A Geometric Control System with Applications to Helicopters

[摘要] This thesis introduces an Automatic Flight Control System for single rotor helicopters which gives a new relevance to the traditional techniques based on the Linear Control Theory. This design was obtained by applying concepts of differential geometry tailored for engineering purposes through the Nonlinear System Theory. The development of this thesis follows the traditional path of applied sciences. First the need to establish techniques for theoretical analysis of flight machanics, where the small disturbance methods are no longer valid, is reviewed. This is followed by a presentation of the nonlinear problem and a survey of the development of the theoretical tools available. At this stage the process, a single rotor helicopter, is modelled. The model is then cast in a form suitable for Nonlinear System Theory techniques. Next, the mathematical theory to be applied is fully developed. It consists of finding the conditions required by a nonlinear system to be transformable under state feedback to a linear canonical form; the construction of the feedback is also presented. A Flight Control System is designed by applying this theory to the helicopter model previously formulated. The above application requires the development of Symbolic Algebraic Manipulation programmes, which are also included. Finally, a set of simulation studies demonstrate the performance of the design.

[发布机构] University:University of Glasgow

[关键词] Aerospace engineering