• 한국컴퓨터정보학회:학술대회논문집
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• 한국컴퓨터정보학회 2015년도 제52차 하계학술대회논문집 23권2호
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• pp.5-8
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• 2015

소프트웨어의 작동 중에 중대한 고장 없이 유연하게 대처할 수 있는 성질은 견고성이라 불리며 임베디드 소프트웨어에서 중요하게 여겨진다. 본 논문에서는 개발 중인 임베디드 소프트웨어의 견고성을 조기에 검증하기 위하여, 실물 시스템을 이용한 테스트가 갖는 물리적 한계를 극복할 수 있는 Software-in-the-Loop 시뮬레이션을 이용하여 개발 중인 PC에 견고성 테스팅 환경을 갖추는 방법을 제시한다. 제시한 방법은 소프트웨어의 견고성을 표현할 수 있게끔 만드는 테스트 케이스를 생성하고, 가상 시뮬레이션 환경을 구성하여 테스트 케이스를 실행함으로써 소프트웨어의 견고성을 객관적인 수치의 형태로 나타내는 방법을 보인다.

• 한국정보통신학회논문지
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• 제21권6호
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• pp.1218-1224
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• 2017

액화천연가스운반선(LNGC) 건조 시 증가하는 리스크로 인해 시스템 통합 및 안전 운용에 다양한 시나리오의 사전 시뮬레이션이 필요하다. 특히, LNGC에서 전력관리시스템은 중요한 장비이고, 전력 제어 시스템과의 오류없는 통합이 이루어져야 기대하는 성능 및 안전성이 보장된다. 본 논문에서는 LNGC에서 발생하는 오류를 개선하기 위해 Software-In-the-Loop(SIL) 기반의 PMS 테스트용 전력 발생원과 소모원에 대한 시뮬레이션 모델을 구현하였다. PMS 제어 및 검증을 위해 MATLAB/Simulink를 활용하여 수치적 물리 시뮬레이션 모델링을 수행하였고, 시뮬레이션 모델을 검증하기 위하여 시운전 시나리오를 대상으로 부하 분배 테스트를 하였다. PMS SIL 시뮬레이션은 고부가가치 선박 및 해양플랜트의 시운전, 설치, 유지보수 시장 진출에 크게 기여할 것으로 사료된다.

• 제어로봇시스템학회논문지
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• 제10권10호
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• pp.956-960
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• 2004

The Vehicle Dynamic Simulator(VDS) is a key equipment of the performance verification of attitude control subsystem and it simulates the real dynamic environment that spacecraft undergoes during mission operation. All the software models and hardware interfaces necessary for the closed-loop simulation of the spacecraft dynamics are implemented. Using VDS, KOMPAT-2 attitude control logic functions and performance was verified. In this paper, the hardware and software configurations of KOMPSAT-2 VDS was described briefly and the information flow and exchanges between software models and actual hardwares during close loop simulation was described in the systematic point of view.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1992년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 19-21 Oct. 1992
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• pp.112-116
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• 1992

In this paper, a fuzzy logic controller(FLC) is designed for the pointing loop of the spin-stabilized platform. For the fuzzy inference, a fuzzy accelerator board using the Togai InfraLogic software and digital fuzzy processor(DFP110FC) is designed, and a validation of an algorithm for fuzzy logic control is also presented. The pointing loop of the spin-stabilized platform using FLC has better performance of step responses than a proportional controller in case of same loop hain through the software simulation and the experiment of implemented hardware.

• 한국군사과학기술학회지
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• 제16권4호
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• pp.435-440
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• 2013

In this paper, a design method of the simulation program for HILS(Hardware-In-the-Loop Simulation) system is proposed. The present method consists of definition of requirements for HILS, development of specifications, and implementation of the program to satisfy the specifications. In the implementation of the program, the application of hardware interface and the concept of structural modularization are proposed to satisfy the specifications. The concepts of CSCI(Computer Software Configuration Item) and encapsulation are used for structural modularization. The proposed method was practically applied to the development of the simulation program for the efficient operation in HILS of an anti-ship missile system.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2005년도 ICCAS
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• pp.535-538
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• 2005

Today, most fixed-wing aircrafts are equipped with the antiskid brake system. It can modulate braking moments in the wheels optimally, when an aircraft is landing. So it can reduce landing distance and increase safeties. The antiskid brake system for an aircraft are mainly composed of braking moment modulators (hydraulic control valves) and brake control unit. In this paper, a Mark IV type - fully digital - brake controller is studied. For the development of its control algorithms, a 5-DOF (Degree of Freedom) aircraft landing model is composed in the form of matlab/simulink model at first. Then, braking moment control algorithms using wheel decelerations and slips are made. The developed algorithms are tested in software simulations using state-flow toolboxes in matlab/simulink model. Also, a real-time simulation systems are made, which use hydraulic brake systems of a real aircraft, pressure control valves and its controller as hardware components of HIL(Hardware In-the-Loop) simulation. Algorithms tested in software simulations are coded into the controller and the real-time landing simulations are made in very severe road conditions. The real-time simulation results are presented.

