Sovremennye problemy distantsionnogo zondirovaniya Zemli iz kosmosa, 2025, V. 22, No. 3, pp. 97-106
Algorithms for spacecraft astroorientation in the orbital coordinate system
1 JSC Military Industrial Corporation "NPO Mashinostroenia", Reutov, Moscow region, Russia
Accepted: 10.04.2025
DOI: 10.21046/2070-7401-2025-22-3-97-106
The article discusses algorithms for astroorientation of a spacecraft relative to the orbital coordinate system. According to the author, these issues are insufficiently covered in Russian literature which is most likely due to the well-established concept of using astroorientation algorithms written in relation to an inertial coordinate system. At the same time, it is widely believed that the latter approach leads to fewer orientation errors, but there is no convincing evidence for this assumption. Moreover, there are a number of problems that are quite difficult to solve in these systems, for example, the issues of determining and compensating for the self-drift of gyroscopes of a block of gyroscopic angular velocity meters in flight conditions, adapting the orientation system to a gyroscopic structure, correctable autonomous mode, and a number of others. In this regard, the issues of constructing and researching spacecraft astroorientation algorithms in the orbital coordinate system remain relevant. The article discusses two approaches to construction of such systems: a system for astrocorrection of readings of the angular velocity measuring unit with feedback and a system for astroorientation of the spacecraft according to the final rotation vector. The article presents brief derivation of differential equations describing the behavior of the systems, their structural and functional schemes, static errors of the systems in general form and graphs of transient processes.
Keywords: astroorientation, feedback, final rotation vector, orientation restoration
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