Robust sliding mode speed hold control system design for full nonlinear aircraft model with parameter uncertainties: A step beyond

2012 ◽  
Author(s):  
E. Abdulhamitbilal ◽  
E. M. Jafarov
Keyword(s):  
Control System ◽  
System Design ◽  
Sliding Mode ◽  
Control System Design ◽  
Parameter Uncertainties ◽  
Aircraft Model

Integrated Aircraft Modeling Research for Accurate Flight Control System Design

2013 ◽  
Vol 791-793 ◽  
pp. 658-662
Author(s):  
Chao Zhang ◽  
Yi Nan Liu ◽  
Jian Hui Xu
Keyword(s):  
Control System ◽  
System Design ◽  
Flight Control ◽  
Time Delays ◽  
Flight Dynamics ◽  
Control System Design ◽  
Control Law ◽  
Flight Control System ◽  
Aircraft Model ◽  
Simulation Results

In order to realize accurate flight control system design and simulation, an integrated scheme of aircraft model which consists of flight dynamics, fly-by-wire (FBW) platform and flight environment is proposed. Flight environment includes gravity, wind, and atmosphere. And the actuator and sensors such as gyroscope and accelerometer models are considered in the FBW platform. All parts of the integrated model are closely connected and interacted with each other. Simulation results confirm the effectiveness of the integrated aircraft model and also indicate that the (Flight Control Law) FCL must be designed with robustness to sensor noise and time delays with the FBW platform in addition to the required robustness to model uncertainty in flight dynamics.

Vehicle ABS control system design via integral sliding mode

2016 ◽  
Vol 10 (4) ◽  
pp. 356
Author(s):  
Shibly A. Al Samarraie ◽  
Mohsin N. Hamzah ◽  
Yasir K. Al Nadawi
Keyword(s):  
Control System ◽  
System Design ◽  
Sliding Mode ◽  
Control System Design ◽  
Integral Sliding Mode

Dynamic Anti-Windup Design for Missile Overload Control System

2012 ◽  
Vol 236-237 ◽  
pp. 273-277 ◽  
Author(s):  
Xian Jun Shi ◽  
Hong Chao Zhao ◽  
Ke Wen Xu
Keyword(s):  
Control System ◽  
System Design ◽  
Actuator Saturation ◽  
Sliding Mode ◽  
Control System Design ◽  
Sliding Mode Controller ◽  
Overload Control ◽  
Saturation Time ◽  
Simulation Results ◽  
Saturation Phase

The former research on the overload control system of a supersonic missile didn’t consider actuator saturation. In order to reduce the windup effect caused by actuator saturation, we developed a dynamic anti-windup compensator. The overload control system design adopted a two-step approach. Firstly a sliding mode controller was designed ignoring the saturation. Secondly a dynamic anti-windup compensator was designed. It added to the control system to reduce the windup effect. It disengaged the actuator fast from saturation phase after the actuator entered saturation. Simulation results showed that the dynamic anti-windup compensator reduced 52% of saturation time of the control system. Hence the performance of the overload control system is improved effectively.

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