• 한국해양공학회:학술대회논문집
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• 한국해양공학회 2006년 창립20주년기념 정기학술대회 및 국제워크샵
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• pp.315-318
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• 2006

This paper concerns about coupled dynamic analysis of the deep-seabed mining system in launching operation. The dynamic behavior of mining system consisting of lifting pipe, buffer station, flexible conduit and self-propelled miner is simulated in time domain. The launching operation is divided into four critical phases: (1) deployment of miner and flexible conduit, (2) deployment of lifting pipe, flexible conduit and miner, (3) touch-down of miner, (4) final launching. The dynamic responses of sub-systems - miner, flexible conduit, buffer and lifting pipe - are analyzed in each launching phase. According to the changing periods of forced excitation at the top, the dynamic responses of sub-systems are diverse in their characteristics. It has been shown that the total integrated responses of sub-systems are strongly affected by the design parameters. Especially, the principal dimensions of flexible conduit seem to be significant in determining of the global response. Based on the simulation results, safe operation conditions are investigated.

• 한국시뮬레이션학회논문지
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• 제27권4호
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• pp.69-77
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• 2018

발사관은 탑재물을 보관하고 외부 환경으로부터 부식 및 파손되는 것을 방지하는 역할을 한다. 발사관과 유도탄의 제작, 조립 그리고 장입 상태에 따라 발사할 때 유도탄의 초기 거동을 결정하게 된다. 본 연구의 목적은 유도탄이 발사관에서 사출될 때 유도탄의 초기 거동을 결정하는 요소를 통계적으로 분석하여 발사관의 안전성을 확인하는 것이다. 유도탄이 발사될 때 거동에 영향을 주는 오차 요소들을 선정한 후 Monte-Carlo 시뮬레이션을 수행하여 통계적으로 분석하였다. 시뮬레이션 결과를 바탕으로, 각 오차 요소들을 고려한 다물체 동역학 해석을 상용프로그램인 Recurdyn을 이용하여 동역학 해석을 수행하여 유도탄 발사할 때 발생하는 중력 침하 및 레일과 슈 사이에 발생하는 응력을 구하였다. 해당 결과를 바탕으로 현재 설계된 발사관에 대한 안전성을 검증하였다.

• 한국자동차공학회논문집
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• 제7권7호
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• pp.157-166
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• 1999

This paper describes the launching characteristics of a passenger car using a Push-Belt type Continuously Variable Transmission(CVT) which equipped a wet type multi-plate clutch asa starting device and a solid flywheel with a torsional damper for a torsional coupling device. To reduce the torsional vibration of the drive-line , some torsional coupling devices were used for the passenger car equipped CVT having the clutch as a starting device especially . In this study, we developed the computer simulation program to investigate the launching characteristics of a passenger car equipped CVT using the mathematical models of this system. For the mathematical models of the vehicle, the CVT, the we type multi-plate clutch and the torsional damper, we obtained the specification and the necessary data through the reverse engineering of those. For the verification of our analysis, we performed the test of prototype car with different throttle positions at road and dynamometer. The launching characteristics of a passenger car considered here an acceleration performance and an ascending performance.

• 한국항공우주학회지
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• 제37권1호
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• pp.55-61
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• 2009

본 논문은 검증된 수직발사 유도탄을 모델로 고려하여 개발하려는 수직발사 유도탄의 추력을 예측하는 방법을 제안한다. 개발하려는 수직발사 유도탄의 추력을 예측하기위해 모델에 상사법칙과 Pi 이론을 적용하였다. 검증된 수직발사 유도탄의 6-DOF 프로그램에 기반한 예측 결과와 개발하려는 수직발사 유도탄의 모의시험 결과를 비교하여 제안된 방법의 타당성을 검증하였다.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2005년도 추계 학술대회논문집
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• pp.255-259
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• 2005

An analysis is made of flow and rocket motion during a supersonic separation stage of air-launching rocket from the mother plane. Three-dimensional Euler and Navier-Stokes equations are numerically solved to analyze the steady/unsteady flow field around the rocket which is being separated from two cases of mother plane configuration: one is an idealized ogive-cylinder body and the other is a real F-4E Phantom. The simulation results clearly demonstrate the effect of shock-expansion wave interaction between the rocket and the mother plane. As a result, a design-guideline of supersonic air-launching rocket for the safe separation is proposed.

