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 accordance with the method of bi-plane, the paper looks at the portable motion of the vehicle 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 selfoscillation, and to assess the accuracy of the craft orientation.