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.

scholarly journals UAV Control System Design Using Backstepping-Sliding Mode Controller

2018 ◽  
Vol 11 (3) ◽  
pp. 183-190
Author(s):  
Jongho Han ◽  
차현록 ◽  
Gye-Seong Lee ◽  
Myeonghwan Hwang ◽  
Dong Hyun Kim
Keyword(s):  
Control System ◽  
System Design ◽  
Sliding Mode ◽  
Control System Design ◽  
Sliding Mode Controller

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.

Based on Analysis of Fast Simulation Algorithm for Multi-Objective BVR Attacking Fire Control System

2014 ◽  
Vol 898 ◽  
pp. 900-903
Author(s):  
Yi Guo Ji ◽  
Zhong Xiang Tao ◽  
Cui Chen ◽  
Zhi Huan Lan ◽  
Chun Yan Tian
Keyword(s):  
Control System ◽  
System Design ◽  
Continuous Improvement ◽  
Control System Design ◽  
Simulation Algorithm ◽  
Fast Simulation ◽  
Fire Control ◽  
Multi Objective ◽  
Combat Aircraft ◽  
Simulation Results

With the continuous improvement of fire control system functions to further improve the performance of missile weapons, combat aircraft requires BVR combat capability, multi-objective BVRAC will be the next major form of combat and trends. This article will fast simulation algorithm is applied to multi-target attack fire control system design, we propose a multi-target attack BVR fire control system design. Simulation results show that: the design of high precision, calculation speed, fully meet the requirements of real-time speed and airborne weapons systems.

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