• Journal of the Korea Academia-Industrial cooperation Society
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• v.17 no.12
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• pp.193-197
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• 2016

The performance of Precision Guided Missiles is estimated by using hit probability only, which is calculated by hits against total amounts of fires in current domestic live-fire tests. It has a limitation in judging the performance of all produced Precision Guided Missiles by using the calculated hit probability according to the result of live-fire test, because the overall characteristics of the produced Precision Guided Missiles are not considered. In other words, a method is needed to estimate the confidence level which is more reliable than simply calculated hit probability according to the result of live-fire test for guaranteeing the hit probability of Precision Guided Missiles by certain level, which is already being operated or produced. This paper introduces a method to estimate the confidence level of Precision Guided Missiles by minimum live-fire tests using Hypergeometric distribution and Bayes' rule suitable for the characteristics of Precision Guided Missiles, which are small production, high costs and unable to check whether the missile hits the target or not before the live-fire tests. Also, this paper suggests a reasonable confidence level for showing the performance of the Precision Guided Missiles using the results of live-fire tests and domestic and foreign literature, when the result of live-fire tests will be decided.

• Journal of the Korea Institute of Military Science and Technology
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• v.23 no.5
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• pp.494-501
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• 2020

When we develop an OpenGL-based coastline map that displays the high resolution data of GSHHG, it takes tens of seconds until the first scene is rendered. That is because it takes time to tessellate polygons with a huge number of vertices. A commonly used solution is that it converts original data to a customized data in advance, and it displays these. But if we should use original data to display a coastline map, we need to find another solution. In this paper we suggest using a polygon splitting technique to minimize tessellation time. In order to prove its effectiveness, we implemented a software applied this technique and measured its performance. The software applied this technique took a few seconds to display the first scene and we confirmed its effectiveness.

• Journal of the Korea Institute of Military Science and Technology
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• v.18 no.2
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• pp.173-180
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• 2015

North Korea has developed ballistic missiles over the past 30 years. It is believed that they have a variety of ballistic missiles more than 1,000. Because these ballistic missiles threaten South Korea directly, accurate analysis of them is essential. Flight trajectories of the ballistic missiles are generally changed by means of adjusting payload weight, Isp, flight path angle, and cut-off time. The flight path angle is widely used to control the missile range. However it is difficult to predict the missile trajectory exactly in real operational environment because the missile could be launched according to its intention and purpose. This work analyzed the 1,000 km range MRBM's trajectory characteristics from adjusting flight path angle which is depressed as well as lofted method. The analysis of missile trajectory characteristics is based on the simulation of the missile trajectory model developed by KNDU research team.

• Journal of the Korea Institute of Military Science and Technology
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• v.18 no.5
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• pp.558-565
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• 2015

The current methods, such as Binomial Probability Distribution or T-test, to calculate the number of samples of Precise Guided Missiles(PGMs) for test and evaluation are statistically problematic to make reasonable decisions thus use the budget efficiently. Also, the method to verify an accuracy rate of the PGMs using these old methods seems to be lack of objectiveness. This paper presents an effective, efficient solution adapted from the clinical medicine testing method of healthcare industry research, which may overcome our problems. This method considers and addresses both manufacturers' and consumers' risk simultaneously. By taking into account the weapon system project characteristics which take a relatively longer time and require higher-level budget, this approach also suggests a reasonable and feasible method to determine the amount of samples of the PGMs and making a criterion to verify an accuracy rate of the missiles that are required to test. Thus, this method is expected to contribute to acquisition and operations of high-reliability PGMs by MND and its field-users.

• Journal of the Korean Society of Systems Engineering
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• v.6 no.1
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• pp.33-39
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• 2010

Anti-surface missiles have been the most dangerous threat to the surface ships, therefore analyzing the defense effectiveness of surface ships against diverse anti-surface missiles attack strategies is very important to evaluate and anticipate the naval combat ship's abilities in terms of AAW (Anti-Air Warfare). In this paper, we don't study on the defense effectiveness of a ship against a missile, but focus on the defense effectiveness for surface ships against multiple missiles specialized in strategies of anti-surface missiles; ripple fire attack and simultaneous time on target attack (STOT). So, we conduct a variety of monte-carlo simulations with high-fidelity simulators, analyze the measure of defense effectiveness for the key factors of strategies and evaluate the effects and possible interactions of several factors through the analysis of the design of experiment (DOE).

