Aerospace Instrument-Making Annotation << Back Orbital motion controlled model space vehicle with elastic structural components based on the principle of least Manuilov J.S. Aleshin E.N. Designing control systems of the orbital motion of the spacecraft to a certain extent determined by its design features. To solve the problem of synthesis of control orbiting spacecraft with elastic elements of design occupies a special place representation problem of the orbital motion of a complex managed multiply dynamic object with elastic elements. The paper presents a model of managed orbital motion of the spacecraft with elastic elements structure, built on the principle of least action. This model allows in terms of ensuring optimal energy balance in the controlled system more fully take into account the characteristics of the power and energy of interaction of its individual components , as well as the transition to partial differential equations in the form of Euler -Lagrange equations . Using the methods of sampling and approximation, and transformation procedures, reduction, decomposition and linearization allowed to make the transition to the finite-dimensional representation of the dynamics of the controlled motion of the spacecraft with elastic elements of the design. Key words: spacecraft, mechanical system, multiply the dynamic object-driven orbital motion, the elastic element of design. Contacts: E-mail: aleshin_evgeny@inbox.ru Pp. 37-46.