К анализу систем ориентации деформируемых космических аппаратов
13
On the analysis of the orientation of deformable spacecraft
© L.V. Severova, S.P. Severоv
Bauman Moscow State Technical University, Moscow, 105005, Russia
The problem under consideration is formulated as follows. There is a spacecraft (SC)
with external elastic elements of solar panel type. The main design parameters of the
spacecraft and dynamic characteristics (shape, frequency and damping) are assumed to
be theoretically determined and experimentally confirmed by flight or ground simulation
tests. SC has a system of sensors that determine its orientation to the specified object in
the sky, as well as an active complex of executive bodies — the engines. The craft must
keep the specified orientation in the definitely small area of variations. At the preliminary
design stage it is required to synthesize a nonlinear system of orientation of the deformed
craft. The study is aimed at using the flywheel rotor as the executive body and the method
of poly-phase plane for algorithmization of orientation management processes. In ac-
cordance with the method of bi-plane, the paper looks at the portable motion of the vehi-
cle on a single sheet and the relative motion of solar cells on the second sheet of the
phase bi-plane. The results could be used to detect the closed limit cycles of self-
oscillation, and to assess the accuracy of the craft orientation.
Keywords:
spacecraft, solar panels, the system of orientation, the phase plane.
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