Sliding Mode Implementation of an Attitude Command Flight Control System for a Helicopter in Hover

被引：1
|
作者：
McGeoch, D. J. [1 ]
McGookin, E. W. [1 ]
Houston, S. S. [2 ]
机构：
[1] Univ Glasgow, Ctr Syst & Control, Dept Elect & Elect Engn, Glasgow G12 8LT, Lanark, Scotland
[2] Univ Glasgow, Rotorcraft Flight Dynam Grp, Dept Aerosp Engn, Glasgow G12 8QQ, Lanark, Scotland
来源：
ACTA POLYTECHNICA | 2005年 / 45卷 / 04期
关键词：
helicopter; sliding mode control; hover; handling qualities; ADS-33E-PRF; response types;
D O I：
暂无
中图分类号：
T [工业技术];
学科分类号：
08 ;
摘要：
This paper presents an investigation into the design of a flight control system, using a decoupled non-linear sliding mode control structure, designed using a linearised, 9th order representation of the dynamics of a PUMA helicopter in hover. The controllers are then tested upon a higher order, non-linear helicopter model, called RASCAL. This design approach is used for attitude command flight control implementation and the control performance is assessed in the terms of handling qualities through the Aeronautical Design Standards for Rotorcraft (ADS-33). In this context a linearised approximation of the helicopter system is used to design an SMC control scheme. These controllers have been found to yield a system that satisfies the Level 1 handling qualities set out by ADS-33.
引用
收藏
页码：88 / 95
页数：8
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