• 한국항공우주학회지
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• 제43권6호
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• pp.533-539
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• 2015

최근 다수의 유도무기는 공간 효율성을 위해 접힘 날개를 적용하고 있다. 날개의 전개과정 중에 작용하는 공기력은 날개 전개 성능에 많은 영향을 주기 때문에, 일반적으로 CFD 해석을 통하여 공력계수를 산출한다. 이와 다른 방법으로 Missile Datcom을 이용하여, 날개의 전개 과정을 날개 상반각 변화로 가정하여 입력하면, 빠르고 간편하게 CFD 해석 결과와 근접한 공력계수 산출이 가능하다. 또한 동체에 돌출부가 존재하는 경우 날개를 서로 포개어 접어야 되는 상황이 발생할 수 있고, 전개과정 중에 한쪽 날개가 다른 쪽 날개의 전개 과정을 방해 또는 도와주게 되는 구속효과가 발생하게 된다. 따라서 공기력 효과 및 구속 효과를 고려하여 날개의 초기구속 여부 판단 기준과 전개 거동 특성을 수식화 하였고, 날개 전개 성능 분석을 수행하였으며, 성능 분석 결과를 풍동 시험 데이터와 비교하였다. 날개의 전개 성능은 풍동시험에서 나타난 전개 취약 풍향을 정확하게 예측하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년도 학술대회
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• pp.245-250
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• 2008

For simulation of a wing unfolding motion for the various aerodynamic conditions, equation governing unfolding motion and moments applying to the unfolding wing were modelled. Aerodynamic roll moment consists of the static roll moment and the damping moment, which were obtained through wind tunnel tests and numerical analyses respectively. Panel method was used to compute the roll damping coefficient with twisted wing, whose deflection angle was equivalent to angle of attack due to the deployment motion. Roll damping coefficient is a function of angle of attack, sideslip angle, and deployment angle but not of angular velocity of deployment. Simulation with aerodynamic damping model gave more similar deployment time compared to wing deployment test results.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2008년 추계학술대회논문집
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• pp.245-250
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• 2008

For simulation of a wing unfolding motion for the various aerodynamic conditions, equation governing unfolding motion and moments applying to the unfolding wing were modelled. Aerodynamic roll moment consists of the static roll moment and the damping moment, which were obtained through wind tunnel tests and numerical analyses respectively. Panel method was used to compute the roll damping coefficient with twisted wing, whose deflection angle was equivalent to angle of attack due to the deployment motion. Roll damping coefficient is a function of angle of attack, sideslip angle, and deployment angle but not of angular velocity of deployment. Simulation with aerodynamic damping model gave more similar deployment time compared to wing deployment test results.

• 한국군사과학기술학회지
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• 제27권2호
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• pp.277-284
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• 2024

For the high reliability of guidance weapon, it is important to maintain the stable supply voltage for guidance system while the bomb is gliding. However, the DC motor drive for guidance control in the low temperature can lead to the critical voltage drop due to a large inrush current. In this paper, we propose the wing deployment logic design to enhance the guidance system stability. To derive the stable drive logic based on PWM, we controlled the duty cycles for input voltage of DC motor in low temperature. The initial duty cycle was set to 40 % to relieve the inrush current. Moreover, the proper time, which is less than 1 second for controlling duty cycles, was determined by the iterative wing deployments of guidance kit. Finally, the validity of proposed logic was confirmed from the result the maximum voltage drop for the wing deployment was decreased by 23 %.

• 한국군사과학기술학회지
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• 제22권3호
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• pp.353-359
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• 2019

In this study, a aerodynamic loads prediction to design a deploying device of folded fin was introduced. In general, resultant flow conditions around the fin are used to obtain deploying moments and required energy. However, when it comes to the air vehicles launched from a mobile platform, more specific flow conditions can be provided. With the conditions, the design criteria can be calculated more realistically. In this study, therefore, aerodynamic moments induced by aerodynamic loads and energy required in deployment were calculated using wind-over-deck(WOD) velocity, combination of a platform velocity and a wind velocity. For the calculation, wind tunnel test was conducted on various angle of attack, side slip angles, and folding angles. It was found that the aerodynamic moments and the energy required in deployment using the non-uniform flow due to the velocity components were less than those using the uniform flow without the components.

• 한국항공운항학회지
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• 제19권3호
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• pp.1-9
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• 2011

In this paper, a conceptual design process for Very Light Jet aircraft has been proposed incorporating aircraft safety certification. During the proposed design process, satisfaction of the airworthiness certification for an intermediate resulting aircraft configuration is evaluated and then redesigns are carried out if necessary and until the designed aircraft configuration satisfies the airworthiness requirements. Certification database has been developed using FAR 23, AC 23, KAS 23, and CS 23 as the airworthiness certification. Based on the developed certification database Design Certifcation Related Table has been produced to use the airworthiness requirements as design constraints in the propsed design process. Using Quality Function Deployment the design variables for a redesign are carefully selected and a design optimization is performed. To demonstrate the feasibility and effectiveness of rapid aircraft conceptual design using the proposed approach, a Very Light Jet design optimization including a redesign of wing flap has been performed and the design results have been presented.

