• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.9
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• pp.88-93
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• 2003

This Paper described the simulation program development for helicopter. In the design of flight control system to accomplish some special missions like UAV, it is important to minimize the execution time obtaining a linear model from nonlinear model that is used for design of controller. The first step for this kind of purpose is to complete a nonlinear model that contains full dynamic characteristics. The second step is to get the trim values that are obtained from the nonlinear model by solving an algebraic equation. And then stability and control derivatives are derived through hovering to forward flight by numerical perturbation that will be used for linear model for a specified flight condition. The software program(HeliSim) is developed by using MATLAB GUI and will provide easy modeling procedure. The suggested method in this paper is much more simpler than any other method like a fully scale helicopter model. The advantage of our suggested method will reduce the computational time due to simple formula to extract a linear model from nonlinear model that will be beneficially used for flight control system of unmanned helicopter by some reduction of computational load.

• Journal of Astronomy and Space Sciences
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• v.34 no.3
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• pp.225-235
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• 2017

The energy balance in a satellite needs to be designed properly for the satellite to safely operate and carry out successive missions on an orbit. In this study, an analysis program was developed using the MATLAB(R) graphic user interface (GUI) for nanosatellites. This program was used in a simulation to confirm the generated power, consumed power, and battery power in the satellites on the orbit, and its performance was verified with applying different satellite operational modes and units. For data transmission, STK(R)-MATLAB(R) connectivity was used to send the generated power from STK(R) to MATLAB(R) automatically. Moreover, this program is general-purpose; therefore, it can be applied to nanosatellites that have missions or shapes that are different from those of the satellites in this study. This power simulation tool could be used not only to calculate the suitable power budget when developing the power systems, but also to analyze the remaining energy balance in the satellites.

• Proceedings of the Acoustical Society of Korea Conference
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• 1998.06c
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• pp.361-364
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• 1998

주파수 합성기는 주로 PLL을 이용하여 설계하는데, PLL(Phase-lock loop)이란 출력신호 주파수를 항상 일정하게 유지하도록 구성된 주파수 부귀환 회로로써 기본적인 구성은 위상출력기, 저역통과필터, 전압 제어 발진기로 이루어진다. 이런 PLL의 기본적인 구성에 프로그래머블카운터를 VCO의 출력단에 부가하여 구성한 형태가 주파수합성기이다. 이 주파수합성기의 출력을 프로그래머블 디바이더에 입력하기 전에 주파수를 낮출 필요가 있는데, 현재 슈퍼헤테로다인 다운 컨버터방식과 프리스케일러방식과 펄스 스웰로 카운터를 사용하는 방식 등의 3가지 방법이 있다. 본 논문에서는 펄스 스웰로 카운터 방식의 주파수 합성기를 MATLAB의 GUI환경과 병행하여 시뮬레이션 과정을 통한 동작특성을 이해하고, 한 화면에서 이루어지는 조작에 의해 모든 주파수 합성기의 요소를 관찰할 수 있도록 모델링하였다. 그리고, 모델링한 주파수합성기와 실제 주파수합성기에서 예상되는 출력과 비교하여 그 결과에 있어서 얼마나 유사한지 살펴보았다.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.64 no.6
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• pp.878-884
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• 2015

In this paper, Power Management System(PMS) simulator for Liquid Nature Gas Carrier(LNGC) is developed. Major components of power system for LNGC, such as generator, diesel engine and governor, transformer, circuit breaker, and 3 phase loads models are built based on MATLAB/SIMULINK. With these designed major parts, PMS simulator modeling is carried out. Based on MATLAB/Graphical User Interface, PMS simulator control for LNGC, and Human Machine Interface for monitoring is designed. PMS simulator for LNGC carries out simulation according to sequence of characteristics analysis. By comparing results of predicted simulation for each sequence to that of characteristics analysis, the reliability of PMS simulator for LNGC will be verified.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2002.04a
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• pp.33-34
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• 2002

