• KDI북한경제리뷰
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• v.22 no.11
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• pp.53-62
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• 2020

• KDI북한경제리뷰
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• v.22 no.1
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• pp.104-118
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• 2020

• KDI북한경제리뷰
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• v.23 no.8
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• pp.50-55
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• 2021

• KDI북한경제리뷰
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• v.21 no.4
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• pp.23-38
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• 2019

• Defense and Technology
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• no.6 s.124
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• pp.8-11
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• 1989

한국국방연구원(KIDA)이 주최하고 한국방위산업진흥회(KDIA)가 후원한 "방위산업 정책토론회"가 4월27일 한국국방연구원에서 성황리에 개최되었다. 이번 토론회는 1970년대 초반 태동된 방위산업에 대한 전반적인 평가와 전망을 진단하고, 향후 발전방향을 모색하기 위해 마련되었다. 총 4개 부문으로 나뉘어 진행된 이번 토론회는-제1토론 : 방위산업의 평가, 역할 및 전망, 제2토론 : 국방연구개발 활성화방안, 제3토론 : 군사기술이전과 국제방산협력, 제4토론 : 방위산업 육성정책등의 주제에 관해-각계 전문가의 발표에 이어 종합토론의 순서로 이어졌다. 이 좌담회 글은 Panel 토론자들의 토론내용을 요약 및 발췌하여 정리한 것이다

• Journal of the Korea Institute of Military Science and Technology
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• v.25 no.2
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• pp.117-124
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• 2022

Single-ring circular array antennas can be applied to direction finding systems in order to use nose-section in other purposes, and the interferometry is a proper direction finding method to those systems. We usually make the interferometer baseline long enough to achieve good angular accuracy. However, an interferometer with baseline longer than a half-wavelength has the ambiguity problem. In this paper, we present a novel method for solving the ambiguity problem in interferometry systems. This technique is based on the amplitude comparison method and the space division table, and it can place a target within the angular region in which the ambiguity problem does not occur by roughly estimating direction-of-arrival. The Monte Carlo simulation results show that proposed method can effectively remove the ambiguity problem in the system.

• 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 Institute of Military Science and Technology
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• v.26 no.2
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• pp.171-178
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• 2023

PCM data is result of air-vehicle flight test, this data is distributed for each engineers to analyze its condition. Since line-of-sight between the air-vehicle and the ground receiver cannot always be secured, remote PCM data recording system was claimed to be required. In this paper multi-function PCM data recorder has been described. This PCM data recorder was intended to place on inside of flight object. It can record about two hours in 32 GB SD card with maximum 7 Mbps data rate. RS-422/485 and RJ-45 interface enhanced accessibility for users. 5 V and 1 A power consumption and 19.5 mm × 152.5 mm × 102.3 mm allow to connect with mobile PCM devices. It acquired more than 190-minutes data in 12-times flight test. Also, it achieved military standard environmental test MIL-STD-810G to prove its stability and solidness.

• Journal of the Society of Naval Architects of Korea
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• v.60 no.4
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• pp.256-265
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• 2023

This paper describes the results of the development of the submarine Free Running Model (FRM). First, the goal of development was set based on the test conditions and the test environment, and the system was obtained accordingly. The target submarine, Joubert BB2 submarine, was selected with a scale of 18.35 in accordance with the development goal. In order to conduct a submarine FRM test underwater, where communication is impossible, the FRM must operate at least semi-autonomously. For this purpose, an Extended Kalman Filter (EKF) based underwater integrated navigation system and control system using a sailplane and an X-shaped sternplane were designed respectively. In addition, a ballast system was designed to enable the model to float to the water surface in case of an emergency. To verify its propulsion, navigation, and control performance, the FRM tests were conducted in both indoor and outdoor basins. As a result, the relationship between propeller RPM and vehicle speed was derived, and it was confirmed that the navigation and control performance met the target value.

• Journal of the Korea Institute of Military Science and Technology
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• v.27 no.1
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• pp.70-79
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• 2024

This paper describes the results of the development of the the unmanned aerial vehicle system integration laboratory(UAV SIL) for the integrated verification. This UAV SIL is designed to test the robustness of the UAV system including the operational logics and the flight control system behaviors under many abnormal and emergency conditions such as data-link losses, airborne subsystem failures, engine shut down conditions, and ground control station faults. This paper presents how to build the UAV SIL and how to verify the in-development UAV system through the UAV SIL.