• 한국소음진동공학회논문집
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• 제22권9호
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• pp.889-895
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• 2012

A vertical launching system(VLS) is a system for holding and firing missiles on surface ships. When a missile is launched in VLS, relative motion between canister and missile and drag force induced by wind can cause initial unstability of a missile. Thus dynamic analysis of initial behavior of vertically launched missile should be performed to prevent collision with any structure of a ship. In this study, dynamic analyses of initial behavior of vertically launched missile are performed using Monte-Carlo simulation, which relys on random sampling and probabilistic distribution of variables. Each parameter related with dynamic behavior of a missile is modeled with probability variables and Recurdyn, a commercial software for multi body dynamic analysis, is used to perform Monte-Carlo simulation. As a result, initial behavior of a missile is evaluated with respect to various performance indexes in a probabilistic sense and sensitivity of the each parameters is calculated.

• Computers and Concrete
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• 제27권1호
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• pp.1-12
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• 2021

This work presents a safety assessment of an underground tunnel subjected to a ballistic missile attack employing the numerical approach. For the impact simulation, a box shaped reinforced concrete (RC) structure with a cross section dimension of 8.0×10.0 m under a soil layer that was attacked by a SCUD missile was modeled using finite element (FE) software LS-DYNA. SCUD missile is one of a series of tactical ballistic missiles developed by Soviet Union during the Cold War, which is adopted for a short-range ballistic missile. The developed FE simulation for the penetration depth of the missile impacting into the soil structure was verified from the well-known formula of the penetration prediction. The soil-structure interaction, the soil type, and the impact missile velocity effects on the penetration depth of the missile into the different soil types were investigated. The safety assessment of the underground tunnel was performed with regard to the different depths of the underground tunnel. For each missile velocity and soil type, a specific depth called the unsafe depth was obtained from the analysis results. The structure beneath the soil beyond this depth remains safe. The unsafe depth was found to be increased with the increasing missile velocity.

• 한국시뮬레이션학회논문지
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• 제26권1호
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• pp.13-19
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• 2017

국내 유도무기 개발과정에서 가장 일반적으로 적용되는 M&S 도구는 유도탄의 각 구성품 및 공력특성 모델을 반영한 6자유도 비행모의 프로그램이다. 하지만 3세대 대전차 유도무기와 같이 영상탐색기가 적용되는 경우 6자유도 비행모의만으로 다양한 조건 하에서의 체계 성능을 확인할 수 없다. 영상탐색기의 추적 성능은 표적의 대조비나 온도차뿐만 아니라 유도탄 거동에 따른 표적 위치 이격, 회전 등에 민감하게 반응하기 때문에 유도무기 개발 과정에서 영상 추적 성능과 유도탄 비행성능을 통합하여 분석할 수 있는 M&S 도구가 요구된다. 3세대 대전차 유도무기인 현궁 개발 과정에서는 형상 설계 단계부터 '합성영상 생성 S/W'-'영상추적기'-'비행모의 프로그램'을 연동한 통합비행 M&S 도구를 개발, 적용하였다. 통합비행 M&S 도구 기반으로 몬테카를로 시뮬레이션을 수행한 후 체계 주요 성능 지수, 즉 명중률 비교를 통해 적합한 형상을 선정하였다. 본 논문에서는 3세대 대전차유도무기 형상설계를 위한 고려요소와 함께 통합비행 M&S 방법론 및 분석 결과를 기술하였다.

• 한국멀티미디어학회논문지
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• 제23권8호
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• pp.1066-1074
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• 2020

High Level Architecture/Run-Time Infrastructure (HLA/RTI) is used to connect individual simulators on networks in order to interoperate heterogeneous simulators. In defense domain, Ship Air Defense Model (SADM) and Extended Air Defense Simulation (EADSIM) are two of most advanced simulation tools. To interoperate these SADM and EADSIM, this paper attempts to use HLA/RTI that helps to support a Composite Combat Mission Planning Simulation Environment (CCMPSE). The CCMPSE allows us to analyze a group of simulations for comprehensive and accurate experiments. For the first time, this paper analyzes guided missile simulations in EADSIM and SADM by comparing related simulation models in their parameters and considerations. It presents characteristics of these models in view of guided missile simulation perspectives. For the contributions of this paper, it provides insights to select guided missiles between SADM and EADSIM on the CCMPSE according to specific simulation purposes.

