scholarly journals Lateral/Directional Control Law Design for Civil Airplane Based on Eigen Structure Assignment

2021 ◽  
Vol 2132 (1) ◽  
pp. 012050
Author(s):  
Bingbing Li ◽  
Dongguang Xu ◽  
Xiaohui Zheng ◽  
Bowen Zheng
Keyword(s):  
Flight Control ◽  
Aircraft Design ◽  
Control Law ◽  
Sideslip Angle ◽  
Directional Control ◽  
Roll Rate ◽  
Mode Characteristics ◽  
Design Requirements ◽  
Structure Assignment ◽  
Directional Flight

Abstract Considering disadvantages of lateral/directional mode characteristics of civil aircraft, design requirements are thus presented and the P-Beta control law architecture is adopted for the lateral/directional control law. Meanwhile, the practical application of eigen structure assignment in the design of lateral/directional control law is studied. By eigen structure assignment the closed loop is designed, and the decoupling of roll channel and yaw channel is realized. Through the design of feed-forward command channel, the pilot’s stick control roll rate and pedal control sideslip angle are realized. Simulation results show that the designed lateral/directional flight control law could meet design requirements.

The Study and Design of UAV Dynamic Inversion Flight Control Law

2010 ◽  
Vol 139-141 ◽  
pp. 1757-1762
Author(s):  
Ji Lin He ◽  
Rao Bao Jiang ◽  
Bo Liu ◽  
Xin Zhao ◽  
Qing Hua He
Keyword(s):  
Flight Control ◽  
Slow Variable ◽  
Dynamic Inversion ◽  
Control Law ◽  
Fast Variable ◽  
Nonlinear Mathematical Model ◽  
Outer Loop ◽  
Small Perturbations ◽  
Inversion Theory ◽  
Design Requirements

That the dynamic model is characteristic of nonlinearity and that linear equation design approach based on small perturbations of linear system has failed to meet the design requirements cause the study of the dynamic inversion control. Integrating the dynamic inversion theory and the UAV nonlinear mathematical model, the paper, in accordance with the speed of status variable change, has designed respectively the UAV inner-loop fast variable and outer-loop slow variable controllers and thus, found the dynamic inversion flight control law applicable to UAV and conducted the simulation study. A conclusion can be drawn that the control law is satisfactory in flight control.

Special issue “Flight control law design”

1999 ◽  
Vol 3 (3) ◽  
pp. 111-113
Author(s):  
Georg Grübel ◽  
Jean-François Magni
Keyword(s):  
Flight Control ◽  
Control Law ◽  
Special Issue

High-Sideslip Model Reference Adaptive Flight Control for Aileron Locked Aircraft

2014 ◽  
Vol 651-653 ◽  
pp. 751-756
Author(s):  
Peng Fei Cheng ◽  
Cheng Fu Wu ◽  
Yue Guo
Keyword(s):  
Flight Control ◽  
Control Method ◽  
Reference Model ◽  
Sideslip Angle ◽  
Model Reference ◽  
Control Scheme ◽  
Adaptive Flight Control ◽  
Random Initialization ◽  
Model Reference Adaptive ◽  
The Given

This paper develops a high-sideslip flight control scheme based on model reference adaptive control (MRAC) to stabilize aircraft under aileron deadlock of one side. Firstly, the cascaded flight control scheme for high-sideslip straight flight is presented and how the control signals transfer is also analyzed. After that, the control structure and laws of MRAC for attitude inner-loop connected with sideslip command are designed. Finally, the control scheme is verified under a nonlinear aircraft model in conditions of no fault and one side aileron deadlock respectively. The simulation results show that when one side aileron deadlock occurs in accompany with the plant’s aerodynamic data perturbation and random initialization of controller parameters, this control method could utilize operation points of no-fault aircraft to force the faulty aircraft following the given reference model responses and finally tracking given sideslip angle command without static error robustly.

scholarly journals A Study on the Design of Software Switching Mechanism for Develops the Flight Control Law

2006 ◽  
Vol 12 (11) ◽  
pp. 1130-1137 ◽  
Author(s):  
Chong-Sup Kim ◽  
In-Je Cho ◽  
Jong-Min Ahn ◽  
Ji-Hwan Shin ◽  
Sang-Seon Park
Keyword(s):  
Flight Control ◽  
Control Law ◽  
Switching Mechanism
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