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.
G.Bertoni, N.Bertozzi, P.Castaldi, M.E.Penati, M.Bonfe, S.Simani (2011). Integrated design of an aircraft guidance system using feed-back linearization. AUTOMATIC CONTROL IN AEROSPACE, 16, 85-94.
Integrated design of an aircraft guidance system using feed-back linearization
BERTONI, GIANNI;CASTALDI, PAOLO;PENATI, MARIA ELISABETTA;
2011
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.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
