• Journal of the Korea Institute of Military Science and Technology
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• v.20 no.2
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• pp.255-263
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• 2017

An infrared-guided missile has been emerging as a major threat against combat aircraft due to its passive guidance characteristics and with recent advances in stealth technology. Hence, the infrared stealth technology and its effectiveness-evaluation technique become more significant than ever before. In this study, we applied missile aerodynamics to lethal range calculation which allowed more precise prediction. CFD analyses were newly involved in estimating drag force characteristics of an infrared-guided missile. Velocity profiles during flight period of the missile were constructed utilizing these drag characteristics and then incorporated into our in-house code to predict corresponding lethal ranges. The results showed that the present method can predict lethal range more appropriately than the previous one with constant velocity profile. As one of the results, if a fighter gains altitude more which reduces less drag of the attacking missile, then the lethal envelope increases significantly more compared to the lock-on envelope.

• Journal of the Korea Institute of Military Science and Technology
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• v.22 no.6
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• pp.745-753
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• 2019

Recently, with the development of long-range / high-altitude guided weapon system for defense against ballistic missile, test range and firing altitude for guided weapons are increasing. Due to the increase in the test range and the intercepting altitude, it is expected to increase the range of safety area required for the firing test. Comparing to the foreign countries which have many desert or non-residence, in the domestic circumstances where the population is concentrated and distributed, it is more important to predict the falling area and to set the safety area for safely carry out the long-range / high-altitude intercept test. In this paper, we consider the following three points. The first is the booster fall trajectory modeling, the second is the shroud fall trajectory modeling, and finally, the debris dispersion modeling for the missile intercept. Especially, the AUTODYN model was used to predict debris falling area which produced in the high-speed guided missile intercepting test.

• Journal of Advanced Navigation Technology
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• v.23 no.2
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• pp.97-103
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• 2019

In this paper, we designed and fabricated a receiving modem that can be applied to guided weapons can change real-time targets with little effect of fading. The designed modem consists of synchronous detector, timing error estimator, timing recovery, differential decoder and viterbi decoder, and it's implemented in FPGA so that it can be redesigned and modified according to requirements. The modem board was directly converted from IF frequency to baseband and converted into digital data through ADC. It is confirmed that it is applicable to the guided weapons that changing real-time targets through simulations, measurements and test.

• Journal of the Korean Society of Safety
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• v.30 no.4
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• pp.142-150
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• 2015

A portable recoilless guided missile generates a strong back blast and impulsive noise at the nozzle when it launches. In the case of indoor operations, the hazard of the blast noise from a recoilless weapon increases due to limited indoor spaces. Also, the noise levels determine the operational feasibility of a weapon; therefore, it is important to predict the blast noise levels distribution in the indoor space in advance. In addition, computational fluid dynamics (CFD) method generally used for fluid related simulations, requires high computing cost and time to simulate the whole domains. The domain includes both blast wave region and large and various indoor space region. Therefore, an efficient method for predicting the far-field noise level within a short time should be developed. This paper describes an analysis model for predicting the indoor noise distributions by considering the shape effect of the building within a short time. A new developed blast wave model was implemented using the noise source. Additionally, noise reflections at the closed surfaces such as walls and noise transmissions at the opened surfaces such as windows and doors were considered in calculating the noise levels. The predicted noise levels were compared with the experimental data obtained from the indoor launch test to validate the reliability of program.

• Journal of the Korean Society of Safety
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• v.30 no.2
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• pp.63-69
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• 2015

Recoilless weapons, which lead strong back blast and impulse noise more than 160 dB, have been used in compliance with the regulation of the safety zone for the safe operations. However, the safety zone regulations for the newly developed weapons should be prepared since the existing guidelines do not provide any information concerning the reason for the safety zone. In this study, the outdoor launch tests were performed to collect the data such as noise, pressure and temperature of the back blast. An assessment method using data obtained from launch tests has been proposed to determine the safety zone. The safety zone has been determined with consideration for the following criteria: Impulse noise, temperature and pressure of the back blast and blast angle. As a results, new safety zones for them have been established for the recoilless weapon developed by ADD (Agency for Defense Development). We expect that this research can be used as a guideline for establishing a new safety zone regulation of similar weapon to be developed.

