• 한국게임학회 논문지
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• 제6권4호
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• pp.79-87
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• 2006

본 논문은 기계학습 기법을 이용한 게임 캐릭터를 제어하는 엔진을 설계하고 구현하는 것을 제안한다. 제안된 엔진은 실제 게임에서 상황 데이터를 추출하여 지식 데이터로 사용하므로 지능 캐릭터의 행동 패턴을 게이머들이 쉽게 인식하지 못하는 장점이 있다. 이를 위하여 상황 데이터를 추출하여 학습하는 모듈과 임의의 상황 데이터에 대하여 최적의 상황 제어를 판단하는 시험 모듈을 개발하는 것을 제안하였다. 구현된 엔진은 FEAR에 이식되고 Quake2 게임에 적용되었다. 또한 개발된 엔진의 올바른 동작과 효율성을 위하여 다양한 실험을 하였다. 실험으로부터 개발된 엔진이 올바르게 동작할 뿐만 아니라 제한된 시간 내에 효율적으로 동작함을 알 수 있었다.

• 한국유체기계학회 논문집
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• 제18권1호
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• pp.37-43
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• 2015

A Beta-type Stirling engine is developed and tested on the operation stability and cycle performance. The flow rate for cooling water ranges from 300 to 1500 ml/min, while the temperature of heat source changes from 300 to $500^{\circ}C$. The internal pressure, working temperatures, and operation speed are measured and the engine performance is estimated from them. In the experiment, the rise in the temperature of heat source reduces internal pressure but increases operation speed, and overall, enhances the power output. The faster coolant flow rate contributes to the high temperature limit for stable operation, the cycle efficiency due to the alleviated thermal expansion of power piston, and the heat input to the engine, respectively. The experimental Stirling engine showed the maximum power output of 12.1 W and the cycle efficiency of 3.0 % when the cooling flow is 900 ml/min and the heat source temperature is $500^{\circ}C$.

• 한국유체기계학회 논문집
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• 제18권1호
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• pp.29-36
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• 2015

Recently, Stirling engines are emerging as a key device for power conversion of renewable energy or waste energy. This study develops a LTDSE(Low Temperature Differential Stirling Engine) using a water spray for higher heat transfer and performs load performance tests for various flow rates and temperatures of hot water spray for variable engine loads emulated by a mechanical friction device. Internal temperature and pressure, working frequency and inlet and outlet temperature of the supply water are measured. As a result, the increases in flow rate and temperature of hot water respectively enhance the power output, efficiency and the working frequency, while the increasing engine load leads to decreases in working frequency but increases in the pressure amplitude. Eventually, it is revealed there exists a maximum shaft power of the test engine.

• 대한원격탐사학회:학술대회논문집
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• 대한원격탐사학회 2003년도 Proceedings of ACRS 2003 ISRS
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• pp.189-191
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• 2003

The types of service using location information are being various and extending its domain as wireless internet technology is developing and its application part is widespread, so it is prospected that LBS (Location-Based Services) will be killer application in wireless internet services. The MODB (Moving Object Database) stores and manages very large current/ past moving object data, so it is very important part in LBS platform. The performance of LBS platform is tightly depending on the performance of this MODB. The other important part is alerting engine in LBS platform, which is system to transmit various value-added information or notify emergency information to mobile phone after triggering specified events. This alert engine is supported as extended function of MODB, that is to say, the alerting function is closely related with MODB. So alert cartridge on MODB must provide not only moving point triggering about going into, going out specified geographical area but also batch alerting about nearest neighbor from specified geographical area. In this paper, we study of extended part on MODB to support the alert engine. And we design alert engine cartridge on MODB before implementing the system.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2008년 영문 학술대회
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• pp.173-181
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• 2008

Gas turbine engine for aircraft are usually operated at the altitude condition which is quite different from the ground condition. In order to measure the precise performance data at the altitude condition, the engine should be tested at the altitude condition by a real flight test or an altitude simulation test with an altitude test facility. In this paper describes the design of altitude test facility for turbo shaft engine. This facility will be located in test cell #2 at the Korea Aerospace Research Institute. Test Cell #2 will be used for altitude testing engines with mass flow rate up to 40kg/s and inlet temperatures in the range from $-65^{\circ}C$ to $200^{\circ}C$. The existing compressor/exhauster station with heater & cooler system will be used to simulate altitude conditions in Test Cell #2.

