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.
2011
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.
G.Bertoni; N.Bertozzi; P.Castaldi; M.E.Penati; M.Bonfe; S.Simani
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Utilizza questo identificativo per citare o creare un link a questo documento: https://hdl.handle.net/11585/117264
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