• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.5
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• pp.19-28
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• 2014

Firing test of solid rocket motor with pintle-technology carried out and the measured pressure-time curve was compared with the values predicted by the internal ballistic and performance analysis. Without baffle, the measured combustion chamber pressure was similar with the predicted pressure at the beginning of combustion, but gradual increase in pressure, which was unexpected with the end-burning grain of which burning area is constant, was observed. A baffle was inserted to make uniform flow over the pintle. Unlike the thruster without baffle, the measured combustion chamber pressure was 1.4 times higher than the predicted value. Through the CFD simulation, 10% of total pressure loss of the flow was observed from combustion chamber to nozzle throat when the baffle was inserted. The measured pressure with baffle was predicted well by considering the total pressure loss in the internal ballistic modelling and performance analysis.

• 제어로봇시스템학회:학술대회논문집
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• 1997.10a
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• pp.1-3
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• 1997

This paper presents a muzzle velocity measuring equipment(MVME) for the AN/UPQ6 model using doppler signals, which are generated from the difference of the transmitter signals and the receiver signals. It describes the principles of a velocity measurement, a ballistic analysis program and the accuracy of the MVME. With a comparison between the existence velocity meter and this system, the accuracy and the usefulness of this equipment is validates.

• KIPS Transactions on Computer and Communication Systems
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• v.4 no.12
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• pp.399-408
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• 2015

In the direct Gun Fire Control System(GFCS), it is essential to analyze the impact of the specific error components on the hit probability to optimize the system design. For this purpose the sensitivity equations of these error components are conveniently used, but it is too difficult to get those equations for the complex system with too many system elements. Normally sensitivity analysis is performed using numerical and statistical methods for the ground combat system. This method requires much computation, and makes us difficult to estimate the sensitivity change of specific error component intuitionally for the changing operating conditions. In this paper we propose a set of sensitivity equations deriving from closed form solution of the ballistic differential equation for the bullet. They are handy equations with very little computations, easy to understand the physical meaning of the related system variables. Some simulation results are shown to demonstrate usefulness of our algorithm for the 30mm projectile.

• Journal of the Korea Society for Simulation
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• v.24 no.3
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• pp.9-16
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• 2015

This research focuses on analysis of the flight trajectory characteristics of SLBM (Submarine Launched Ballistic Missile) of North Korea. Recently, North Korea tested launching of SLBM which is threatening international security. Also it is known that North Korea had possessed the technologies about SLBM since they disassembled submarines out of commission of the former Soviet Union. If the development of the SLBM of North Korea is completed, it should be affected as asymmetric threat to South Korea. Therefore, for active respondence to these threat, it is essential to analyze the SLBM systematically. In this point of view, this work made a SLBM flight model and simulated. In addition, we controled flight trajectories according to adjusting loft angle and described their characteristics. The sea-based ballistic missile defense system is required for an effective response to the flight trajectory of the SLBM from mid-course to terminal phase.

• Journal of Satellite, Information and Communications
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• v.12 no.4
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• pp.78-86
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• 2017

Japan has a lot of interest about weapons systems development of surrounding national and has invested heavily in securing intelligence assets to get information about them, because of conflict issues between Japan and Russia with four northern islands, China with Senkaku Islands and entry policy into the Pacific. Japan has used a large budget to detect and intercept ballistic missile for reasons of the launch of the Taepodong missile in 1998. After took over SIGINT equipments which U.S. force had operated in 1950s~1960s, Japan made a technological analysis and advanced IT technology to produce superior equipments. Japan's SDF has installed them in 19 locations across Japan. In addition, Japan's JASDF has installed advanced early warning RADAR to detect aircraft and high speed ballistic missile entering JADIZ with S-band in 28 locations across Japan. It is possible to detect missile launch preparations, engine tests, and launch moments at any time for operation of 6 satellites high resolution reconnaissance system and 6 aegis ships. In close cooperation with the US, Japan is accessible to the SBIRS networks which detects the launch of a ballistic missile in neighboring countries. In the future, Because the United States wants Japan to act as part of the United States in East, south Asia, it is believed that the exchange of intelligence on the surrounding countries between two countries will be enhanced.

