This paper focuses on the automatic control of aircraft in the longitudinal plane, during landing, by using the linearized dynamics of aircraft, taking into consideration the wind shears and the errors of the sensors. A new robust automatic landing system (ALS) is obtained by means of the H-inf control, the dynamic inversion, an optimal observer, and two reference models providing the aircraft desired velocity and altitude. The theoretical results are validated by numerical simulations for a Boeing 747 landing; the simulation results are very good (Federal Aviation Administration (FAA) accuracy requirements for Category III are met) and show the robustness of the system even in the presence of wind shears and sensor errors. Moreover, the designed control law has the ability to reject the sensor measurement noises and wind shears with low intensity.
Design of Automatic Landing Systems Using the H-inf Control and the Dynamic Inversion
Contributed by the Dynamic Systems Division of ASME for publication in the JOURNAL OF DYNAMIC SYSTEMS, MEASUREMENT, AND CONTROL. Manuscript received January 3, 2015; final manuscript received November 11, 2015; published online December 11, 2015. Assoc. Editor: Manish Kumar.
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Lungu, R., and Lungu, M. (December 11, 2015). "Design of Automatic Landing Systems Using the H-inf Control and the Dynamic Inversion." ASME. J. Dyn. Sys., Meas., Control. February 2016; 138(2): 024501. https://doi.org/10.1115/1.4032028
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