Design of state feedback controller for an auto pilot: to control the stability of aircraft pitch

被引：0

作者：

Ali, Syed Muhammad ^{[1
]}

Ahmed, Salman ^{[2
]}

机构：

[1] Pukyong Natl Univ, Dept Elect Engn, Busan 48513, South Korea

[2] Univ Engn & Technol, Dept Comp Syst Engn, Peshawar, Pakistan

来源：

INTERNATIONAL JOURNAL OF INTERACTIVE DESIGN AND MANUFACTURING - IJIDEM | 2019年 / 13卷 / 01期

关键词：

Continuous-time system; Discrete-time system; State feedback controller; Eigen-values; SYSTEM;

D O I：

10.1007/s12008-018-0497-1

中图分类号：

T [工业技术];

学科分类号：

08 ;

摘要：

Aircraft motion in 3D plane is considered to be of three rotations. First one is roll, second one is pitch and the third one is yaw. Pitch of an aircraft cannot be neglected and it is one of the key features to control an aircraft. The pitch of an aircraft is in unstable state space variable, which leads to instability of an aircraft and a control scheme is required to stabilize the aircraft. In this paper, we propose a control strategy which can stabilize the aircraft system. Simulation results using MATLAB are presented to demonstrate the efficiency of proposed control scheme.

引用

页码：365 / 372

页数：8

共 20 条

[1] Hidden Oscillations In The Closed-Loop Aircraft-Pilot System And Their Prevention [J].