성능해석 프로그램은 가스터빈 엔진의 개발단계에서는 성능시험의 대체로 개발 비용의 절감과 실제 시험이 어려운 영역의 성능해석을 통해 보다 광범위한 운용 범위의 성능을 파악할 수 있도록 하며 엔진의 운용단계에서는 엔진 상태를 실시간으로 파악하여 엔진 상태에 따른 적절한 정비를 통해 수명 연장과 운용비용 절감의 효과를 가져온다. 이러한 성능해석 프로그램의 중요성은 선진국에서는 이미 70년대부터 부각되어 그 연구가 활발히 진행되어져 왔으며 아날로그 컴퓨터, 하이브리드 컴퓨터, 디지털 컴퓨터 등 다양한 형태로 개발되어 왔다. 최근에는 퍼스날 컴퓨터의 발달로 보다 정밀한 해석이 가능한 프로그램들이 많이 개발되고 있으며 보다 사용자에게 친숙한 GUI(Graphical User Interface) 방식이나 Object-Oriented 방식의 프로그램 개발에 관한 연구가 활발히 이루어지고 있다. 또한 보다 빠르고 복잡한 성능해석이 가능한 프로그램 개발을 위해 MATLAB, MATRIX-x 등 공학용 소프트웨어를 이용한 프로그램들이 개발되고 있다.

• Proceedings of the KIEE Conference
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• 2004.07d
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• pp.2562-2564
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• 2004

This paper addresses a simulation for the Ethernet based data transmission between the CIC(Centralized Traffic Control System) and the SCADA(Supervisory Control and Data Acquisition) system. Fame error rate and throughput are calculated and compared for the two cases that the CTC/SCADA has an extra error control scheme besides the internal CRC32 of the Ethernet and that no extra error control has been done. Simulation program is constructed with the Matlab and the Matlab GUI and then converted into a stand-alone $c^{++}$ program to be used on any non-Matlab environments.

• Proceedings of the KSR Conference
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• 2003.10c
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• pp.183-189
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• 2003

In this paper a simulation was done to verify performance of a message transmission protocol which interfaces LDTS(Local Data Transmission System) with EIS(Electronic Interlocking System), After a stage of analyzing link specifications between LDTS and EIS, transmission messages and messaging formats, simulation parameters were extracted, applied to the error control schemes such as ARQ, FEC, HARQ, and therefrom throughputs and various performance indices were analyzed Simulation program was constructed with Matlab and Matlab GUI and then converted into a stand-alone c++ program to be used on any non-Matlab environments.

• Proceedings of the KAIS Fall Conference
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• 2007.11a
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• pp.148-151
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• 2007

본 논문은 표면 부착형 영구자석 동기전동기 벡터제어 시스템의 속도 및 전류제어와 과변조 기법을 MATLAB/SINULINK의 TI C2000 임베디드 타겟을 이용한 모델기반 제어기 설계방법으로 구현하였고, Mathwork사에서 제공하는 Demo 프로그램의 속도 및 전류제어와 과변조 기법을 비교하여 보았다. 먼저 각 제어기에 대한 구조를 설명하고, 각각의 응답에 대한 시뮬레이션과 실험을 통해 비교 검증하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.11
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• pp.1132-1138
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• 2008

A program that can simulate gas generator after burning liquid rocket engines was developed along with presenting the characteristics of the engines. The program was written in Matlab and used GUI interface so that many users can use it without any difficulties. The results of the program was compared with the real engine which was developed by the LRE advanced country. Most of the parameters concurred within 1% error expect for the pressure at the turbopump. The reasons of the large differences were supposed that pressure decreases at the schematics were smaller than that of the real engines.

• Journal of Satellite, Information and Communications
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• v.6 no.2
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• pp.10-14
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• 2011

This paper suggests the method to calculate radiation limit of ISM(Industrial Scientific Medical) equipment in order to protect radio device in the situation that ISM equipment and radio device are operated in near distance. The factor for correction and protection ratio which is need for protecting radio device were considered to calculate radiation limit of ISM equipment. Also, the scenario which is required to limit radiation power of ISM equipment was referred and the S/W for calculation of radiation limit was developed by using GUI(Graphical User Interface) on Matlab. The suggested method for calculation of radiation limit of ISM equipment will be used to protect radio device from ISM equipment.