• The Journal of Korean Institute of Electromagnetic Engineering and Science
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• v.30 no.6
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• pp.487-497
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• 2019

It is very difficult to detect ballistic missiles because of small cross-sections of the radar and the high maneuverability of the missiles. In addition, it is very difficult to recognize and intercept warheads because of the existence of debris and decoy with similar motion parameters in each flight phase. Therefore, feature vectors based on the maneuver, the micro-motion according to flight phase are needed, and the two types of features must be fused for the efficient recognition of ballistic warhead regardless of the flight phase. In this paper, we introduce feature vectors appropriate for each flight phase and an effective method to fuse them at the feature vector-level and classifier-level. According to the classification simulations using the radar signals predicted by the CAD models, the closer the warhead was to the final destination, the more improved was the classification performance. This was achieved by the classifier-level fusion, regardless of the flight phase in a noisy environment.

• The KSFM Journal of Fluid Machinery
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• v.16 no.2
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• pp.21-26
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• 2013

Super-cavitating vehicle which is operating under water speeds up to 100m/s. In this process super-cavitation around body reduces frictional resistance. This paper introduces experimental study on different width of suction path as there is a warhead in the torpedo. Hydraulic performances of turbopump at non-cavitating condition does not display a significant differences depending on different width of suction path. However, cavitation performance of each model shows obvious differences in the same condition of experience. In case of radial inlet, the value of critical NPSH(which indicates 3% head drop) increases about 20% in comparison of axial inlet.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.3
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• pp.340-347
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• 2013

Weapon effect is a key issue throughout the life cycle of weapon systems. Only when weapon effect is considered properly, Effects Based Operation(EBO), Effects Based Acquisition(EBA), and Effects Based Development(EBD) could be possible. Because the transfer of weapon effect technologies is restricted in most foreign counties, independent development is necessary. In this paper, framework of weapon effects calculator for hardened targets is proposed to meet the own development needs. It is designed focusing on running time, validation and expandibility by adoption of modular architecture. Required technologies for each module are identified, and unclassified ones are summarized.

• Journal of Mechanical Science and Technology
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• v.16 no.6
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• pp.770-775
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• 2002

In this paper, a game optimal receding horizon guidance law (GRHG) is proposed, which does not use information of the time-to-go and target maneuvers. It is shown that by adjusting design parameters appropriately, the proposed GRHG is identical to the existing receding horizon guidance law (RHG), which can intercept the target by keeping the relative vertical separation less than the given value, within which the warhead of the missile is detonated, after the appropriately selected time in the presence of arbitrary target maneuvers and initial relative vertical separation rates between the target and missile. Through a simulation study, the performance of the GRHG is illustrated and compared with that of the existing optimal guidance law (OGL).

• Journal of Aerospace System Engineering
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• v.10 no.3
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• pp.44-51
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• 2016

This paper describes the operational concept of the Aegis ship's missile defense. Recently, North Korea conducted a fourth nuclear-weapon test that involved the launch of a long-range missile and the underwater launch of an SLBM. The ground-based BMD (Ballistic Missile Defense) system is very limited for the SLBM of a miniaturized nuclear warhead; therefore, it is necessary to build a reliable sea-based missile-defense system. The ROK Navy has, however, only utilized the Aegis ship that is designed with a search-and-tracking sensor but is without a ballistic-missile interception capability. Given this information, this work focuses on the operational concept of the Aegis BMD by comparing the BMD capabilities of the ROK with those of the U.S.

• Journal of Aerospace System Engineering
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• v.10 no.1
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• pp.118-126
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• 2016

North Korea has continued developing ballistic missiles with various ranges. Even through the recent launch long-range missiles, it can be inferred that North Korea's Missile technology has reached a level where it can even threaten the US. moreover, through the three times nuclear tests, North Korea is known to have succeeded at gaining 10~20KT of explosive power as well as the minimization and lightening of nuclear warhead. Considering the short length of war zone in Korean peninsula and the possibility of nuclear equipment, if be the most severe threat across the whole peninsula. Since the midcourse phase flight takes the longest time, ROK should establish the ability to intercept at this middle phase. From this perspective, this paper describes mission effect of a sea-based BMD system through empirical threat and flight characteristic analysis using MIT model that was not suggested in original research.

• Journal of the Korean Ceramic Society
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• v.43 no.10 s.293
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• pp.653-659
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• 2006

The glass-SiC composites have been manufactured via viscous flow of glass for investigating their sinterability and various properties. The relative density of 99.6% could be achieved when 5 wt% SiC was mixed with glass powder, glass-rearranged at 460$^{\circ}C$ for 3 h and then sintered at 665$^{\circ}C$ for 1 h. The sintered density was decreased as adding more than 5 wt% SiC to glass powder. The resistance properties against hyper velocity copper jet formed by explosion of K215 warhead were compared with other ceramics such as $Al_2O_3$ and pyrex, resulting in lower values than that of $Al_2O_3$.

• Journal of the military operations research society of Korea
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• v.23 no.1
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• pp.1-13
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• 1997

This research investigates a kill probability model for the performance evaluation of guided missile system, and also develops the user interface implementation for the output of the model based on the visual object-oriented programming application. This paper describes in detail the methodology for the kill probability attained by a missile warhead detonating near an airborne target. 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. This research will bridge the gap between the sophisticated kill probability model and users who want to see the results interactively with visualization, which can benefit many of other military systems. Some examples are shown, but these will be improved to be better with visual simulation which can visualize all the simulation process of the model.

• Journal of the Korea Institute of Military Science and Technology
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• v.14 no.6
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• pp.1114-1120
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• 2011

Shaped Charge's penetration performance is depended on the shape of warhead and explosive, liner materials. The liner that manufactured to small homogeneous grain increase the penetration performance and decrease the deviation of penetration performance. This texture is obtained by forging process but, creating the process that remove crack and get small homogeneous grain is very hard. In this study, We success to get the homogeneous small grain texture through appling the most suitable process by DEFORM CODE analysis.

• The Transactions of The Korean Institute of Electrical Engineers
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• v.68 no.1
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• pp.145-152
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• 2019

A composite guidance scheme is proposed for air-to-ground anti-tank missiles launched from an airborne platform. Long-range anti-tank missiles usually use a fiber optic line (FOL) for the datalink between an operator and the missile to obtain real-time target information and to command the missile. Also, impact angle control is used to maximize the warhead effectiveness, but it should be carefully implemented due to interference between the launch platform and the FOL. Thus, the proposed guidance scheme takes into account both impact angle and FOL constraints. Under system lag and acceleration limits, a selection method of guidance gains and calculation logic of the maximum achievable impact angle are proposed for a guideline of practical implementation. The performance of the proposed guidance scheme is investigated by nonlinear simulations with various engagement conditions.