Parametric synthesis of the design of a flexible and deformable spacecraft

The problem of synthesis of the dynamic characteristics of the design of a flexible and deformable spacecraft (SC) is considered. For its solution, a modal-physical form of the mathematical model [1] is obtained for the spatial motion of a flexible SC about its center of gravity. On the basis of the model obtained, the structure and the dynamic parameters of a flexible SC as a control object are determined. Formulas are obtained that establish relations between the dynamic parameters of the flexible SC as a control object and the physical parameters of its structure. A "portrait" of the dynamics of the structure is constructed on the basis of these formulas [1]. The construction of the portrait is exemplified by the dynamics of the structure of the pitch channel for a simplified flexible and deformable SC.