system controlled by microcontrollers and software. Electrical tests of the engineering model have been performed successfully and the system is ready for space qualification after environmental testing. This system may be of interest to institutions involved in future space experiments with similar needs for mechanisms control. ©2001 American Institute of Physics.
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