• 한국군사과학기술학회지
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• 제15권1호
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• pp.86-92
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• 2012

When missile is launched, a launcher needs to be leveled with accuracy to avoid the systems's instability. In general, a launcher is leveled by adjusting the stroke of leveling jacks; however, it is still challenge to control the leveling jacks fast and accurately. This paper thus proposed an innovative algorithm for compensating ground inclination of a missile launcher to expand operational field of a missile launcher. Using two inclinometers attached on a launcher, a base jack for leveling is selected and the mixed gradient where launcher stands on can be estimated. Due to the limited stroke, the launcher can compensate its ground inclination within maximum stroke margin. Then, the ground inclination of a launcher can be compensated by calculated angle using weighting factors. The effectiveness of proposed algorithm is proved with a prototype missile launcher.

• 한국정밀공학회:학술대회논문집
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• 한국정밀공학회 1996년도 추계학술대회 논문집
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• pp.1017-1022
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• 1996

This paper presents results of dynamic analysis of the missile initial motion arising from the missile detent force. Using ADAMS (Automatic Dynamic Analysis of Mechanical System) software, a non-linear 46-DOF (Degree of Freedom) model is developed for the launcher system including missile and launch tube contact problem. From the dynamic analysis, it is found that initial angular velocity of the missile increases when the missile detent force increases (more than 18 g) and also rocket exhaust plume is taken into account. To achieve the missile launching s ability, it needs to reduce the missile initial detent force and exhaust plume area of the launcher. Results of the dynamic analysis on the system natural frequency agree well with those obtained from experimental modal tests. The overall results suggest that the proposed method is a useful tool for prediction of initial missile stability as well as d :sign of the missile launcher system.

• 한국군사과학기술학회지
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• 제16권5호
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• pp.590-597
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• 2013

For a lower tier defense, the distance between a launcher and an engagement control station is quite important to estimate the proper defense area and to effectively arrange missile launchers. In this paper, we have analyzed an effectiveness of anti-ballistic missile launcher arrangement for the lower tier defense against the ballistic missile. The operation concept, specific configuration and aerodynamic characteristics of the ballistic missile such as SCUD-B/C, Nodong are considered in order to develop a realistic engagement simulation. The diverse engagement results through numerical simulations are provided to conduct the effectiveness analysis of anti-ballistic missiles.

• 한국군사과학기술학회지
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• 제11권3호
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• pp.13-18
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• 2008

During the launching phase, a launcher is vibrated by launching forces and as a result, the vibrating launcher affects the behavior of the missile. One of the important performances of the launcher is that the launched missile should be in a stable condition at the launching stage. In this paper, the launcher vibration at the launching phase is investigated in order to secure the stable flight of the missile. Using the finite element method, launching dynamics is investigated to analyze the behaviors of the launcher and missile considering the effect of the launcher vibration. In addition, performance of consecutive launching and launching dynamics of the launcher which launches missiles consecutively are studied for the various conditions after first launch.

• 한국정밀공학회지
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• 제14권4호
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• pp.22-29
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• 1997

This paper presents results on dynamic analysis of the missile initial motion arising from the missile detent force. Using ADAMS (Automatic Dynamic Analysis of Mechanical Syatem) software, a non- linear46-DOF (Degree of Freedom) model is developed for the launcher system including missile and lunch tube contact problem. From the dynamic analysis, it is found that initial angular velocity of the missile incre- ases when the missile detent force increases and also when rocket exhaust plume is taken into account. To achieve the missile launching stability, it needs to reduce the missile initial detent force and exhaust plume area of the lancher. Results of the dynamic analysis on the system natural frequency agree well with those obtained from experimental modal tests. The overall results suggest that the proposed method is a useful tool for prediction of initial missile stability as well as design of the missile launcher system.

• 한국산학기술학회논문지
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• 제20권2호
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• pp.329-335
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• 2019

본 연구에서는 특정 유도무기체계에 대한 신뢰도 성장 분석을 수행하였다. 개발단계에서의 시험을 통해 고장 모드와 원인을 식별하고 시험 중 발견된 고장을 분석하여 지속적인 관리 활동을 수행하고 있다. 해당 유도무기체계는 유도탄과 발사 체계로 구성되어 있으며, 각 장비의 시험 결과에 따라 신뢰도 성장 분석을 실시하였다. 유도탄의 경우에는 일회성 무기로 성공과 실패인 이산형 데이터로 시험 결과를 획득하였다. 발사체계의 경우에는 시험에서 지속해서 장비 운용을 하여 연속형 데이터로 시험 결과를 획득하였다. 각각의 시험 결과 형태로 신뢰도 성장 모델을 Standard Gompertz 모델과 Crow-Extended 모델을 적용하였다. 해당 모델을 사용하여 현재까지 수행한 시험 결과에 대한 신뢰도 성장 분석 결과를 확인하였다. 또한 미래에 수행될 시험 결과를 가정하여 신뢰도 성장 결과를 예측할 수 있었다. 본 연구는 해당 유도무기체계의 신뢰도 목표값을 달성하고 시험 횟수를 결정하는데 있어 유용하게 활용될 수 있을 것이다. 그리고 이후 계획된 시험을 확인하여 해당 유도무기체계에 대한 신뢰도 성장 관리를 지속적으로 추진할 예정이다.

• 한국군사과학기술학회지
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• 제2권2호
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• pp.92-98
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• 1999

Dynamic behavior of missile which is fired in canister is analyzed by flexible multibody dynamics. The bending elasticity of missile is very important in case that missile is fired in the inclined launcher. In this paper, the force element model for the missile launching stage and the finite element model of missile are developed. The FEA model of missile is condensed into five lumped mass element model and the consistence between FE model and lumped mass model of missile is verified by modal analysis. As a result of analysis, sabot reaction force and pitch rate of missile for the variation of gap size and force element are obtained.

• 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.

• 한국생산제조학회지
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• 제24권3호
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• pp.342-347
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• 2015

The launcher pod for missiles capable of carrying a range of different warheads has been designed to be mounted on the tracked vehicle of the hybrid weapon system (HWS). In the development of this launcher pod, its structure was designed to be resilient to damage caused by shock and vibration, as well as preventing assembly errors due to the spring-back of the main composite cover and interfacing parts. This study investigated the design of the newly developed launcher pod, with its hybrid composite-metal structure, through simulation and experiment. Both simulation and actual experiments showed that the structure of the launcher is resilient to vibration and shock. The launcher pod was also subjected to vibration and shock tests to verify its performance.

• 한국군사과학기술학회지
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• 제11권2호
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• pp.66-72
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• 2008

A distributed missile system is composed of command control center, radar and launcher which exchange information each other to use wire or wireless network. The distributed missile system is required mobility for operational convenience and survivability. Also missile system requests land navigation system to provide relatively accurate attitude. For reason of these requirements, each subsystem needs land navigation which provides information of position and attitude. This paper represents operational concept for land navigation to consider operational environment and concrete operational procedure to apply the operational concept. In state that there is no operation for land navigation of distributed missile system internally so for, this paper could be helped to establish operational concept and procedure of this kind of system.