• Journal of Institute of Control, Robotics and Systems
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• v.11 no.1
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• pp.84-91
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• 2005

In this paper, we describe the real-time parallel processing simulator developed for the use of performance analysis of rolling missiles. The real-time parallel processing simulator developed here consists of seeker emulator generating infrared image signal on aircraft, real-time computer, host computer, system unit, and actual equipments such as auto-pilot processor and seeker processor. Software is developed from mathematic models, 6 degree-of-freedom module, aerodynamic module which are resided in real-time computer, and graphic user interface program resided in host computer. The real-time computer consists of six TIC-40 processors connected in parallel. The seeker emulator is designed by using analog circuits coupled with mechanical equipments. The system unit provides interface function to match impedance between the components and processes very small electrical signals. Also real launch unit of missiles is interfaced to simulator through system unit. In order to apply the real-time parallel processing simulator to performance analysis equipment of rolling missiles it is essential to perform the performance verification test of simulator.

• Journal of the Korea Institute of Military Science and Technology
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• v.21 no.6
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• pp.842-849
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• 2018

This research suggests the development of simulator for a Simulation Test of a moving object's path generation and following. There are many kinds of moving objects in weapon systems, such as vehicles, missiles, robots and so on. So need tests of moving simulations during development process of weapon systems. To simulate a moving object, need an flexible path. So this report suggests a $B\acute{e}zier$ curve algorithm for generation of smooth curve path. And when new developments of weapon systems are started, many kinds of simulators are created. But, these simulators are not reused in other project because there are different kinds of development environment. So need to allow users to add specific features, And this report suggests using Dynamic Link Library(DLL).

• Journal of the Korea Institute of Military Science and Technology
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• v.26 no.1
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• pp.64-71
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• 2023

In the recent defence industries, it is required to develop the small and low cost embedded systems for guided missiles. According to the characteristics of guided missiles, the mission is conducted with multiple phases, which include a squib activation phase. By considering the unexpected squib activation, the squib system should be disabled after the launch of a guided missile. Therefore, the squib system needs to include the functions of the safe ignition and status check. This paper presents the squib ignition and status check circuits design for the compact embedded systems in guided missiles. Validation results show that for the functions of the squib ignition and status check, the presented circuits design performs well. The designed circuits also were implemented with various electronic devices and validated by the ground and flight tests.

• Journal of Advanced Navigation Technology
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• v.20 no.2
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• pp.134-140
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• 2016

This paper analyzed flight trajectory characteristics of ballistic missiles considering effects of drag forces. It is difficult to intercept ballistic missiles which fly over atmosphere with supersonic speeds and small radar cross section (RCS). In particular, the velocities in the phases of boost and terminal are changed significantly due to the steep variation of the drag force. Therefore, in order to build up a successful ballistic missile defense systems, the effects of the drag forces should be considered in the analysis of ballistic missile trajectory characteristics. In this point of view, this work analyzed the effects of drag forces and derived the flight trajectory characteristics of Scud B, C and Nodong missiles. Model of the ballistic missile flight trajectory is considered the effects of Coriolis and centrifugal forces, and specifications of the missiles are open sources.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.3
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• pp.203-211
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• 2016

In contrast with STT missiles, the guidance law design for BTT missiles should be based on 3-dimensional pursuit kinematics, since the pitch and roll channels of BTT missiles are coupled dynamically. More generally than the prior works, the dynamics of pitch and roll channels, as well as 3-dimensional pursuit kinematics are considered in the design of our terminal-phase optimal guidance law for BTT missiles proposed in this paper. Thereby, the proposed optimal guidance law guarantees high capturability with small miss distance without significant performance degradation due to time-lag effect even in case of relatively slow autopilot dynamics. Moreover, the resulting optimal guidance law is expressed explicitly in feedback-form with the coefficients given as the functions of time-to-go. The effectiveness and practicality of our work is demonstrated through various simulation results.