Nowadays, attitude control systems of satellites with rigid and flexible components are demanding more and more better performance resulting in the application of new advanced nonlinear control theory. This is the case when the dynamics of the plant that describe the attitude motion of the satellite is nonlinear and the mission involves stringent pointing accuracy. As a result, control designs methods presently available, needs more investigation to know their capability and limitations. In that context, the guaranty of the controller performance depends not only on its good design but also on the knowledge of the nonlinear characteristics of the system in order to improve the overall control system efficiency. In this paper, a new nonlinear control law for satellite attitude control (SAC) is presented. It is based on an extension of the linear quadratic regulator (LQR) theory to the case where the dynamics is described by a nonlinear system of equation (Euler’s equation). The control law performance is investigated in frequency domain evaluating the compromise between the gain level and bandwidth length. In time domain the control law performance is observed by its capability of shifting the overshot to the origin direction. By and large, one observes that the nonlinear terns in the control law are able to deal with the nonlinear term in the model, which reveals that the nonlinear control law is more efficient than the control law based on the linear theory, even in the presence of the parameters variation.
Weitere Kapitel dieses Buchs durch Wischen aufrufen
Bitte loggen Sie sich ein, um Zugang zu diesem Inhalt zu erhalten
Sie möchten Zugang zu diesem Inhalt erhalten? Dann informieren Sie sich jetzt über unsere Produkte:
- Design of Satellite Control System using the Optimal Nonlinear Theory
Luiz Carlos Gadelha De Souza
- Springer Netherlands
in-adhesives, MKVS, Zühlke/© Zühlke, Nordson/© Nordson, ViscoTec/© ViscoTec, Hellmich GmbH/© Hellmich GmbH