• 한국경영과학회지
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• 제39권2호
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• pp.37-48
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• 2014

Fighter squadron flight scheduling is the integrated air operation plan that is an important role for improving pilot's flight skill and maintaining combat readiness by efficient using available all air resources including pilot, aircrafts, air-weapons, fuel and supporting facilities etc. Korea airforce, however, has a limit as to an effective flight operation due to manual flight scheduling with scheduler's own experience and intuition. Therefore, in our study, we propose the optimization model of flight scheduling based on mixed integer programming. This model includes several constraints of realistic and essential quantified data related with flight schedule and can assign appropriate pilots optimally which are distinctive three type's solutions : flight, alert and duty crew schedules. Proposed solution method can be improved pilot's capability and allocated further air resources systematically and efficiently. In addition, it can be reduced a workload of flight scheduler and minimized obstructed factors of flight safety. Finally, we demonstrate the experiment's results for the check of efficiency and validity of this model.

• 한국세라믹학회지
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• 제47권6호
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• pp.534-539
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• 2010

$HfB_2$-HfC composites were prepared by reactive hot pressing using Hf and $B_4C$ at temperatures of 1800 and $1900^{\circ}C$ for 60 min under 32 MPa in an Ar atmosphere. The reaction sequences of the $HfB_2$-HfC composite were studied through series of pressureless heat treatments ranging from 800 to $1600^{\circ}C$. The effect of size reduction of the starting powders on densification was investigated by vibration milling. Fully dense $HfB_2$-HfC composites were obtained by size reduction of the starting powders via vibration milling. The oxidation behaviour of the $HfB_2$-HfC composites at $1500^{\circ}C$ in air showed formation of a non-protective $HfO_2$ scale with linear mass gain. Examination of the mechanical properties showed that particle size reduction via vibration milling also led to improved flexural strength, hardness and fracture toughness.

• 문화기술의 융합
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• 제8권4호
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• pp.173-179
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• 2022

2014년 돈바스 분쟁과 2022년 우크라이나-러시아 전쟁 사례를 통해 제공권은 더 이상 공군에 의해서만 확보할 수 있는 것이 아님을 경험하고 있다. 기존의 공군이 수행하던 원거리 감시정찰과 타격은 드론과 미사일로 대체할 수 있으며 적의 공중공격은 판치르와 휴대형 대공미사일 같은 방공무기체계로 국지제공권을 장악하여 지상군의 자유로운 기동 작전을 수행할 수 있다. 즉, 지금처럼 공군과 해군이 원거리 작전을 통해 제공권을 장악하는 것이 훨씬 유리하며 지상군은 이들을 지원해주는 작전개념이 더욱 적절하다. 따라서 본 연구는 이러한 제공권 작전 수행체계에 대해 값비싼 전투기에 집중하기보다 비용 대 효과성 측면을 고려하여 방공무기체계, 드론, 미사일, 정밀유도 포탄 등을 병행 발전시켜 적의 공중공격에 신속히 역공할 수 있도록 제공권 작전 수행체계에 대한 시사점을 제공하는 것이다.

• 전기전자학회논문지
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• 제24권1호
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• pp.178-185
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• 2020

본 논문에서는 미래 LAN 기반 디지털 변전소 보호를 위하여 정밀 시각동기 기반 동기 샘플링 구조를 적용한 계통 구성 IED(Intelligent Electronic Device)의 HW/SW 플랫폼을 제안하였다. 제안한 플랫폼은 전력계통 자동화를 위한 표준인 IEC 61850 프로토콜 및 IED 간 정밀 시각동기를 위한 IEEE 1588 Precision time protocol 통합 소프트웨어가 적용되었으며, Synchronized reference signal을 이용한 IED 간 동기 샘플링 구조를 적용하였다. 이는 미래 IEC 61850 기반 디지털 변전소에 적용될 네트워크 기반 데이터 송수신 환경에서 IED 간 동기 측정된 계전 데이터를 제공하게 함으로써, 네트워크 기반 분산 측정 데이터를 이용한 새로운 보호 및 제어방식을 적용할 수 있는 토대를 제공할 것으로 기대된다. 제시한 플랫폼 기술의 타당성 및 성능을 측정하기 위하여 TMDXIDK572 멀티코어/멀티프로세서 EVM(Evaluation Module)을 기반으로 구현하였으며, 성능 시험 환경을 구성하여 제시한 플랫폼의 시각동기 성능 및 동기 샘플링 기능의 동작을 확인하였다.

