• 한국군사과학기술학회지
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• 제5권2호
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• pp.37-49
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• 2002

In this paper, flyout stability of missile that is launched in inclined launcher using sabots is analyzed. To include missile bending motion during flyout, FEA model of missile is converted into eight concentrated mass and equivalent stiffness matrix. Six d.o.f ship motion that have influence on flyout stability is modeled and missile firing time is modeled as probability variable to take arbitrary ship attitude into account. Gap between missile and sabot is modeled as normal distribution probability variable and Monte Carlo simulation is performed. As results, the coriolis acceleration effects by ship motion are analyed and statistical results of missile pitch rate are shown.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.647-652
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• 1994

In the previous paper, we presented a new guidance law for a missile during boost phase. Thus, this paper deals with the guidance law for a missile after the thrust cutoff against an accelerating and turning target. It is essentially based on the concept of proportional navigation. Some simulation studies were performed using a three dimensional mathematical model of an air-to-air missile and the effectiveness of the guidance law presented was shown.

• 한국시뮬레이션학회논문지
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• 제29권1호
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• pp.1-9
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• 2020

과학기술의 발전에 따라 탄도탄에 대한 위협이 나날이 증대되고 있으며, 이러한 위협에 대처하기 위한 탄도탄 요격미사일에 대한 개발이 요구되고 있다. 대탄도탄용 요격미사일의 개발을 위해서는 요격시험이 필수적이다. 시험을 통해 얻은 계측자료를 활용하여 요격미사일을 포함한 전체적인 요격 시스템의 성능을 확인할 수 있다. 그러나 요격시험 시에는 요격에 의한 파편이 발생되기 때문에 안전을 위한 민간인의 접근 통제가 필요하다. 따라서 요격시험에 앞서 요격 파편에 대한 안전구역의 신뢰도 높은 추정이 선행되어야 한다. 본 논문에서는 모델링 분석 및 시뮬레이션을 활용하여 요격 파편에 대한 안전구역을 산출하였다. 우선, 탄도탄과 요격미사일의 발사단계에서 요격까지의 전 과정에 대한 시뮬레이션을 수행하였고, 요격 시점에서의 상대 속도 및 상대 각도를 산출하였다. 이 결과를 활용하여 요격 시의 에너지를 계산하고 요격 파편의 방출속도를 산출하였다. 이후, 파편에 작용하는 항력과 중력을 고려하여 낙하 궤적을 산출하였고, 파편의 낙하 지점과 위험도를 종합적으로 고려하여 최종 안전구역을 산출하였다.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1996년도 한국자동제어학술회의논문집(국내학술편); 포항공과대학교, 포항; 24-26 Oct. 1996
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• pp.1496-1499
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• 1996

A nonlinear tracking control technique developed for the control of nonlinear systems has been applied to the autopilot design of missile system. The difficulties in the application of inversion based control methods such as input-output feedback linearization and sliding mode control due to nonminimum phase characteristics are discussed. To avoid the stability problem associated with unstable zero dynamics, the input-output feedback linearization is applied with output-redefinition method to normal acceleration control. The output-redefinition method gives an indirect way to apply the nonlinear controls to nonminimum phase plants by redefining the plant output such that the tracking control of the modified output ensures the asymptotic tracking of the original output. The numerical simulation shows satisfactory results both for nominal and for slightly perturbed missile systems adopting the sliding mode control technique. However, the robustness problem in this method is briefly investigated and verified with the simulation.

• 한국군사과학기술학회지
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• 제14권3호
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• pp.353-358
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• 2011

In this paper, we have introduced a Missile In the Loop Simulation(MILS) Software developed for the missile ground test, which is based on a commercial hard real-time operating system(OS) on Windows platform called as Real-Time eXtension(RTX). MILS software makes it possible to test overall system functions of a integrated missile on the ground in the flight conditions by real-time imitating its inertial data. By means of MILS, we have performed missiles ground tests, which result in successful real flight tests.

