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

2017 ◽  
Vol 79 (6) ◽  
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.

scholarly journals Preliminary Validation of the Wind Tunnel Based Flight Control System Evaluation Method

2018 ◽  
Vol 179 ◽  
pp. 03021
Author(s):  
Min Huang ◽  
Zhong-wei Wang ◽  
Xing-Bao Yang ◽  
Zhen-yun Guo ◽  
Yao-bin Niu
Keyword(s):  
Control System ◽  
Wind Tunnel ◽  
Flight Control ◽  
Pitch Angle ◽  
Evaluation Method ◽  
Open Loop ◽  
Control Performance ◽  
Flight Control System ◽  
Pitch Control ◽  
Preliminary Validation

As mathematical models of aircraft aerodynamics and rudder loadings always have to be built in the hardware-in-the-loop simulation, wind tunnel based flight control system (FCS) evaluation methods were proposed in order to test and evaluate the flight control systems under real aerodynamic and rudder loading environment. To validate the evaluation method, a wind tunnel based flight control system test was performed in a hypersonic wind tunnel facility. As the aircraft support rig in the wind tunnel is static, the aircraft angle of attack cannot be changed in this test. During the test, the elevator response, the lift force and the pitching moment were measured. By analysing the measured data, the elevator control performance of the pitch control system was determined, and the pitch angle was successfully predicted, but the open-loop pitch control performance was not determined. These results validate the feasibility of evaluating the elevator control performance and predicting the pitch angle of a FCS by the wind tunnel based FCS evaluation method.

An H∞ Design Approach for a PID Automatic Flight Control System of a Launch Vehicle

2016 ◽  
Vol 859 ◽  
pp. 116-123
Author(s):  
Adrian Mihail Stoica ◽  
Mihaela Raluca Stefanescu
Keyword(s):  
Flight Control ◽  
Pid Controller ◽  
Design Methodology ◽  
Launch Vehicle ◽  
Proportional Integral Derivative ◽  
Flight Control System ◽  
Numerical Examples ◽  
Stability Robustness ◽  
Norm Minimization ◽  
Atmospheric Disturbances

The paper presents a design methodology for the automatic flight control of a launch vehicle. In the proposed approach the controller has a PID (Proportional-Integral-Derivative) structure but its gains are determined solving an H∞ norm minimization problem of the mapping from the atmospheric disturbances to the control amplitude and to the angle of attack of the launcher. The design methodology is illustrated by numerical examples in which both time responses and stability robustness properties of the optimal PID controller are analyzed.

PID Control Based Missile Sub-Channel Simulation

2012 ◽  
Vol 433-440 ◽  
pp. 7011-7016 ◽  
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.

scholarly journals Multistrand, Fast Reaction, Shape Memory Alloy System for Uninhabited Aerial Vehicle Flight Control

2012 ◽  
Vol 2012 ◽  
pp. 1-8
Author(s):  
M. Brennison ◽  
R. M. Barrett ◽  
L. Kerth
Keyword(s):  
Control System ◽  
Shape Memory Alloy ◽  
Shape Memory ◽  
Flight Control ◽  
Alloy System ◽  
Open Loop ◽  
Flight Control System ◽  
Loop Design ◽  
Aerial Vehicle ◽  
Sma Actuator

This paper details an investigation of shape memory alloy (SMA) filaments which are used to drive a flight control system with precision control in a real flight environment. An antagonistic SMA actuator was developed with an integrated demodulator circuit from a JR NES 911 subscale UAV actuator. Most SMA actuator studies concentrate on modeling the open-loop characteristics of such a system with full actuator performance modeling. This paper is a bit different in that it is very practically oriented and centered on development of a flight-capable system which solves the most tricky, practical problems associated with using SMA filaments for aircraft flight control. By using well-tuned feedback loops, it is shown that intermediate SMA performance prediction is not appropriate for flight control system (FCS) design. Rather, capturing the peak behavior is far more important, along with appropriate feedback loop design. To prove the system, an SMA actuator was designed and installed in the fuselage of a 2 m uninhabited aerial vehicle (UAV) and used to control the rudder through slips and coordinated turns. The actuator was capable of 20 degrees of positive and negative deflection and was capable of 7.5 in-oz (5.29 N cm) of torque at a bandwidth of 2.8 Hz.