• Selected Papers of The Society of Naval Architects of Korea
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• 제2권1호
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• pp.29-46
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• 1994

In this paper, the effect of a skirt deformation on the responses of an Air Cushion Vehicle in waves is investigated. The air in the bag and plenum chamber is assumed to be compressible and to have a uniform pressure distribution in each volume. The free surface deformation is determined in the framework of a linear potential theory by replacing the cushion pressure with the pressure patch which is oscillating and translating uniformly. And the bag-finger skirt assumed to be deformed due to the pressure disturbance while its surface area remained constant. The restoring force and moment due to the deformation of bag-finger skirt from equilibrium shape is incorporated with the equations of heave and pitch motions. The numerical results of motion responses due to various ratios of the bag and cushion pressure or bag-to-finger depth ratios are shown.

• Selected Papers of The Society of Naval Architects of Korea
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• 제2권1호
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• pp.140-155
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• 1994

The hydrodynamic problem is treated here when a pressurized bag is submerged partially in the water and the end points of it oscillate. SES(Surface Effect Ship) has a bag filled with pressurized air at the stern in order to prevent the air leakage, and the pitch motion of SES is largely affected by the hydrodynamic force of the bag. The shape of a bag can be determined with the pressure difference between inside and outside. Once the hydrodynamic pressure is given, the shape of a bag can be obtained, however in order to calculate the hydrodynamic pressure we should know the shape change of the bag, and vice versa. Therefore the type of boundary condition on the surface of a bag is a moving boundary like a free surface boundary. The present paper describes the formulation of this problem and treats a linearized problem. The computations of the radiation problem for an oscillating bag are shown in comparison with the case that the bag is treated as a rigid body. The hydrodynamic forces are calculated for various values of the pressure inside the bag and the submerged depth.

• 한국해양공학회지
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• 제21권3호
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• pp.1-7
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• 2007

In this study, the heat balance test of an engine was conducted, and the heat released to coolant is measured and corrected using a power adjustment factor for high fuel temperature to simulate heat rejection of the engine. An engine-converter matching simulation program which can compute the engine speed, transmission output speed, transmission input and output power is developed from the vehicle, transmission and engine performance curve. With this information and the engine heat rejection characteristics, the engine and transmission heat rejection rates can be determined at given condition. In analyzing the air mass flow, a sub program computing the air mass flow rate from the equation of the pressure balance between cooling fan static pressure rise and pressure losses of cooling components is developed.

• 한국분말재료학회지
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• 제11권2호
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• pp.130-136
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• 2004

The passivation and oxidation process of tungsten and molybdenum narlopowders, produced by electrical explosion of wires was studied by means of FE-SEM, XPS. XRD, TEM, DIA-TGA and sire distribution analysis. In addition, the phase transformation of W and Mo nanopowders under oxidation in air was investigated. A chemical process is suggested for the oxidation of W and Mo nano-particles after a comprehensive testing of passivated and oxidized powders.

• 설비공학논문집
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• 제17권6호
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• pp.587-595
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• 2005

The heat and flow characteristics in a parallel-flow heat exchanger were examined numerically to obtain its optimal design variables. A desirability function approach was introduced to optimize its performance with respect to the design parameters over the design domain. By varying the importance of heat transfer and pressure drop which are out put variables, the optimal values of the design parameters are examined. As a result, the us-age of the desirability function is very effective for the optimization of the design variables in a heat exchanger since the changes of optimal values are physically appropriate by varying the importance of each output variable.

• 한국산학기술학회논문지
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• 제18권8호
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• pp.41-47
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• 2017

새로운 기술의 도입과 정교함이 더해진 최근의 지상무기가 지능형 포탄의 발달로 이어졌으며 주요 선진국의 관심을 이끌었다. 본 연구에서는 회전운동을 하는 비행체에 대한 공력 데이터를 확보하기 위해 BLU-103 모델을 통한 전산유체역학해석을 수행하였다. 먼저 회전하는 비행체의 정상해석 기법을 모사하기 위해 동체는 고정시키고 주변의 공기를 회전시켜 동체가 회전 하는 것과 같은 원리를 이용하였다. 회전운동 하는 비행체의 공력 타당성을 검토하기 위해 단순형상에 대해 받음각 0도에서 90도, 옆 미끄럼각 0도에서 90도까지 각각 30도 간격으로 고려하여 해석을 수행하였다. Drag book에 제시되어 있는 항력 값을 통해 단순모델에 대한 항력계수가 1.0 ~ 1.2의 정량적 결과를 만족한다는 사실을 확인하였다. 단순형상에서의 해석조건을 통해 검증 된 유효한 입력 값을 동일하게 실제형상에 적용하여 회전 유무에 따른 공력데이터베이스를 구축하였고 경향성을 분석하였다. 분석 결과 단순모델 뿐 아니라 실제 모델의 회전 시 축력계수, 수직력 계수, 측력 계수가 증가한다는 사실을 확인 하였고 특히 수직력 계수의 영향이 크게 작용되어 비행에 유리할 것이라 판단하였다.