• 한국멀티미디어학회논문지
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• 제22권8호
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• pp.930-939
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• 2019

High-Level Architecture(HLA)/Run-Time Infrastructure(RTI) are standards for distributed simulation systems and offer a technology to interconnect them and form one single simulation system. In defense domain, M&S is the only way to prove effectiveness of weapon systems except for Live Fire Testing (LFT). This paper focuses on guided missile simulations in weapon systems for engagement analyses and proposes the integrated flying vehicle model that is based on HLA/RTI. There are a lot of missiles in real world; therefore, we should develop each missile models in M&S in order to apply battlefield scenarios. To deal with the difficulties, in this paper, firstly, I classify these missiles into three models: ballastic, cruise, and surface-to-air missile models, and then I design each missile model and integrates them into a single model. This paper also offers a case study with my integrated flying vehicle model. At the conclusion, this paper presents contributions of this paper.

• 한국시뮬레이션학회논문지
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• 제30권1호
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• pp.31-42
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• 2021

한국군은 북한의 탄도미사일 위협에 대응하기 위해 단층방어의 취약점을 보완할 수 있는 다층방어를 구성 중이다. 이에 따라 다층방어체계의 요격률을 극대화 할 수 있는 운용방안 연구가 필요하며, 한국형 미사일 방어체계의 운용방안을 연구하기 위해서는 한국군의 작전환경, 전략적 타격체계의 효과 등을 종합적으로 고려해야 할 것이다. 따라서 본 연구는 한국형 미사일 방어체계의 특성을 반영한 시뮬레이션을 구성하고 총 4가지 요격미사일 운용방안을 선정하여 비교분석 하였다. 시뮬레이션 결과, 탄도미사일 위협 추정량과 요격미사일 보유량, 전략적 타격체계의 효과를 종합적으로 고려하는 것이 다양한 상황에서 높은 요격률을 달성할 수 있음을 확인하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1991년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 22-24 Oct. 1991
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• pp.389-394
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• 1991

The surface-to-air missile system using Command to Line-Of-Sight (CLOS) guidance law is represented by complex nonlinear differential equations with 6 degree-of-freedom. This paper presents the characterictics of missile system and the effect of various error sources by Monte-Carlo simulation method. By simulation the part of playing a main role in the surface-to-air missile system is radar. Therefore for the performance of missile system the development of the technique reducing the error of radar is required. And the effect of accelerometer error is a few large, too. But, because accelerometer costs cheap this problem is solved easily. And the main error source of missile system data is the thrust, which affects directly to acceleration. The result is the important information about designing and fabricating missile system. And this makes the missile system best because of sharing elaborate and expense effectively.

• 한국정밀공학회지
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• 제33권10호
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• pp.781-787
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• 2016

We introduce FEST (Flight Environment Simulation Test) procedures for precise guided missiles to reliably improve systems. Flight vibration specification was established based on power spectral density curves calculated from flight test data of a high speed precise guided missile. A FEST pre-profile was developed according to flight vibration specification and delivered to a precise guided missile assembly. Vibration responses were measured by installing accelerometers on electronic components vulnerable to dynamic forces. The FEST profile was adjusted by comparing the vibration responses and the flight vibration specification. Subsequently, the FEST profile was repeatedly modified through trial and error, because the responses were similar to the flight environment. The modified FEST profile enabled performance testing of assembled precise guided missiles under simulated flight conditions on the ground, where unexpected errors could be corrected before the flight tests, leading to cost and risk reduction in the development of the precise guided missile system.

• 제어로봇시스템학회논문지
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• 제13권3호
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• pp.273-278
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• 2007

In this paper, a performance comparison between CLOS(Command to Line-of-Sight) guidance law and PN(Proportional Navigation) guidance law is made, based on a short range surface-to-air missile simulation program called KNUCLOS. This simulation program has a full nonlinear aerodynamic missile model, a tracker model for missile and target, and target model. According to the simulation results, the PN guidance law has a better performance than CLOS guidance law under various target speed.

• 한국시뮬레이션학회논문지
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• 제18권4호
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• pp.95-105
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• 2009

본 연구에서는 M&S(Modeling and Simulation) 기법을 통하여 보증 유도탄의 주기적 검사방법을 제시하였다. 유도탄 운용 개념과 예측된 저장신뢰도로부터 시나리오를 작성, 이를 기반으로 모의시험을 위한 모델링을 수행하고 시뮬레이션 프로그램으로 구현하였다. 그리고, 시뮬레이션 결과와 이론적인 추정치를 비교 검토하고, 목표로 하는 정상작동확률을 달성할 수 있는 최적의 주기점검 방안을 제시한다.