• Journal of Institute of Control, Robotics and Systems
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• v.16 no.9
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• pp.905-912
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• 2010

Modern version of advanced supersonic fighter have ATCS (Automatic Thrust Control System) to maximum flight safety, fuel efficiency and mission capability the integrated advanced autopilot system such as TFS (Terrain Following System), GCAS (Ground Collision Avoidance System) and AARS (Automatic Attitude Recovery System) and etc. This paper addresses the design and verification of ATCS based on advanced supersonic trainer in HILS (Hardware In the Loop Simulator) with minimum hardware modification to reduce of development cost and maintain of system reliability. The function of ATCS is consisted of target speed hold mode in UA (Up and Away) and angle of attack hold mode in PA (Power Approach). The real-time pilot evaluation reveals that pilot workload is minimized in cruise and approach flight stage by ATCS.

• Journal of Institute of Control, Robotics and Systems
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• v.14 no.8
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• pp.824-836
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• 2008

Relaxed static stability(RSS) concept has been applied to improve aerodynamic performance of modern version supersonic jet fighter aircraft. Therefore, flight control systems are necessary to stabilize an unstable aircraft, and provides adequate handling qualities and achieve performance enhancements. Standard FCSDVP (Flight Control System Design and Verification Process) is provided to reduce development period of the flight control system. In addition, if this process is employed in developing flight control system, it reduces the trial and error for development and verification of flight control system. This paper addresses the flight control system design and verification process for the RSS aircraft utilizing design goal based on military specifications, linear and nonlinear system design and verification based on universal software, handling quality test based on HILS(Hardware In-the-Loop Simulator) environment, and ground and flight test results to verify aircraft dynamic flight responses.

• Journal of Institute of Control, Robotics and Systems
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• v.14 no.12
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• pp.1244-1252
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• 2008

This paper presents the analysis results obtained by the flight test of reconfiguration flight control system for an aircraft. The reconfiguration flight control system was designed by using control allocation scheme that automatically distributes the demanded control moments determined by control law to each actual control surface. In this paper, some control allocation algorithms for reconfiguration control of general aircraft with redundant control surfaces are summarized and their performance evaluation results through nonlinear simulation and Hardware-In-the-Loop-Simulation (HILS) test are shown. Also, Unmanned Aerial Vehicle (UAV) system adopted as a platform for the flight test of reconfiguration flight controller and the implementation procedure of reconfiguration flight controller into real-time UAV system were introduced. Finally, flight test results were analyzed.

• Journal of Aerospace System Engineering
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• v.3 no.3
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• pp.32-38
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• 2009

An autothrottle module for small jet aircraft Fly-By-Wire system was developed. The autothrottle was designed to be composed of DC geared motor and electro-magnetic clutch that enables smooth manual/auto switching. A controller was designed for simple position control using ON/OFF control method with a commercial motor driver. The autothrottle developed was installed in the cockpit mockup and interfaced to the flight control computer for the HILS test. The performance test proved that the throttle lever follows well the command signal from the flight control computer.

• Journal of Navigation and Port Research
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• v.31 no.5 s.121
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• pp.325-332
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• 2007

This study develops a control algorithm on berthing/unberthing system using a joystick for ships with thrusters and a rudder. A nonlinear mathematical model for low speed maneuvering of typical container ships is used to develop a MIMO(multi-input multi-output) nonlinear control algorithm for velocity feedback joystick control. Also a virtual HILS(hardware in the loop simulation) software program for berthing/unberthing is developed to test the performance of the nonlinear and a PID control algorithm. The program is developed using LabWindow/CVI, and a user can see current position and desired trajectory of ship in a monitor, then he can control forward and yaw velocities of a ship using a joystick. The simulation results show that the nonlinear mfd the PID controller have superior performance over a simple open loop joystick control algorithm.

• Journal of the Korea Society for Simulation
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• v.16 no.4
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• pp.23-31
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• 2007

Anti-Air Warfare(AAW) functionality of the naval combat system is the key functionality to ensure the ship's survivability. We have applied a novel method using model-based-simulation to analyze and design AAW functionality of the Patrol Killer Experimemnt Combat System. In this approach, an AAW functional model is described with the FSM(Finite State Machine) and directly executed for the AAW simulation. After prototyping using model based simulation, Hardware In Loop Simulation(HILS) is conducted as the AAW functionality is interfaced with the other ones of the combat system for completing the integration of the system components. This incremental and iterative development approach based on the model based simulation can minimize the development risks and costs caused by the system complexity for military system, bringing out the merit of the rapid prototyping.

• 한국신재생에너지학회:학술대회논문집
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• 2006.11a
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• pp.290-296
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• 2006

Control algorithms and implementation issues for a wind turbine simulator are presented for realistic emulation of variable wind characteristics using a lab-scale motor and generator set. When the average wind speed nd turbulence level is given, the torque reference of prime mover is decided through various blocks, such as random wind speed generator, blade characteristic curves, and tower effect compensation. The variable nature of wind can be implemented and tested by not only the computer simulation but also the hardware-in-loop-simulator (HILS). Some application examples of HILS include the development and test of turbine control software for more efficient and stable operation. Feasibility of the proposed simulator has verified by computer simulations and experiment.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.24 no.1
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• pp.55-61
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• 2016

In this work a guidance and control system for an a powered ram air parafoil under wind disturbance is considered. After analyzing a 6 Dof and 9 Dof nonlinear dynamic models of the parafoil, wind effect is added to them. In order to actively respond to the wind acting on the transverse direction of the vehicle a new guidance algorithm is proposed. After a Hardware-In-the-Loop Simulation (HILS) study, flight tests are performed to demonstrate its potential under wind disturbances.

• 제어로봇시스템학회:학술대회논문집
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• 2005.06a
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• pp.1729-1734
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• 2005

The use of gantry crane systems for transporting payload is very common in industrial application. However, moving the payload using the crane is not an easy task especially when strict specifications on the swing angle and on the transfer time need to be satisfied. To overcome this problem, this paper describes development of an intelligent gantry crane system based on the mechatronic design. A lab-scale gantry crane is designed and then its intelligent controllers are developed. Fuzzy logic controllers are adopted, designed and implemented for controlling payload position as well as the swing angle of the gantry crane. The performance of the intelligent gantry crane system is evaluated on a hardware-in-the-loop simulation (HILS) environment. Moreover robustness of the proposed system is also evaluated. The result shows that the intelligent gantry crane system designed based on the mechatronic design approach has better performance compared with the automatic gantry crane system controlled by classical PID controllers. Moreover simulation result shows that the intelligent gantry crane system is more robust to parameter variation than the automatic gantry crane system.

• 제어로봇시스템학회:학술대회논문집
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• 2000.10a
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• pp.105-105
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• 2000

In this paper, an integrated control of the semi-active suspension system using a reduced full-car model is investigated. By including the reduced full-car dynamics in the control law, the semi-act ive suspension system is able to control not only the vertical acceleration but also the roll and pitch mot ions of the car body, which is not Possible with a quarter-car model or a half-car model. The damping forces for the semi-active dampers are designed to track the damping forces of the skyhook controller designed from the reduced full car dynamics. Computer simulations and experimental results using a real car are also included.