Journal of the Korea Institute of Military Science and Technology 

About: Journal of the Korea Institute of Military Science and Technology is an academic journal published by Korea Institute of Military Science and Technology. The journal publishes majorly in the area(s): Computer science & Radar. It has an ISSN identifier of 1598-9127. It is also open access. Over the lifetime, 1174 publications have been published receiving 1010 citations. The journal is also known as: Journal of the Korea Institute of Military Science and Technology & Journal of the KIMST.

A Requirement Assessment Algorithm for Anti-Ballistic Missile Considering Ballistic Missile's Flight Characteristics

Abstract: A Ballistic Missile(BM) is a missile that follows a sub-orbital ballistic flightpath with the objective of delivering one or more wardheads to a predetermined target and An Anti-Ballistic Missile(ABM) is a missile designed to destroy a ballistic missile before reaching its target. The main objective of this study is to assess the requirement of ABM by considering both flight characteristic of the SCUD-B/C, Nodong missiles and intercept performance of ABM in the Lower tier Ballistic Missile Defense(BMD). The Ballistic Missile`s flight characteristics, such as trajectory, velocity etc., are estimated by simulation using the physical motion equations. The requirement of ABM is calculated by evaluating whether the BMD forces can defend those when the ballistic missiles attack prime facilities.

Classification of Chemical Warfare Agents Using Thick Film Gas Sensor Array

Abstract: Semiconductor thick film gas sensors based on tin oxide are fabricated and their gas response characteristics are examined for four simulant gases of chemical warfare agent (CWA)s. The sensing materials are prepared in three different sets. 1) The Pt or Pd as catalyst is impregnated in the base material of by impregnation method.2) or is added to by physical ball milling process. 3) ZnO or is added to by co-precipitation method. Surface morphology, particle size, and specific surface area of fabricated sensing films are performed by the SEM, XRD and BET respectively. Response characteristics are examined for simulant gases with temperature in the range 200 to , with different gas concentrations. These sensors have high sensitivities more than at 500ppb concentration for test gases and also have shown good repetition tests. Four sensing materials are selected with good sensitivity and stability and are fabricated as a sensor array A sensor array Identities among the four simulant gases through the principal component analysis (PCA). High sensitivity is acquired by using the semiconductor thick film gas sensors and four CWA gases are classified by using a sensor array through PCA.

An Evaluation of Silencer Characteristics by Live Firing Test

Abstract: The present work addresses an experimental study on sound attenuation characteristics of silencer by live firing test. When a gun fires, there exists excessive noise which propagates as a form of blast wave. As muzzle energy of the weapon systems increases, the level of impulsive noise also increases. It is well known that the impulsive noise from a gun gives a serious damage to human bodies and structures. The adverse effects of impulsive sound also cause both social and military problems. So it is very important to study the characteristics of the impulsive sound attenuation. The live firing test is performed to evaluate the effect of four different silencers. The test result is compared with the case of bare muzzle which is not installed the silencer. The frequency characteristics are also analyzed to investigate the diminution of sound pressure level. The results of this study will be helpful to the designing silencer for large caliber weapon systems.

Nonlinear Aeroelastic Simulation of a Full-Span Aircraft with Oscillating Control Surfaces

Abstract: In this paper, the transonic and low-supersonic aeroelastic behavior of the generic fighter model was investigated in the time domain. The simulation of flutter flight test using forced harmonic motion of control surfaces including inertial coupling effects was conducted at the various conditions. The detailed dynamic aeroelastic responses are computed using a coupled time-marching method based on the effective computational structural dynamic and computational fluid dynamics techniques. The nonlinear aerodynamic effects due to an existing shock wave on the lifting surfaces were considered using a transonic small disturbance equation. A modal model obtained by a free vibration analysis was used for the structural model. The relations between the computed flutter boundary and the simulation results of the responses using the harmonic motions of control surfaces at various conditions were investigated.