• Nuclear Engineering and Technology
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• v.46 no.1
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• pp.73-80
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• 2014

A concrete cask is an option for spent nuclear fuel interim storage. A concrete cask usually consists of a metallic canister which confines the spent nuclear fuel assemblies and a concrete overpack. When the overpack undergoes a missile impact, which might be caused by a tornado or an aircraft crash, it should sustain an acceptable level of structural integrity so that its radiation shielding capability and the retrievability of the canister are maintained. A missile impact against a concrete overpack produces two damage modes, local damage and global damage. In conventional approaches [1], those two damage modes are decoupled and evaluated separately. The local damage of concrete is usually evaluated by empirical formulas, while the global damage is evaluated by finite element analysis. However, this decoupled approach may lead to a very conservative estimation of both damages. In this research, finite element analysis with material failure models and element erosion is applied to the evaluation of local and global damage of concrete overpacks under high speed missile impacts. Two types of concrete overpacks with different configurations are considered. The numerical simulation results are compared with test results, and it is shown that the finite element analysis predicts both local and global damage qualitatively well, but the quantitative accuracy of the results are highly dependent on the fine-tuning of material and failure parameters.

• Journal of the Korea Institute of Military Science and Technology
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• v.26 no.2
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• pp.149-158
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• 2023

To predict the aerodynamic characteristics of the grid fins from subsonic to supersonic speeds, low fidelity SW as well as CFD SW were applied. VLM(Vortex Lattice Method) and SE(Shock-Expansion) method were used at subsonic and supersonic speed domain respectively for the rapid prediction of low fidelity SW. For 2 configurations of the grid fins, the CFD computations and tests using the trisonic wind tunnel were also performed to compare the results of the grid fins. The results of low fidelity SW, CFD SW and the wind tunnel tests data were agreed well each other. Through further research on the grid fins, the effective parameters of the grid fin configurations according to the speed regime will be investigated.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.8
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• pp.37-43
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• 2018

A developer solves problems with isolating failures if faults are detected when inspecting missiles using the missile assembly test set (MATS) and then resumes the testing. In order to identify faults, it is necessary to analyze the data coming from the equipment, but the information received may not be sufficient, depending on the inspection environment. In this case, the developer repeats the test until the problem is reproduced or checks the performance of each piece of equipment that is related to the fault. When this task is added, schedule management becomes problematic, and development costs rise. To solve this problem, we need to design a MATS in a systematic way to increase fault coverage while satisfying the required reliability. By designing the necessary processes for each procedure, it is possible to reduce the fault identification time when a fault is detected during operations. But it is not possible to guarantee 100% fault coverage, so we provide another method by comparing costs and effects. This paper describes a development method to enhance the reliability of the missile assembly test set; it describes the expected effects when it is adapted, and describes the limitations of this method.

• Journal of Advanced Navigation Technology
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• v.22 no.2
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• pp.70-75
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• 2018

The mounted store on an aircraft shall be subjected to an ground separation test to verify that a safe separation has been made before it is actually installed to the aircraft. In this study, ground ejection test was conducted with dummy missile to verify the stability of the drop on the land. Bomb rack unit essential to testing ground ejection test, operate at high pressure and produce a significant ejection force to push the missile away from any large orifice. Bomb rack unit modified their bombe pressure and orifice diameter to photograph the drop movement of dummy missile with high-speed camera and to analyze their drop displacement and speed. It is considered useful to provide the initial data for the ejection force analysis on aircraft with actual flight and to carry out the ground separation tests of aircraft with future developments.

• Journal of the Korea Society of Computer and Information
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• v.9 no.1
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• pp.63-70
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• 2004

This paper describes modeling, design and performance test results of infrared thermal image target system which can generate infrared thermal image on aircraft. The system is designed to control image shape and intensity so that the infrared image shape and its emitting intensity are so similar to that of real aircraft. When applying the technique suggested in this paper, the system consumes only small electric power energy about 30(㎾) to generate infrared thermal image which is equivalent to that of real aircraft under full power operation. After verifying performance test, the system developed here has been used as a target for korean potable surface to air missile(KPSAM) at the stage of evaluation test such as target adaptive guidance test and auto-pilot logic test.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.10
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• pp.817-824
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• 2017

This paper presents the characteristics of wing-tail interference for a tail-controlled missile. The magnitude of wing-tail interference was calculated with wind tunnel test results and its effects on aerodynamic coefficients were investigated. The downwash angle of tail wing was calculated with experimental data and the effect of wing-tail interference was expressed as a ratio of angle of attack. Numerical simulations were made to examine flow characteristics of wing-tail interference and the vorticity contour of missile were compared with respect to angle of attack. Experimental and numerical analysis results show that the wing-tail interference has significant effects on static stability of tail-controlled missile.

• Journal of Advanced Navigation Technology
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• v.19 no.5
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• pp.363-369
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• 2015

This paper describes deployment of a sea based sensor platform for the detection of a submarine launched ballistic missile (SLBM). Recently, North Korea successfully conducted the underwater launching test of the SLBM, which will seriously threaten the global security. To defend these threats successfully, a sensor platform of the ballistic missile defense (BMD) should be deployed in the area of high detection probability of the missile. The maximum detection range characteristics of the typical radar sensor system, however, depend on the radar cross section (RCS) and flight trajectories of the target. In this point of view, this work analyzed the flight trajectories based on the tactics and calculated the RCS of the SLBM. In addition, sea based sensor platform position is proposed from the analysis of the detection time.

• Journal of the Korea Institute of Military Science and Technology
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• v.16 no.5
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• pp.598-606
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• 2013

After the missile is launched, the umbilical connector should be separated from it without any physical interference. The umbilical separation device, for this purpose, was developed by means of new concept. Using the investigation of various methods to separate the umbilical connector, a suitable method was selected and a corresponding device was designed and manufactured. To ensure the performance of the developed device, numerical analysis and performance test were conducted and correction was followed. The umbilical separation device was applied to real system operation test and its operation performance was tested. In consequence, several problems were founded, however, good results were generally obtained.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.4
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• pp.452-459
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• 2019

In order to design and manufacture structures such as a guided missile, assembly process with fastener is an essential method of fabrication. In this study, the dynamic characteristics of a cylindrical structure with bolted joints were studied using experimental methods. The change of the natural frequency of the structure with the change of the fastening method and the tightening torque were measured by the test and the finite element analysis was performed using the stiffness model of the fastening part according to the fastening method and compared with the test results.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.20 no.9
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• pp.488-494
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• 2019

Precision Guided Missiles after production and militarization have various characteristics that enable the final performance to be identified by conducting live-fire tests after long-term storage. Likewise, the performance and reliability of ${\bigcirc}{\bigcirc}$ Missiles, which are currently used by the Korean Navy, are also verified consistently by conducting live-fire tests after militarization. Specially, the live fire test at '00 year, which was conducted by Korean Navy, showed the result that 'Ring', which is a component of the canister's front cover, was jammed with wings for propulsion and then broke away from the canister during the missile launch process. This situation led to an interruption of the deployment of wings and finally affected the missile's flight performance. The results of a survey of the canisters of those missiles whose live fire tests were conducted successfully, based on the live fire test at '00 year, showed the 'Ring's separation from canisters. This raises recognition for the need to solve the problems of 'Ring's separation and breakaway. This study suggests an improvement derived by the result of live-fire tests and introduces the effect of final launch performance of ${\bigcirc}{\bigcirc}$ Missiles and test result after applying the improvement.