Stability and Performance Robustness of an L1 Adaptive Dynamic Inversion Flight Control System

2019 ◽  
Author(s):  
Joshua Harris ◽  
Christopher M. Elliott ◽  
Greg S. Tallant
Keyword(s):  
Control System ◽  
Flight Control ◽  
Dynamic Inversion ◽  
Flight Control System ◽  
Adaptive Dynamic ◽  
And Performance ◽  
Performance Robustness

scholarly journals Robust dynamic inversion control of flight control system based on L1 adaptive structure

2021 ◽  
Vol 39 (5) ◽  
pp. 995-1004
Author(s):  
Yu LI ◽  
Xiaoxiong LIU ◽  
Ruichen MING ◽  
Shaoshan SUN ◽  
Weiguo ZHANG
Keyword(s):  
Control System ◽  
Flight Control ◽  
Dynamic Performance ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
Parameter Uncertainties ◽  
Strong Robustness ◽  
Adaptive Structure ◽  
The Stability

Nonlinear Dynamic Inversion(NDI) control has excellent rapidity and decoupling ability, unfortunately it lacks the essential robustness to disturbance. From the perspective of enhancing the robustness, an adaptive NDI method based on L1 adaptive structure is proposed. The L1 adaptive structure is introduced into the NDI control to enhance its robustness, which also guarantees the stability and expected dynamic performance of the system suffering from the disturbance influence. Secondly, the flight control law of the advanced aircraft is designed based on the present method to improve the robustness and fault tolerance of the flight control system. Finally, the effectiveness of the flight control law based on the present approach is verified under the fault disturbance. The results showed that the flight control law based on L1 adaptive NDI has excellent dynamic performance and strong robustness to parameter uncertainties and disturbances.

Design UCAV Flight Control Law Based on Jamming Observer

2011 ◽  
Vol 66-68 ◽  
pp. 27-30
Author(s):  
Hai Wen Du ◽  
Xing Wei Weng ◽  
Yu Song Fu ◽  
Chuan Lin Tang
Keyword(s):  
Control System ◽  
Flight Control ◽  
System Stability ◽  
Good Stability ◽  
Dynamic Inversion ◽  
Control Law ◽  
Flight Control System ◽  
System A ◽  
Simulation Results

In order to study the nonlinear jamming problem in UCAV’s flight control system, a method of using observer to check the system’s jamming was designed, constructed robust dynamic inversion control law based on jamming observer. The simulation results show that the robust dynamic inversion control law based on jamming observer, make UCAV’s flight control system have good stability and robustness, it’s a great convenience analyzing the system stability.

Modeling, control design, and influence analysis of catapult-assisted take-off process for carrier-based aircrafts

2017 ◽  
Vol 232 (13) ◽  
pp. 2527-2540 ◽  
Author(s):  
Ziyang Zhen ◽  
Ju Jiang ◽  
Xinhua Wang ◽  
Kangwei Li
Keyword(s):  
Control System ◽  
Flight Control ◽  
Control Design ◽  
Control Surface ◽  
Flight Control System ◽  
Influence Analysis ◽  
Surface Ship ◽  
Lateral Channel ◽  
And Performance ◽  
Longitudinal Channel

This paper addresses the problems of modeling, control design, and influence analysis of the steam catapult-assisted take-off process of the carrier-based aircrafts. The mathematical models of the carrier-based aircraft, steam catapult, landing gears, and the environmental factors including deck motion and bow airflow have been established to express the aircraft dynamics in the take-off process. An engineering method based automatic flight control system has been designed, which is divided into the longitudinal channel and lateral channel. The influences of the preset control surface, ship deck motion, ship bow airflow, and automatic flight control system system are tested by a series of simulations. The simulation results show that the elevator angle preset is necessary in the stage of accelerated running on the ship deck and the deck motion is the most important factor for safe take-off, while the ship bow airflow is beneficial for climbing up of the aircraft. The automatic flight control system gives the guarantee of safety and performance in the take-off process of the carrier-based aircraft.

Design of Non-Linear Dynamic Inversion UAV with QFT

2012 ◽  
Vol 466-467 ◽  
pp. 676-679 ◽  
Author(s):  
Jie Li ◽  
Jie Zhang ◽  
Zhi Hui Xu
Keyword(s):  
Control System ◽  
Flight Control ◽  
Inversion Method ◽  
Dynamic Inversion ◽  
Model Errors ◽  
Flight Control System ◽  
Linear Dynamic ◽  
Performance Requirements ◽  
Non Linear ◽  
Aerial Vehicle

Flight control system of UAV (Unmanned Aerial Vehicle) has limitations with non-linear dynamic inversion method. This paper introduces QFT based on non-linear dynamic inversion method, for avoiding model errors during existing non-linear function offset, QFT theory is presented firstly, then UAV model is established using non-linear dynamic inversion method, definituding the range of errors and system performance requirements, flight control system of UAV is designed with QFT, the simulating curves show that system has robustness stability.

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