• Journal of IKEEE
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• v.22 no.2
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• pp.420-426
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• 2018

In the near future, CNTFET(Carbon NanoTube Field Effect Transistor) is considered as one of the most promising candidate for the replacement of modern silicon-based transistors by utilizing the ballistic or near-ballistic transport capability of CNT(Carbon NanoTube). For the large-scale fabrication of high performance CNTFET, semiconducting CNTs have to be well-aligned with a fixed pitch and high densities in the each CNTFET. However, due to the immaturity of the CNTFET fabrication process, CNTs can be unevenly positioned in a CNTFET and existing HSPICE library file cannot support the circuit level evaluation of performance variation caused by the unevenly positioned CNTs. To evaluate the performance variation, linear programming methodology was suggested previously, but the errors can be made during the calculation of the current and the gate capacitance of a CNTFET. In this paper, the reasons causing errors will be discussed in detail and the new methodology to reduce the errors will be also suggested. Simulation results shows that the errors can be reduced from 7.096% to 3.15%.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.40 no.3
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• pp.281-288
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• 2016

The ballistic performance data of composite materials is distributed due to material inhomogeneity. In this paper, the uncertainty in residual velocity is obtained experimentally, and a method of predicting it is established numerically for the high-speed impact of a bullet into laminated composites. First, the failure strain distribution was obtained by conducting a tensile test using 10 specimens. Next, a ballistic impact test was carried out for the impact of a fragment-simulating projectile (FSP) bullet with 4ply ([0/90]s) and 8ply ([0/90/0/90]s) glass fiber reinforced plastic (GFRP) plates. Eighteen shots were made at the same impact velocity and the residual velocities were obtained. Finally, simulations were conducted to predict the residual velocities by using the failure strain distributions that were obtained from the tensile test. For this simulation, two impact velocities were chosen at 411.7m/s (4ply) and 592.5m/s (8ply). The simulation results show that the predicted residual velocities are in close agreement with test results. Additionally, the modeling of a composite plate with layered solid elements requires less calculation time than modeling with solid elements.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2008.03a
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• pp.226-234
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• 2008

Grain design has always been a vital and integral part of Solid Rocket Motor(SRM) design. Basing on the design objectives set by the system designer, the SRM designer has many options available for selecting the Grain configuration. Many of the available configurations may fulfill the required parameters of volumetric loading fraction, web fraction & Length to diameter ratios and produce internal ballistic results that may be in accordance to the design objectives. However, for any given set of design objectives, it is deemed necessary that best possible configuration be selected, designed and optimized. Hence optimal results of all applicable configurations are vital to be attained in order to compare and finalize the design that will produce most efficient performance. Generally the engineers pay attention and have skills on a specific grain configuration. The designing methodologies and computer codes available usually focus on single grain configuration may it be Star, Wagon Wheel or slotted tube. Hardly one can find a software or a design methodology where all such configurations can be worked on jointly and not only adequate designs be found but optimal solutions reached by applying an optimization method to find final design best suited for any design objective. In the present work design requirements have been set, grain configurations have been selected and their designing has been conducted. The internal ballistic parameters have been calculated and after finding the preliminary design solutions, the optimal solutions have been found. In doing so, software has been developed comprising of computer programs for designing the 2D grains including Star, Wagon Wheel and Slotted Tube configurations. The optimization toolbox of Matlab Fmincon has been used for getting optimal solutions. The affects of all the independent geometric design variables on the optimized solutions have been analyzed. Based on results attained from Optimization Method, an in depth comparison of Grain Configurations and analysis of performance prediction outputs have been conducted to come to conclusion as to which grain configuration is ideal for the current design requirement under study.

• Journal of Aerospace System Engineering
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• v.15 no.3
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• pp.57-64
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• 2021

In the study, to minimize the error on guided control of the KV (Kill Vehicle) and to secure the hit-to-kill performance, a position accuracy inspection for the DACS (Divert and Attitude Control System) actuation system was proposed. The accuracy performance of the DACS actuation system is one of the most important factors in the interception of ballistic missiles. In order to validate actuation control accuracy of DACS system, an inspection item was set for position accuracy, and the inspection system was designed for DACS pintle. To measure the absolute position value of the DACS pintle, an external measurement system was developed using laser displacement sensors. The inspection system was designed so that it can be compared with the actuation command in real time. The proposed position accuracy inspection system can be inspected not only in a DACS system but also in missile system level. The position accuracy inspection was performed using the designed inspection system, and analysis of the inspection result.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2006.05a
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• pp.7-10
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• 2006

A quasi-equilibrium model is used in order to aid movement and ballistic analysis for a propellant actuated device(PAD) system. The validity of the model is examined by experiments of a PAD system. The appropriateness of its usage for application was explored by comparing the tendency of experiments and analysis results, and the coefficients of friction and heat loss were obtained. The design method developed will be applied to the design of PAD systems.