• Journal of Astronomy and Space Sciences
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• 제30권1호
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• pp.1-10
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• 2013

An integrated orbit and attitude control algorithm for satellite formation flying was developed, and an integrated orbit and attitude software-in-the-loop (SIL) simulator was also developed to test and verify the integrated control algorithm. The integrated algorithm includes state-dependent Riccati equation (SDRE) control algorithm and PD feedback control algorithm as orbit and attitude controller respectively and configures the two algorithms with an integrating effect. The integrated SIL simulator largely comprises an orbit SIL simulator for orbit determination and control, and attitude SIL simulator for attitude determination and control. The two SIL simulators were designed considering the performance and characteristics of related hardware-in-the-loop (HIL) simulators and were combined into the integrated SIL simulator. To verify the developed integrated SIL simulator with the integrated control algorithm, an orbit simulation and integrated orbit and attitude simulation were performed for a formation reconfiguration scenario using the orbit SIL simulator and the integrated SIL simulator, respectively. Then, the two simulation results were compared and analyzed with each other. As a result, the user satellite in both simulations achieved successful formation reconfiguration, and the results of the integrated simulation were closer to those of actual satellite than the orbit simulation. The integrated orbit and attitude control algorithm verified in this study enables us to perform more realistic orbit control for satellite formation flying. In addition, the integrated orbit and attitude SIL simulator is able to provide the environment of easy test and verification not only for the existing diverse orbit or attitude control algorithms but also for integrated orbit and attitude control algorithms.

• 한국정보통신학회:학술대회논문집
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• 한국해양정보통신학회 2003년도 춘계종합학술대회
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• pp.317-319
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• 2003

HILS(Hardware In-the Loop Simulation)은 임베디드(Embedded) 시스템의 개발과 시험에 많이 이용된다. 임베디드(Embedded) 시스템은 시스템의 운전 환경에서 쉽고, 철저하게 그리고 반복해서 시험할 수 없을 때 사용된다. HILS는 빠르고 경제적으로 제품을 개발하는데 유효하다. 또한 생산품이 생산을 시작한 후에 심각한 문제점들이 발견될 가능성을 상당히 줄여주어 생산품 개발 시간동안에 설계 최적화와 하드웨어/소프트웨어 디버깅을 실행하는데 도움을 준다. 본 연구는 Digital Governor의 성능을 확인하기 위해 스팀터빈 플랜트와 동기 발전기를 포함한 시뮬레이터를 HIL(Hardware In-the Loop Simulator)로 구현하였으며, 실시간으로 시스템의 응답을 확인할 수 있도록 소프트웨어로 구성하였다.

• 드라이브 ㆍ 컨트롤
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• 제16권3호
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• pp.67-74
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• 2019

The automotive market has recently been investing much time and costs in improving existing technologies such as ABS (Anti-lock Braking System) and TCS (Traction Control System) and developing new technologies. Additionally, various methods have been applied and developed to reduce this. Among them, the development method using the simulation has been mainly used and developed. In this paper, we have studied a method to develop SILS (Software In the Loop Simulation) for TCS which can test various environment variables under the same conditions. We modeled hardware (vehicle engine and ABS module) and software (control logic) of TCS using MATLAB/Simulink and Carsim. Simulation was performed on the climate, road surface, driving course, etc. to verify the TCS logic. By using SILS to develop TCS control logic and controller, it is possible to verify before production and reduce the development period, manpower and investment costs.

• 한국군사과학기술학회지
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• 제14권3호
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• pp.353-358
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• 2011

In this paper, we have introduced a Missile In the Loop Simulation(MILS) Software developed for the missile ground test, which is based on a commercial hard real-time operating system(OS) on Windows platform called as Real-Time eXtension(RTX). MILS software makes it possible to test overall system functions of a integrated missile on the ground in the flight conditions by real-time imitating its inertial data. By means of MILS, we have performed missiles ground tests, which result in successful real flight tests.