Algorithms of Stabilization of a Spacecraft with Flexible Elements

Abstract

The methods of stabilization of a spacecraft (SC) main body with two flexible elements (antenna and panel) are studied in this paper. The process of stabilization is impeded by vibrations that occur in the nonrigid elements during the orbital and angular maneuvering of the SC and reduce the accuracy of its orientation. For this reason, the methods are also considered in the context of the problem of damping vibrations in the nonrigid elements. We consider the classical control methods, such as the Lyapunov control and linear-quadratic regulator, as well as the increasingly popular SDRE control (State Dependent Riccati Equation Control), which uses Riccati’s equation with the parameters dependent on the state vector. The control algorithms based on the reduced model of a SC with flexible elements are also described. An SC with flexible elements is assumed to be controlled only by the devices mounted on its body.