Smart aerosonde UAV longitudinal flight control system based on genetic algorithm

Synthesis of a flight control system for such an aircraft that achieves stable and acceptable performance across a specified flying envelope in the presence of uncertainties represents an attractive and challenging design problem. This study uses the genetic self-tuning PID algorithm to develop an intelligent flight control system for the aerosonde UAV model. To improve the system's transient responses, the gains of the PID controller are improved using a genetic algorithm (GA). Simulink/MATLAB software is used to model and simulate the proposed system. The proposed PID controller integrated with the GA is compared with the classical one. Three simulation scenarios are carried out. In the first scenario, and at normal conditions, the proposed controller performance is better than the classical one. While in the second scenario, identical results are achieved from both controllers. Finally, in the third scenario, the PID controller with GA shows the robustness and durability of the system compared with the classical PID in presence of external wind disturbance. The simulation results prove the system parameters optimization.

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IMPROVEMENT OF QUADROTOR PERFORMANCE WITH FLIGHT CONTROL SYSTEM USING PARTICLE SWARM PROPORTIONAL-INTEGRAL-DERIVATIVE (PS-PID)

Jurnal Teknologi ◽

10.11113/jt.v79.10680 ◽

2017 ◽

Vol 79 (6) ◽

Cited By ~ 1

Author(s):

Andi Adriansyah ◽

Shamsudin H. M. Amin ◽

Anwar Minarso ◽

Eko Ihsanto

Keyword(s):

Control System ◽

Flight Control ◽

Pid Controller ◽

Rapid Development ◽

Particle Swarm ◽

Open Loop ◽

Control Performance ◽

Proportional Integral Derivative ◽

Flight Control System ◽

Advanced Control

The rapid development of microprocessor, electrical, sensors and advanced control technology make a quadrotor fast expansion. Unfortunately, a quadrotor is unstable and impossible to fly in fully open loop system. PID controller is one of methodology that has been proposed to control the flight control system. Unfortunately, adjustment of PID parameters for robust control performance is not easy and still problems. The paper proposed a flight controller system based on a PID controller. The PID parameters are tuned automatically using Particle Swarm Optimization (PSO). Objective of this method is to improve the flight control system performance. Several experiments have been performed. According to these experiments the proposed system able to generate optimal and reliable PID parameters for robust flight controller. The system also has 41.57 % improvement in settling time response.

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Knowledge-Based Automatic Fault Detection in Flight Control System

Volume 9: Mechanical Systems and Control, Parts A, B, and C ◽

10.1115/imece2007-41495 ◽

2007 ◽

Author(s):

C. H. Lo ◽

Eric H. K. Fung ◽

Y. K. Wong

Keyword(s):

Genetic Algorithm ◽

Genetic Algorithms ◽

Control System ◽

Fault Detection ◽

Flight Control ◽

Detection System ◽

Flight Control System ◽

Actuator Failure ◽

Fuzzy Genetic Algorithm ◽

Fuzzy Genetic

There are various possible failures, like, actuator, sensor, or structural, which can occur on a sophisticated modern aircraft. In certain situations the need for an automatic fault detection system provides additional information about the status of the aircraft to assist pilots to compensate for failures. In this paper, we develop an intelligent technique based on fuzzy-genetic algorithm for automatically detecting failures in flight control system. The fuzzy-genetic algorithm is proposed to construct the automatic fault detection system for monitoring aircraft behaviors. Fuzzy system is employed to estimates the times and types of actuator failure. Genetic algorithms are used to generate an optimal fuzzy rule set based on the training data. The optimization capability of genetic algorithms provides and efficient and effective way to generate optimal fuzzy rules. Different types of actuator failure can be detected by the fuzzy-genetic algorithm based automatic fault detection system after tuning its rule table. Simulations with different actuator failures of the non-linear F-16 aircraft model are conducted to appraise the performance of the proposed automatic fault detection system.

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High Altitude Airship Flight Control System Design and Simulation

Applied Mechanics and Materials ◽

10.4028/www.scientific.net/amm.128-129.142 ◽

2011 ◽

Vol 128-129 ◽

pp. 142-145

Author(s):

Yong Hua Fan ◽

Xin Li ◽

Yun Feng Yu

Keyword(s):

Control System ◽

High Altitude ◽

System Design ◽

Flight Control ◽

Control System Design ◽

Flight Control System ◽

Compound Control ◽

Control Scheme ◽

Self Tuning

The high altitude airship can not have desired performance to control the altitude rapidly and accurately when the elevator or ancillary air bursa charge or deflation is used only, because the elevator has little efficiency when the velocity is low and auxiliary air bursas charge or deflation control is very slow. It is present a method to design flight control system for a high altitude airship using auxiliary air bursas charge or deflation and elevator combination control. This combination control scheme is that the ancillary air bursa and elevator are also used to control the airship attitude to get large raise velocity and the ancillary air bursa control is used to adjust the airship altitude for suspension. In this paper, a high altitude airship model with compound control of elevator and ancillary air bursa charge and deflation is given firstly. Then the combination controller is designed by using fuzzy self-tuning control. Finally, it has been proved by simulation that the flight control system has desirable performance and the compound control scheme is feasible.

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Flight control system design and optimisation with a genetic algorithm

Aerospace Science and Technology ◽

10.1016/j.ast.2004.09.003 ◽

2005 ◽

Vol 9 (1) ◽

pp. 73-80 ◽

Cited By ~ 12

Author(s):

Roberto Fantinutto ◽

Giorgio Guglieri ◽

Fulvia B. Quagliotti

Keyword(s):

Genetic Algorithm ◽

Control System ◽

System Design ◽

Flight Control ◽

Control System Design ◽

Flight Control System

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PID Control Based Missile Sub-Channel Simulation

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.433-440.7011 ◽

2012 ◽

Vol 433-440 ◽

pp. 7011-7016 ◽

Cited By ~ 1

Author(s):

Chao Bo Chen ◽

Bing Liu ◽

Ning He ◽

Song Gao ◽

Quan Pan

Keyword(s):

Control System ◽

Real Time ◽

Flight Control ◽

Pid Control ◽

Pid Controller ◽

Channel Model ◽

Control Method ◽

Flight Control System ◽

Aerodynamic Control ◽

The Stability

The accuracy and real-time of modern missile flight control system of traditional aerodynamic can not be satisfied. In this paper a new method is presented to improve the accuracy and real-time of missiles under this condition. First of all, a missile sub-channel model of the dynamic equations and steering gear is established, then based on the established model, using PID controller to control steering gear and three channels of missile pitch, yaw, roll respectively which is called missile sub-channel PID control method, and finally making use of MATLAB/Simulink to complete the simulation. Simulation results show that compared with traditional aerodynamic control system, this method can reduce the response time of aerodynamic missile and enhance the stability of the control system obviously.

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