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Способ восстановления курсовой ориентации космического аппарата…
Инженерный журнал: наука и инновации
# 5·2017 9
Method for restoring the heading orientation of a spacecraft
using the orbital gyrocompass
©
I.N. Abezyaev, A.V. Andreyanenkova, P.E. Velichko,
A.I. Potselovkin, D.V. Fokin
JSC MIC NPO Mashinostroyenia, Reutov town, Moscow region, 143966, Russia
At present, the development of algorithms for controlling the angular orientation and
stabilization of the orbital spacecraft is one of the most relevant and dynamically devel-
oping areas in the field of astronautics and control theory. A special role in the algorithm
for reducing the bound coordinate system to the orbital coordinate system is the stage of
the heading motion. The current orientation systems, including the orbital gyrocompass,
do not have the proper quality of transient processes that would satisfy the requirements
of customers. Such systems require solving the problem of reducing the time for con-
structing OCS in the course channel and improving the quality of the transitional process
as a whole. This paper analyzes the "classical" orbital gyrocompassing (OGC) method
and shows its shortcomings. A new method to restore heading orientation using OGC is
proposed. It significantly reduces the time of transient processes and improves their qual-
ity. The graphs reflecting the behavior of spacecraft in the process of restoring the head-
ing orientation using the proposed method are presented.
Keywords:
restoring the heading orientation, orbital gyrocompass, orbital gyrocompass-
ing, spacecraft motion control system, angular motion of a spacecraft, spacecraft orien-
tation, spacecraft stabilization, program course turn
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