Multiple-Model Adaptive Flight Control Scheme for Accommodation of Actuator Failures

2002 ◽  
Vol 25 (4) ◽  
pp. 712-724 ◽  
Author(s):  
Jovan D. Boskovic ◽  
Raman K. Mehra
Keyword(s):  
Flight Control ◽  
Multiple Model ◽  
Actuator Failures ◽  
Control Scheme ◽  
Adaptive Flight Control

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.

Correction: Adaptive Flight Control with Unknown Time-Varying Unstable Zero Dynamics

2020 ◽  
Author(s):  
Syed Aseem Ul Islam ◽  
Adam L. Bruce ◽  
Tam W. Nguyen ◽  
Ilya Kolmanovsky ◽  
Dennis Bernstein
Keyword(s):  
Flight Control ◽  
Zero Dynamics ◽  
Time Varying ◽  
Adaptive Flight Control

A direct MRAC based multivariable multiple-model switching control scheme

Automatica ◽  
2017 ◽  
Vol 84 ◽  
pp. 190-198 ◽  
Author(s):  
Chang Tan ◽  
Gang Tao ◽  
Ruiyun Qi ◽  
Hui Yang
Keyword(s):  
Switching Control ◽  
Multiple Model ◽  
Control Scheme

scholarly journals Analisis Sistem Kendali Terbang dengan Gain Scheduling Pada Pesawat Efek Permukaan

WARTA ARDHIA ◽  
2017 ◽  
Vol 43 (2) ◽  
pp. 141
Author(s):  
Sayuti Syamsuar
Keyword(s):  
Control System ◽  
Flight Control ◽  
Surface Effect ◽  
Wind Tunnel Test ◽  
Longitudinal Mode ◽  
Gain Scheduling ◽  
Control Surface ◽  
Root Locus ◽  
Output Response ◽  
Adaptive Flight Control

This paper provides an overview of the design of adaptive flight control system of wing in surface effect craft Lippisch configuration 8 passengers capacity during cruise in the low speed and low altitude. The control system will be used the control surface, such as elevator deflection as input and pitch angle deflection as output response or by using engine throttle setting as input and others output response in the longitudinal mode. This paper describes some methodologies control system method and analysis such as PID controller system with gain scheduling approach, and root locus method. The observable matrices (4 x 4) on the longitudinal mode that used in the control system became from aerodynamic derivative parameters of 8 seaters configuration that calculated by DATCOM numerical simulation or wind tunnel test result and dummy data.  Kajian ini merupakan rancangan sistem kendali terbang adaptif pada pesawat efek permukaan konfigurasi Lippisch kapasitas 8 orang saat terbang mendatar pada kecepatan dan ketinggian terbang rendah. Sistem kendali terbang yang digunakan, seperti defleksi elevator sebagai input dan defleksi sudut pitch sebagai respon output atau penggunaan defleksi throttle mesin sebagai input dan parameter respon output lain pada gerak matra longitudinal. Kajian menjelaskan penggunaan beberapa metodologi dan analisis sistem kendali terbang adaptif, seperti kontroler PID dengan pendekatan gain scheduling, dan metoda root locus. Matriks ruang keadaan berukuran (4 x 4) pada matra longitudinal yang digunakan pada sistem kendali terbang adaptif diperoleh dari parameter turunan aerodinamika hasil perhitungan numerik DATCOM atau hasil uji terowongan angin dan data dummy.

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