• 한국항해항만학회지
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• 제32권1호
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• pp.1-7
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• 2008

최근 중국의 경제 활성화에 힘입어 물동량이 급증하게 되었고, 따라서 선박의 폭발적인 요구도 생기게 되었다. 그러나 조선소의 건조 능력은 드라이도크의 용량에 의하여 크게 의존할 수밖에 없는 실정이다. 드라이도크의 건조는 상당히 긴 기간을 필요로 하고, 또 건조 비용도 많이 들기 때문에 장기적인 조선의 수요의 관점에서 타당성을 검토할 필요가 있다. 더욱 시급한 것은 당장 목전에 와 있는 조선 수요를 적절히 감당해 주어야 한다는 점이다. 그래서 여러 조선소에서는 드라이도크의 부족을 메우기 위한 다양한 방안들이 검토되었다. 현대중공업에서는 육상 건조법을 도입하였고, 삼성중공업과 STX 조선소에서는 플로팅도크에서 건조하는 방법을 도입하였다. 본 논문은 육상에서 건조한 대블록을 플로팅도크에 밀어 넣는 Skid Launching System(SLS)을 위한 도크 제어 시뮬레이터를 개발하여 모의 조정한 결과를 보인다. 대형 블록을 플로팅도크에 밀어 넣기 전에 발라스트 순서도를 작성하여 모의 작업을 통하여 안정성을 확인한 뒤 실제 작업 시 이 순서대로 작업을 하여 플로팅도크의 안전성을 확보하기 위한 장치를 개발한 것이다.

• 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.

• 한국군사과학기술학회지
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• 제12권4호
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• pp.407-414
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• 2009

This paper describes a conceptual model for the performance analysis simulator of a weapon launching system. The system performance analysis simulator is envisioned to provide an integrated analysis environment in which the system performance and operational effectiveness can be analyzed in more rapid and efficient way. The conceptual model for the simulator describes a referent independently of specific technology and implementation, and it can be used to transform the simulator requirements into the simulator system specifications.

• 유체기계공업학회:학술대회논문집
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• 유체기계공업학회 2006년 제4회 한국유체공학학술대회 논문집
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• pp.423-426
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• 2006

An analysis is made of flow and rocket motion during a supersonic separation stage of air-launching rocket(ALR) from the mother plane. Three-dimensional compressible Navier-Stokes equations is numerically solved to analyze the steady/unsteady flow field around the rocket which is being separated from the mother plane configuration(F-4E Phantom). The simulation results clearly demonstrate the effect of shock-expansion wave interaction between the rocket and the mother plane. To predict the behavior of the ALR according to the change of the C.G., three cases of numerical analysis are performed. As a result, a design-guideline of supersonic air-launching rocket for the safe separation is proposed.

• 한국전산유체공학회:학술대회논문집
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• 한국전산유체공학회 2004년도 추계 학술대회논문집
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• pp.155-160
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• 2004

This paper describes a supersonic separation of air-launching rocket from the mother plane. Three dimensional Euler equations were numerically solved to analyze steady/unsteady state fluid flows. To solve the Euler equations, named CFD-FASTRAN that is commercial computation code. The results of simulation clearly demonstrate effect of shock-expansion wave interaction between the rocket and the mother plane. Moreover, important influential factors at separating stage of the rocket were extracted with a comprehensive analysis. Finally, from the consideration of supersonic-separation, a guideline to safety-separation is given to the design of supersonic air-launching rocket.