• 한국시뮬레이션학회논문지
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• 제19권1호
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• pp.63-71
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• 2010

현대전에서는 정보전을 기반으로 미사일, 유도무기 등의 사정거리와 정밀도가 향상됨에 따라 지대공미사일(SAM : Surface to Air Missile)의 요격성능의 중요성이 부각되고 있다. 위협적인 공중 공격을 예측 하고 방어하기 위해 최선의 방법으로 지대공 레이더와 유도미사일을 이용한 공중방어시스템 구축이 필요하다. 지대공미사일 개발 과정에서 Modeling and Simulation (M&S)을 이용하는 것은 시간적, 공간적 제한을 극복할 수 있고 시행착오를 줄임으로 비용을 절감할 수 있는 이점이 있다. M&S는 최신 무기체계 설계 및 교육/훈련 분야에 많이 적용되고 있다. 본 연구는 지대공미사일의 요격 성능 평가를 위한 시뮬레이터를 개발하는 것에 목적이 있다. 본 연구에서는 다양한 사양의 지대공미사일 요격 성능을 고려할 수 있는 지대공미사일 요격 성능 분석 시뮬레이터의 아키텍처를 제시하고 개발하였다. 개발된 지대공미사일 요격 성능 분석 시뮬레이터는 C++와 Direct3D를 기반으로 개발되었으며, Direct3D를 이용한 3D 가시화를 통해 사용자에게 애니메이션 창에 시각적으로 시뮬레이션의 진행 경과를 보여줄 수 있도록 개발되었다. 사용자의 교전모델 설계 운영 정보는 입력창을 통해 입력되며, 이 정보는 객체 관리자, 운영 관리자, 통합 관리자로 구성된 시뮬레이션 엔진에서 자동으로 지대공미사일을 모델링 및 시뮬레이션 하여 빠른 시간 안에 시뮬레이터 사용자에게 피드백을 제공한다.

• 대한전기학회:학술대회논문집
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• 대한전기학회 2002년도 하계학술대회 논문집 D
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• pp.2659-2661
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• 2002

The development of guided missile requires complex guidance schemes and hardware units because of high maneuver, delicate and variable missions. In this point of view, simulation systems and facilities which test missile hardwares and softwares are needed. This paper introduces the hardware-in-the loop simulation system and facilities which include the real-time computation systems and 3 Axis FMS(Flight Motion Simulator).

• Computers and Concrete
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• 제26권5호
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• pp.377-384
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• 2020

A two-dimensional particle flow cod (PFC) is used to study the effect of missile impact on the concrete target. For this purpose firstly calibration of numerical model was performed so that tensile strength of numerical models and experimental sample were the same. Secondly, a concrete model was built. The number of concrete layers and the angle of concrete layers related to horizontal axis were changed. Their numbers were 1, 2, 3 and 4. The angles were 0°, 15°, 30°, 45°, 60°, 75° and 90°. A semi-circle missile was simulated at top of the concrete layers. Its velocity in opposite side of Y direction was 100 m/s. three measuring circles were situated at the below the missile in the model to receive the applied force. The load in the missile and measuring circles together with failure pattern were registered at the beginning of the impaction. The results show that concrete layers number and concrete layers angle have important effect on the failure load while the failure pattern was nearly constant in all of the models.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1992년도 한국자동제어학술회의논문집(국내학술편); KOEX, Seoul; 19-21 Oct. 1992
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• pp.165-170
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• 1992

In this paper, the Hardware-In-The-Loop Simulation(HILS) of missile systems are studied. The HILS is an effective performance evaluation technique that bridges the simulation fidelity gap between analytic all-digital simulations and actual flight tests of missile systems. The HILS may be required to perform system integration tests, performance evaluation at system or subsystem level. Major elements of this HILS facility will include the flight table, simulation computers, I/O computer and peripheral equipments. HILS of missile systems typically involve computer modeling of flight dynamics coupled with a hardware guidance and control(G/C) systems. This paper describes a real time performance evaluation technique of a G/C system, Development of a HILS for a Autopilot of SAM G/C will be used as an example.

• 한국국방경영분석학회지
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• 제26권2호
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• pp.28-38
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• 2000

This research investigates a kill probability model for the performance evaluation of guided missile system, and also develops graphical user interface for the input and output of the model based on the visual object-oriented programming application. The major simulation events used in this research are missile guidance homing point, burst points, and kill mechanism(direct kill, blast kill and fragment kill). For the user interface, we also design and implement the visualization system that can show the graphic style of the kill probability attained by the model. The results of sample run are shown, but these could be improved to be better with visual simulation which can visulaize all the simulation process of the model.