• 한국군사과학기술학회지
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• 제20권1호
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• pp.148-157
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• 2017

Miniature guided-bullet is an advanced military technology of developing guided missile which is designed to hit a target precisely while having easily carriable miniature size. A key issue of developing such system involves size reduction of the original guided missile system, and this in turn arouses stiffness issue regarding small and thin sized control surface. In this study, procedures on how to calculate the critical flutter speed of special type of control surface with the change of its dimension or material property is arranged. During this procedure, design parameters related to critical flutter speed are abridged to help preliminary design of similar structure even faster than time-consuming, and cumbersome computer analysis.

• 한국군사과학기술학회지
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• 제7권3호
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• pp.21-29
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• 2004

Numerical analysis of aerodynamic heating for KPSAM is performed using aerodynamic heating model suitable to KPSAM, which has complex flow field resulting from the spike attached to the dome, such as large separation area and the strong shock/boundary layer interaction region around reattachment point on the dome. The aerodynamic heating model is validated and modified through the comparison between the flight test measurement and the thermal analysis results. TFD temperature sensors are installed on the dome to measure surface temperature during the flight. Computation results, obtained from the heat transfer analysis on the sensors, agree well with flight test data. The aerodynamic heating model provides heat transfer rate into surface as a boundary condition of unsteady 1D/axisymmetric thermal analysis on the missile structure. The axisymmetric thermal analysis using FLUENT is more versatile than the 1D analysis and can be applied to the heating problem related with complex structures and multi-dimensional heat transfer problems such as prediction of temperature rise at contact surface of different materials.

• 한국시뮬레이션학회논문지
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• 제22권2호
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• pp.1-10
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• 2013

모델링 및 시뮬레이션 기술은 전장 환경을 고려한 실험 환경을 조성하여 무기 체계의 구성 요소에 대한 성능 분석을 실제와 유사하게 할 수 있다. 그러나 이전까지 모델링 및 시뮬레이션에서 개발된 무기체계 모델은 제한된 범위 내에서만 활용되어 확장성이 낮고 재사용성은 크게 고려하지 않았다. 이에 본 연구에서는 재사용성을 고려하여 개발된 컴포넌트에 대한 사용 검증 및 확장성 판단을 위한 검증도구와 컴포넌트를 효율적으로 관리하기 위한 관리 도구를 개발한다. 또한 이전 연구에서 설계한 유도무기체계의 동적 컴포넌트 재구성 아키텍처를 지대공유도무기 SAM(Surface to Air Missile) 교전 시뮬레이터에 적용하여 기 개발된 컴포넌트에 대한 효과도를 확인한다. 그리하여, 동적 컴포넌트 재구성 아키텍처의 시뮬레이션 적용을 통해 컴포넌트 기반의 재사용으로 유도무기체계에 대한 다양한 시스템을 구성하게 되었다.

• 한국항공우주학회지
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• 제43권10호
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• pp.910-919
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• 2015

전투기 탑재용 무장제어 알고리듬은 교전상황에서 전투기의 임무 수행 및 생존과 직결된다. 공대지 유도탄의 경우 조종사에게 LAR로 알려진 발사 유효 범위를 무장제어 알고리듬을 통하여 전투기 MFD상에 전시해 준다. LAR는 교전 거리의 계산을 통해 산출된 사거리 테이블을 이용하여 생성된다. 본 논문에서는 AGM-84와 AGM-88 공대지 유도탄의 운용모의에 대하여 소개하고, 이를 바탕으로 Pseudo 6자유도 모델에 기반한 사거리 테이블 산출과 실시간 LAR 산출 알고리듬에 대한 내용을 언급하였다. 구성한 알고리듬의 성능 검증을 위하여 모의대상 유도탄의 교전 시뮬레이션을 수행하고 LAR를 산출하여 분석하였다.

• 제어로봇시스템학회논문지
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• 제13권6호
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• pp.525-530
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• 2007

In this paper, a performance comparison between traditional TPN (true proportional navigation) guidance law and PPN(pure proportional navigation) guidance law is made, based on a short range surface-to-air missile simulation program. This simulation program has a nonlinear aerodynamic missile model, a roll stabilized autopilot, a nonlinear radar model, and a target model, According to the simulation results, the PPN guidance law has better performances than TPN guidance law under the condition of evasive target.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.125.2-125
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• 2001

Inertial navigation error is the major source of miss distance when only the inertial navigation system is used for guidance, and tend to monotonically increase if the flight time is small compared to the Schuler period. Miss distance due to these inertial navigation errors, therefore, can be minimized when a missile has the minimum time trajectory. Moreover, vertical component of navigation error becomes null if he impact angle to a surface target approaches to 90 degrees. In this paper, the minimum time trajectories with the steep terminal impact angle constraint are obtained by using CFSQP 2.5, and their properties are analyzed to give a guideline for he construction of an effective guidance algorithm for short range tactical surface-to-surface missiles.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2002년도 추계 학술대회논문집
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• pp.109-113
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• 2002

