• KIPE Magazine
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• v.23 no.6
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• pp.51-57
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• 2018

• KIPE Magazine
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• v.23 no.6
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• pp.65-71
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• 2018

• The Transactions of The Korean Institute of Electrical Engineers
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• v.63 no.4
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• pp.559-564
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• 2014

A microgrid as a small scale power system is operated by the grid-connected mode and islanded mode. It is anticipated that the battery energy storage system (BESS) is able to be applied to the microgrid for stable power control, such as tie-line and smoothing control in the grid-connected mode and voltage and frequency control in the islanded mode. In this paper, a digital signal processor (DSP), Two BESS controllers based on TMS320F28335 of a microgrid are implemented and are tested to show control performance in the hardware-in-the loop simulation (HILS) system.

• Proceedings of the KIPE Conference
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• 2011.11a
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• pp.12-13
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• 2011

본 논문에서는 동기전동기의 제어기 Model, 모터 Model, 실제 모터를 시뮬레이션 및 구동하기 위해서 RT-Lab을 이용하여 HILS를 구현하였다. 제어기 Model과 모터 Model은 MATLAB/Simulink를 이용하여 구현하였다. 모터 Model과 실제모터의 동작을 통해 제어기의 성능을 검증하였다. Motor Model은 실제모터와 선택적으로 동작시켜 실제모터와 유사하게 만들 수 있음을 확인하였다. 모든 Model 및 PWM의 동작 주기는 20kHz로 동작하며, 이를 검증을 하기 위해 400[W] 표면부착형 동기모터 다이나모 장치와 3상 모터 드라이버를 제작하여 성능을 확인하였다.

• 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.

• 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.

• Proceedings of the KIEE Conference
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• 2005.07d
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• pp.2540-2542
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• 2005

This paper proposed the new HILS technique called Injection Method for Inertial Sensor Verification of high maneuvering missiles. The performance of Inertial Sensor is verified by Injection Method and traditional FMS Method. After all, Injection Method for Inertial Sensor has capability for various scenario and critical condition test.

• 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.

• 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.