Guidance and Nonlinear Fault Tolerant Control for a General Aviation Vehicle

An innovative technique for integrated design of aircraft guidance system using Feedback Linearization technique is discussed. Numerical results using a Piper PA-30 non linear mathematical model are given in a various range of flight situations. The integrated approach is expected to be characterized by a good flexibility about trajectories, aircrafts and autopilots used, significant precise performances, and capability of rejection atmosphere disturbances and faults on command surfaces