Numerical analysis of aerodynamic heating for KPSAM is performed using aerodynamic heating model suitable to KPSAM, which has complex flow field resulting from the spike attached to the dome, such as large separation area and the strong shock/boundary layer interaction region around reattachment point on the dome. The aerodynamic heating model is validated and modified through the comparison between the flight test measurement and the thermal analysis results. TFD temperature sensors are installed on the dome to measure surface temperature during the flight. Computation results, obtained from the heat transfer analysis on the sensors, agree well with flight test data. The aerodynamic heating model provides heat transfer rate into surface as a boundary condition of unsteady 1D/axisymmetric thermal analysis on the missile structure. The axisymmetric thermal analysis using FLUENT is more versatile than the 1D analysis and can be applied to the heating problem related with complex structures and multi-dimensional heat transfer problems such as prediction of temperature rise at contact surface of different materials.

• 한국정보통신학회:학술대회논문집
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• 한국정보통신학회 2015년도 추계학술대회
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• pp.462-464
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• 2015

최초의 이지스 순양함인 타이콘데로가함(USS Ticonderoga)이 건조된 이후 알레이버크급(Arleigh Burke class) 구축함이 미 해군 수상함 전력의 주력함으로 양산되고 있으며, 지속적으로 성능을 개량하여 최근에는 최신형 이지스 전투체계 버전인 베이스라인 9(Baseline 9)가 전력화 되었다. 미 해군은 이지스함에 탄도미사일 방어체계 능력을 탑재한 이지스 BMD를 탄도미사일 방어체계의 일부분으로 운용하고 있으며, 증가하는 탄도미사일의 위협에 보다 효과적으로 대응하기 위해 DDG-51 Flight III부터 기존의 AN/SPY-1D 보다 대공 성능이 향상된 AMDR(Air & Missile Defense Radar)를 탑재할 예정이다. 본 논문에서는 미국의 이지스함의 발전 현황과 기술적 특징에 대해 연구하고 AMDR의 특성에 대해 조사하여 기술하였다.

• Strategy21
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• 통권42호
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• pp.196-223
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• 2017

The aim of this paper is to analyze China's naval strengthening and threat reflected in submarines, aircraft, destroyers and missile capabilities and US Navy's counter-forces. China is strengthening its naval forces in accordance with its three-step naval force build-up plan, and the introduction of Russian destroyers and submarines is a foothold for China's naval enforcement. The Chinese Navy also converted the concept of the First-Second Island Chain Defense, which it had already maintained, to the concept of maritime layer defense. Currently, the Chinese Navy maintains the concept of a Three-Maritime Layer Defense which includes the South China Sea, where artificial islands are being built by China, in the First Layer Defense and the East China Sea in the Third Layer Defense. Along with the advancement of Chinese Navy's submarines, surface vessels and aircraft's operational capabilities, ballistic and cruise missile capabilities become a major threat to the US Navy. If a crisis occurs in the East China Sea or in the Taiwan Waters, the US Navy will face more difficulties in employing the Carrier Strike Group to manage the crisis. Meanwhile, if a crisis occurs on the Korean Peninsula, it will be a burden to dispatch Carrier Strike GroupS to the East and West Seas of the Korean Peninsula. For the stable future, the US Navy should develop a strategy to respond more effectively to the Chinese Navy, which is challenging new maritime supremacy in East Asia.

• 한국소음진동공학회:학술대회논문집
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• 한국소음진동공학회 2002년도 추계학술대회논문집
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• pp.914-920
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• 2002

Nonlinear flow-induced vibration characteristics of a generic missile wing (or control surface) are investigated in this study. The wing model has freeplay structural nonlinearity at its pitch axis. Nonlinear aerodynamic flows with unsteady shock waves are considered in the transonic flow region. To practically consider the effects of freeplay structural nonlinearity, the fictitious mass method (FMM) is applied to structural vibration analysis based on a finite element method (FEM). A computational fluid dynamics (CFD) technique is used for computing the nonlinear unsteady aerodynamics of all-movable wings. The aerodynamic analysis is based on the efficient transonic small-disturbance aerodynamic equations of motion using the potential-flow theory. To solve the nonlinear aeroelastic governing equations including the freeplay effect, a modal-based computational structural dynamic (CSD) analysis technique based on fictitious mass method (FMM) is used in time-domain. In addition, CSD and unsteady CFD techniques are simultaneously coupled to give accurate computational results. Various aeroelastic computations have been performed for a generic missile wing model. Linear and nonlinear aeroelastic computations have been conducted and the characteristics of flow-induced vibration are introduced.