• Journal of Positioning, Navigation, and Timing
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• v.4 no.1
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• pp.9-16
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• 2015

The applications of Global Navigation Satellite System (GNSS) receivers are becoming wider in various commercial and military systems including even small weapon systems such as artillery shells. The precision-guided munitions such as Small Diameter Bomb (SDB) of United States can be used for pinpoint strike by acquiring and tracking GNSS signals in high mobility situation. In this paper, a small GNSS receiver with embedded interference suppression capability working under high dynamic stress is developed which is applicable to the various weapon systems and can be used in other several harsh environments. It applies a kind of matched filter and multiple correlator schemes for fast signal acquisition and tracking of even weak signals and frequency domain signal processing method to eliminate the narrowband interference. To evaluate the performance of the developed GNSS receiver, the test scenario of high mobility and interference environment with the GNSS simulator and signal generator is devised. Then, the signal acquisition time, navigation accuracy, sensitivity, and interference suppression performances under high dynamic operation are evaluated. And the comparison test with the commercial GNSS receiver which has high sensitivity is made under the same test condition.

• Journal of the Korea Institute of Military Science and Technology
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• v.19 no.5
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• pp.606-612
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• 2016

A Captive Flight Test(CFT) is used to verify the performance of missile component such as seeker and guiding algorithm of missile. Recently most of surface to air missile adapts multi-mode guidance method which include command guidance and active/passive guidance. A CFT system for missile system adapting multi-mode guidance method consists of pod equipment, command transmitting system and measuring system. In this paper, we proposed CFT system and testing method for missile which adapt multi-mode guidance, and system integration procedure by using distributed missile system integration method and procedure. The proposed CFT system and system integration method was applied to CFT of surface to air missile, and brought successful result.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.11a
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• pp.463-466
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• 2008

The weapon systems with a liquid propulsion engine have been used for various purposes and demands of the liquid fuel with variety of properties for its operational purposes and environment. The cyclic hydrocarbons including norbornane or dicyclopentane structures have many applications to the guided weapon systems due to the high density and high energy characteristics, also efforts have been given in many fields. In this study, the cyclic hydrocarbons that we designed and fabricated were investigated to obtain tendency on the structures.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.35 no.11B
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• pp.1704-1709
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• 2010

A small number of countries are leading the world in the development of advanced weapon systems. In general, the access to the information on the design of advanced systems is limited. As such, when similar weapon systems need to be developed, a special methodology must be considered to catch up with both the technological and information barriers. In this paper, we study a design methodology based on the combination of the reverse engineering and the design structure matrix (DSM) approach. The methodology begins by analyzing the advanced system by reverse engineering and produces a set of design results in the form of physical architecture, functional architecture and system requirements. The design results are further enhanced by applying the DSM clustering. As a result, one can get an improved design result. As a target system, a guided missile system was considered.

• Journal of Convergence for Information Technology
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• v.11 no.6
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• pp.113-119
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• 2021

Since the weapon system project has a large ripple effect on the country by investing a huge budget, analysis of acquisition methods that secured economic feasibility is required in the planning stage to promote the weapon acquisition project. In response to this demand, economic analysis for acquisition method is preformed in the research stage of previous studies, but the analysis on economic analysis for acquisition alternative is imperfect at the present. In this research, we identify the limitations of the effect analysis and propose an additional cost-benefit analysis method to analyze the economic feasibility of the acquisition alternative. It is possible to present the universal results of economic feasibility analysis for not only multiple alternatives but also single alternatives by presenting benefit/cost ratio. It is applied to research on acquisition project of OO guided rocket, and the result of economic analysis for each alternative is presented.