Optimised flight control system with fault tolerance for an unmanned Aerial Vehicle

An unmanned Aerial Vehicle (UAV) is a powered aerial vehicle that does not carry a human operator and uses aerodynamic forces to provide vehicle lift which can fly autonomously. The optimal system parameters are efficiently shaped using the Integral squared error optimization and to improve the reliability of UAV the nominal control of UAV is improved. This is achieved by designing a fault tolerant control system. Thess aim of the work is to minimize the error function and an unconstrained problem is solved using the conditions of optimality and the fault tolerant control system design can be achieved using the eigen structure technique which stabilizes the system.