Carrier Landing Flight Path Angle Control via Higher-Order Sliding Mode

Author

Junfeng Chen ; Wei Han ; Guang Xu

Author_Institution

Dept. of Airborne Vehicle Eng., Naval Aeronaut. & Astronaut. Univ., Yantai, China

Volume

2

fYear

2014

fDate

26-27 Aug. 2014

Firstpage

146

Lastpage

149

Abstract

The accuracy of flight path angle is significant in carrier landing, thus the control of flight path angle is studied in this paper. A flight control system is designed via higher-order sliding mode which is bounded, continuously time-dependent, and provides higher accuracy than standard sliding mode. The robust exact differentiator is used to calculate the higher-order derivatives of sliding mode manifold. Based on aforementioned system, the automatic power compensate system is designed via PID controller. The simulation results are presented.

Keywords

aerospace control; control system synthesis; position control; three-term control; variable structure systems; PID controller; automatic power compensate system; carrier landing flight path angle control; differentiator; flight control system design; higher-order sliding mode; sliding mode manifold higher-order derivatives; Aerospace control; Aircraft; Atmospheric modeling; Manifolds; Mathematical model; Robustness; Sliding mode control; chattering attenuation; fight path angle; higher-order sliding mode control; robust exact differentiator;

fLanguage

English

Publisher

ieee

Conference_Titel

Intelligent Human-Machine Systems and Cybernetics (IHMSC), 2014 Sixth International Conference on

Conference_Location

Hangzhou

Print_ISBN

978-1-4799-4956-4

Type

conf

DOI

10.1109/IHMSC.2014.138

Filename

6911469