• 한국의류학회지
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• 제24권5호
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• pp.714-723
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• 2000

The purpose of this study is to develop functional and sensible brassiere for middle-aged women. As a methodology, engineering design process, especially, QFD(Quality Function Deployment) was adopted to translate consumer's needs into product design parameters. Wearing tests of commercial brassiere were performed for the development o subjective measurement scale. The environmental condition was controlled at 28$\pm$1$^{\circ}C$, 65$\pm$3%RH. As results, subjective measurement scale and dimension for the evaluation of sensible brassiere were extracted from factor analysis. Four factors were fitting, aesthetic property, pressure sensation, displacement of brassiere due to movement. Regression equations with the subjective evaluation descriptors were developed for the prediction of wearing comfort of brassiere. (R2=.82) The most critical design parameter was wire-related property and second one was stretchability of main material of brassiere. Also, wearing comfort of brassiere was affected by the interaction of initial stretchability of wing and support of strap.

• 한국항행학회논문지
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• 제26권5호
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• pp.312-318
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• 2022

현재 대한민국은 인구절벽 현상에 의한 병역자원의 감소 문제에 직면해 있으며 이에 대응하기 위해 군 구조 개편 및 전력 구조 변화를 추구하고 있다. 육군은 이런 상황 변화에 대한 대응으로 미래 전장을 주도할 드론봇 전투체계의 전력화를 추진하고 있다. 미래의 전장은 지휘통제, 감시정찰, 정밀타격이 결합된 통합 전장 개념으로 전환될 것이며 이러한 변화에 따라 드론봇을 포함한 무인 전투체계가 실전 배치되어, 위험도가 높고 인간이 수행하기 어려운 전투상황에 더욱 광범위하게 적용될 것이다. 본 논문에서는 이러한 변화에 대한 대응 방안의 하나로 BDI 아키텍처 기반의 의사 결정 시스템을 가진 자율행동 소프트웨어를 개발하였다. 자율행동 소프트웨어는 다 기종에 대한 적용성 확보를 위해 프레임워크 구조를 적용하였고 대상 무인기를 대대급 감시정찰 무인기로 가정하여 PC기반 환경에서 기능을 검증하였다.

• 한국군사과학기술학회지
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• 제26권1호
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• pp.83-90
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• 2023

The external store fitted to the aircraft may affect the flight characteristics and flight safety of the aircraft, which requires the analyses and testing on it. The purpose of this study is to identify and analyze types of failures that can affect the flight safety of aircraft due to the installation of external stores, and to check the flight safety of aircraft through dropping tests of the external stores. After identifying the types of failures that could affect the flight safety of the aircraft, the criticality was calculated to analyze the effect on the flight safety of the aircraft. Four types of failures were selected: unintentional dropping, failure of dropping, unintentional main wing deployment, and release of tail wing restraint of the external store, which are considered to affect the flight safety of the aircraft due to the operation of the external store. As a result of the aircraft's flight safety analysis on the failure types, the criticality requirements were met. Based on this, after obtaining the airworthiness certification, the drop test was successfully performed to confirm the flight safety of the aircraft by mounting an external store on the aircraft. However, in addition to the four hazards carried out in this study, the real external stores of the military aircraft may have various factors affecting the flight safety of the aircraft, so further research will be needed.

• 한국ITS학회:학술대회논문집
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• 한국ITS학회 2007년도 제6회 추계학술대회 및 정기총회
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• pp.225-229
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• 2007

최근에 무선 센서 네트워크는 여러 분야에서 다양하게 활용되고 있으며 간단한 환경 모니터링 시스템에서부터 기계, 구조물, 교량, 비행기와 같은 모션 모니터링과 군사, 텔레매틱스와 같은 정보량이 많고 복잡한 시스템에 적용이 시도되고 있다. 따라서 간단한 역할만 수행하면서 저 전력으로 오랜 시간 동안 운용을 목표로 해온 무선 센서 네트워크는 어려운 작업을 수행하도록 요구되고 있다. 일반적으로 무선 센서 네트워크의 MAC 프로토콜들은 주기적으로 sleep / wake를 반복하여 필요한 에너지 소비를 줄이며 이를 Duty Cycling이라고 한다. 하지만 이러한 Duty Cycling은 sleep 구간 동안에 전송할 수 없어서 홉(Hop)이 늘어날수록 전송지연이 증가하는 단점이 있다. 이러한 전송지연은 비행기 날개, 군사, 텔레매틱스 등의 복잡한 시스템이나 교통사고위험 감지 경고 시스템과 같이 빠른 데이터 처리가 필요한 시스템에서 큰 문제점이 될 수 있다. 본 논문에서는 수신 구간을 분산 배치 알고리즘(Distributed Duty Cycling, DDC)을 통하여 무선 센서 네트워크 MAC(Media Access Control) 프로토콜에서 발생하는 전송지연을 크게 줄이는 기법을 제안한다. 제안한 알고리즘은 CC2420DBK를 이용한 필드 테스트를 통해서 검증되었으며 실험 결과를 통해서 DDC 알고리즘을 통해서 전송지연을 크게 줄이고 에너지 소비 또한 감소한다는 것을 확인 할 수 있다.