The paper presents the automatic control of the aircraft in the longitudinal plane during landing, taking into account the sensor errors and the wind shears. The H-inf control provides robust stability with respect to the uncertainties caused by different disturbances and noise type signals, while the dynamic inversion provides good precision tracking. These techniques are combined and a robust automatic landing system is obtained; by adding an optimal observer and two reference models providing the desired altitude and velocity, one obtained a new automatic landing system which is very suited for landing control in the longitudinal plane. The optimal control law is calculated in two ways, this improving the generality, applicability, and simplicity degree of the automatic landing system. The theoretical results are validated by numerical simulations for a Boeing 747 landing; the simulation results are very good (Federal Aviation Administration accuracy requirements for Category III are met) and show the robustness of the algorithm even in the presence of wind shears and sensor errors. Moreover, the designed control law has the ability to reject the sensor measurement noises, wind gust, and wind shears with low intensity.
Automatic landing control using H-inf control and dynamic inversion
2014
15 Seiten, Bilder, 43 Quellen
Aufsatz (Zeitschrift)
Englisch
Automatic landing control using H-inf control and dynamic inversion
Online Contents | 2014
|Automatic landing control using H-inf control and dynamic inversion
SAGE Publications | 2014
|A L1 Adaptive Control Scheme for UAV Carrier Landing Using Nonlinear Dynamic Inversion
DOAJ | 2019
|Application of H2/H∞ and dynamic inversion techniques to aircraft landing control
Online Contents | 2015
|Control Law for Automatic Landing Using Fuzzy-Logic Control
Online Contents | 2008
|