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.
Guidance and Nonlinear Fault Tolerant Control for a General Aviation Vehicle
BONFE', Marcello;SIMANI, Silvio;
2009
Abstract
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.File in questo prodotto:
Non ci sono file associati a questo prodotto.
I documenti in SFERA sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