• 동력기계공학회지
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• 제12권1호
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• pp.41-46
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• 2008

The primary objective of this study is to truly understand exciting forces of the in-line 4 cylinders engine. Exciting forces of the engine apply a source of the vehicle NVH(Noise, Vibration, Harshness). To understand exciting forces, first was governed theoretical equations for single cylinder engine. And this theoretical equations was programming using MATLAB software. To compare theoretical analysis value, was applied MSC.ADAMS software. To determined the specification of engine(2,000cc, in-line 4) was applied ADAMS/Engine module. And this specification for engine was applied ADAMS/View and MATLAB software. The geometry model for ADAMS/View analysis was produced by the 3-D design modeling software. After imported 3-D model, each rigid body was jointed suitable. Under idle speed for engine, was analysed. The results of analysis are fairly well agreed with those of three analysis method. Using MATLAB software proposed in this study, engine exciting fores can be predicted. Also using ADAMS/Engine module and ADAMS/View software, engine exciting forces can be predicted.

• International Journal of Automotive Technology
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• 제8권1호
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• pp.93-102
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• 2007

The frontal crash optimization of an engine room member using the response surface method was studied. The engine room member is composed of the front side member and the sub-frame. The thicknesses of the panels on the front side member and the sub-frame were selected as the design variables. The purpose of the optimization was to reduce the weight of the structure, under the constraint that the objective quantity of crash energy is absorbed. The response surface method was used to approximate the crash behavior in mathematical form for optimization procedure. To research the effect of the regression method, two different methodologies were used in constructing the response surface model, the least square method and the moving least square method. The optimum with the two methods was verified by the simulation result. The precision of the surrogate model affected the optimal design. The moving least square method showed better approximation than the least square method. In addition to the deterministic optimization, the reliability-based design optimization using the response surface method was executed to examine the effect of uncertainties in design variables. The requirement for reliability made the optimal structure be heavier than the result of the deterministic optimization. Compared with the deterministic optimum, the optimal design using the reliability-based design optimization showed higher crash energy absorption and little probability of failure in achieving the objective.

• 동력기계공학회지
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• 제22권1호
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• pp.5-10
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• 2018

In order to employ factorial design on electronically-controlled diesel engine, effects of 5 factors on specific fuel consumption, nitrogen oxides and carbon monoxide were examined by fractional and full factorial design in this research. There were different results between fractional and full factorial design, then effect of variables as ambient condition and measurement of fuel consumption were confirmed. It was shown that ambient condition affected uniformly trend of nitrogen oxides and carbon monoxide. However, both ambient condition and measurement of fuel consumption had nothing to do with trend of specific fuel consumption and therefore it must be careful to employ factorial design on specific fuel consumption as response.

• 한국추진공학회지
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• 제2권1호
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• pp.88-94
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• 1998

이 연구에서는 100인승 항공기 급의 저익-주익장착나셀(wing mounted nacelle)의 추진기관 장착설계 방법을 제시하였다. 장착설계 방법을 구체적으로 설명하기 위해 세부적인 설계제한조건(design constraint)과 설계요구조건(design requirement and objectives)을 정의하고, 그러한 기준을 근거로 실례의 항공기(K100)를 사용하여 주익장착방식의 장착설계를 수행하였다. 장착설계는 간섭항력(interference drag), roll clearance, ground clearance, nose gear collapse margin, rotor burst, 연료탱크용량 등의 설계제한사항들을 고려하여 엔진성능을 만족시킬 수 있는 최적의 나셀 장착위치(spanwise, FS, WL)와 장착각도(toe-in, incidence, droop angle), wing dry bay의 위치와 크기를 결정하여 향후에 개발될 주익장착방식의 추진기관 장착설계에 활용될 수 있는 설계절차를 구축하였다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2012년도 제38회 춘계학술대회논문집
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• pp.219-224
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• 2012

본 연구에서 중형 상용민간항공기 추진진기관인 분리형 노즐을 갖는 2 스풀 터보팬 엔진인 BR715-56의[1] 정상 성능모델을 구성 및 탈설계점 성능해석이 상용코드인 MATLAB/SIMULINK를[2] 이용하여 엔진성능특성과 엔진진단을 위해 수행되었다. 먼저 팬, 고압압축기, 고압터빈, 저압터빈 구성품 성능 맵들이 축척방법을 이용하여 유사성능 맵들을 축척하여 생성되었고 다음 탈설계점 성능모사 프로그램이 구성품들 간 유량과 일 조화에 의해 구성되었다. 모델은 용이한 정상 및 동적 모사와 사용자 편의의 장점을 갖는 SIMULINK 프로그램을 이용하여 개발되었다. 제안한 모델에 의한 탈설계점 해석 결과들은 다양한 작동 조건들에서 GASTURB에 의한 해석 결과들과 잘 일치함이 확인 되었다.