Abstract
This research was carried out with the purpose of designing and simulating a control system for the longitudinal dynamics of an autopilot of a general aviation aircraft, which allows the execution of an approach and landing circuit automatically and correctly, based on the requirements given by the maximum category of the Instrument Landing System (CAT III C) that allows fully automatic landing. In the design of the control loops to perform the coupling to the glide slope, the Linear Quadratic Regulator (LQR) Methodology and the Affine Parameterization Methodology were used. The controllers were then tested through a dynamic autopilot simulation model for the aircraft under study, where a gap was found between the pitch angle reference and the measured pitch angle of the aircraft, so it would be necessary in the future to implement a state observer for the design of the vertical attitude controller, so that the developed control system complies with the general requirements and the proposed pre-design specifications. The methodology used could serve as a basis for the compilation of new results and possible comparisons.
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Notes
- 1.
ILS: Instrument Landing System.
- 2.
ICAO: International Civil Aviation Organization.
- 3.
IFR: Instrument Flight Rules.
- 4.
NEM: Nonlinear Energy Method.
- 5.
NNs: Neural Networks.
- 6.
A/P: Auto Pilot.
- 7.
MIMO: Multiple-Input, Multiple-Output.
- 8.
SISO: Single-Input, Single-Output.
- 9.
FCC: Flight Control Computer.
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Coello, L.A., Jácome, F.A., Zurita, J.R., Casa, C.W., Vélez, J.S. (2023). Design and Simulation of an Aircraft Autopilot Control System: Longitudinal Dynamics. In: Botto-Tobar, M., Gómez, O.S., Rosero Miranda, R., Díaz Cadena, A., Luna-Encalada, W. (eds) Trends in Artificial Intelligence and Computer Engineering. ICAETT 2022. Lecture Notes in Networks and Systems, vol 619. Springer, Cham. https://doi.org/10.1007/978-3-031-25942-5_31
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