Neural-sliding mode augmented robust controller for autolanding of fixed wing aircraft

• Autorzy: Ismail I. , Pashilkar A. A. , Ayyagari R. , Sundararajan N.
• Języki publikacji: EN

Abstrakty

EN

Neural and sliding mode controllers are generally based on the principle of nonlinear dynamic inversion. This leads to control signals containing high frequency components. This can result in actuator rate limiting due to loss of phase at higher frequencies. Large control inputs, for example due to the saturation component of the sliding mode controller can also result in position saturation of the actuator. In this paper we show that by the introduction of suitable phase compensators and an antiwindup scheme the neuralaided sliding mode controller performance can be improved. A novel scheme is proposed for the cascaded feedback controller which addresses practical requirements of both state limiting and control surface saturation respectively.

Słowa kluczowe

EN

controller; nonlinear dynamic inversion; control signal; phase compensator; antiwindup scheme; wing aircraft; autolanding

• Wydawca: University of Social Sciences
• Czasopismo: Journal of Artificial Intelligence and Soft Computing Research
• Rocznik: 2012
• Tom: Vol. 2, No. 4
• Strony: 317--330
• Opis fizyczny: Bibliogr. 17 poz., rys.

Twórcy

autor

Ismail I.

• Scientists, Flight Mechanics and Control Division, CSIR-National Aerospace Laboratories Bangalore – 560017, India

autor

Pashilkar A. A.

• Scientists, Flight Mechanics and Control Division, CSIR-National Aerospace Laboratories Bangalore – 560017, India

autor

Ayyagari R.

• Dept. of Instrumentation and Control Engg., National Institute of Technology CityTiruchirappalli, India

autor

Sundararajan N.

• School of Electrical & Electronic Engineering Nanyang Technological University, Singapore 639798

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