DocumentCode :
589415
Title :
Control of Hypersonic Vehicle Based on Improved QFT
Author :
Shi Zhen ; Wang Fei ; Ma Wen-qiao
Author_Institution :
Coll. of Autom., Harbin Eng. Univ., Harbin, China
Volume :
1
fYear :
2012
fDate :
28-29 Oct. 2012
Firstpage :
227
Lastpage :
230
Abstract :
Hypersonic vehicle has high military value in terms of real-time reconnaissance, remote rapid deployment and precision strike, especially the implementation of real-time reconnaissance mission has unique advantages. Efficient thrust, the aircraft must be flying high dynamic pressure conditions, in order to control the resulting aerodynamic heating and aerodynamic drag for the hypersonic vehicle angle of attack for precise control, at the same time, the dynamic characteristics of the hypersonic vehicle conventional aircraft are very different, the most critical aerodynamic characteristics are good enough stability of the pre-degree in terms of the control system must have a very strong robust feedback system. the QFT method, using an improved design of hypersonic flight longitudinal channel controller. Simulation results show that the robust controller design meets the system requirements.
Keywords :
aerodynamics; aircraft control; control system synthesis; drag; feedback; heating; military aircraft; robust control; QFT; aerodynamic drag control; aerodynamic heating control; dynamic characteristics; hypersonic flight longitudinal channel controller design; hypersonic vehicle control; hypersonic vehicle conventional aircraft; military value; precision strike; real-time reconnaissance mission; remote rapid deployment; robust controller design; robust feedback system; Aerodynamics; Aerospace control; Aircraft; Control systems; Robustness; Vehicle dynamics; Vehicles; QFT; control system; hepersonic; nonlinear;
fLanguage :
English
Publisher :
ieee
Conference_Titel :
Computational Intelligence and Design (ISCID), 2012 Fifth International Symposium on
Conference_Location :
Hangzhou
Print_ISBN :
978-1-4673-2646-9
Type :
conf
DOI :
10.1109/ISCID.2012.64
Filename :
6406959
Link To Document :
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