scholarly journals The Design of an Automatic Flight Control System and Dynamic Simulation for Fixed-Wing Unmanned Aerial Vehicle (UAV) using X-Plane and LabVIEW

2021 ◽  
Vol 1 (1) ◽  
Author(s):  
Nur Ezzyana Ameera Mazlan ◽  
◽  
Syariful Syafiq Shamsudin ◽  
Mohammad Fahmi Pairan ◽  
Mohd Fauzi Yaakub ◽  
...  
Keyword(s):  
Control System ◽  
Unmanned Aerial Vehicle ◽  
Flight Control ◽  
Pid Controller ◽  
Pole Placement ◽  
Flight Simulator ◽  
Flight Control System ◽  
Labview Software ◽  
Controller Gain ◽  
Aerial Vehicle

This research focuses on developing an automatic flight control system for a fixed-wing unmanned aerial vehicle (UAV) using a software-in-the-loop method in which the PID controller is implemented in National Instruments LabVIEW software and the flight dynamics of the fixed-wing UAV are simulated using the X-Plane flight simulator. The fixed-wing UAV model is created using the Plane Maker software and is based on existing geometry and propulsion data from the literature. Gain tuning for the PID controller is accomplished using the pole placement technique. In this approach, the controller gain can be calculated using the dynamic parameters in the transfer function model and the desired characteristic equation. The proposed controller designs' performance is validated using attitude, altitude, and velocity hold simulations. The results demonstrate that the technique can be an effective tool for researchers to validate their UAV control algorithms by utilising the realistic UAV or manned aircraft models available in the X-Plane flight simulator.

scholarly journals Simultaneous Optimization of Tuning PID Cascade Control System Using Duelist Algorithms

2017 ◽  
Author(s):  
Totok R. Biyanto
Keyword(s):  
Control System ◽  
Pid Controller ◽  
Open Loop ◽  
Previous Method ◽  
Cascade Control ◽  
Simultaneous Optimization ◽  
Primary Loop ◽  
System P ◽  
Advanced Control ◽  
Cascade Control System

In this research, Proportional-Integral-Derivative (PID) controller was integrated into the advanced control system to achieve an optimal performance. One type of advanced control system is cascade control. In conventional cascade control, controller parameters in primary and secondary loops are tuned sequentially. First, the parameters in secondary controller are tuned using certain tuning rule, meanwhile the primary loop in the open loop mode. Furthermore, the controller parameters in primary loop are tuned by considering the influence of the controlled secondary loop. This makes the tuning of PID cascade control more difficult and takes more time consuming. This paper describes a method of simultaneous tuning cascade control system using Duelist Algorithm (DA) to estimate the proper control parameters of the primary and the secondary loops in the plants. The analysis was conducted based on the evaluation of the closed-loop response to a step set point changes. The results show that the proposed method has better control performance than the previous method. PID auto tuning using DA provide more robust performance of the control system.

scholarly journals Development of Real-Time Maneuver Library Generation Technique for Implementing Tactical Maneuvers of Fixed-Wing Aircraft

2020 ◽  
Vol 2020 ◽  
pp. 1-12
Author(s):  
Do hyeon Lee ◽  
Chang-Joo Kim ◽  
Man Jung Heo ◽  
Joo Wan Hwang ◽  
Hee Gyeong Lyu ◽  
...  
Keyword(s):  
Control System ◽  
Real Time ◽  
Air Force ◽  
Flight Control ◽  
Pid Control ◽  
Control Technique ◽  
Proportional Integral Derivative ◽  
Flight Control System ◽  
Generation Technique ◽  
Flight Simulations

This study develops the real-time maneuver library generation technique for performing aggressive maneuvers of fixed-wing aircraft. Firstly, the general maneuver libraries are defined, and then 7th-order polynomials are used to create the maneuver libraries. The attitude command attitude hold (ACAH) system, the rate command rate hold (RCRH) system, and the speed command speed hold (SCSH) system using the proportional-integral-derivative (PID) control technique are designed to minimize the complexity of the flight control system (FCS) and to reduce the weight and volume of the payload. Moreover, the FCS is used for implementing tactical maneuvers. Finally, flight simulations are implemented for the longitudinal loop and Immelmann-turn maneuvers to check the usefulness of the proposed maneuver library generation technique. This study can affect the development of flight techniques for aircraft tactical maneuvers and the modification of air force operational manuals.

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