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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korea Institute of Military Science and Technology
Journal Basic Information
Journal DOI :
The Korea Institute of Military Science and Technology
Editor in Chief :
Volume & Issues
Volume 6, Issue 4 - Dec 2003
Volume 6, Issue 3 - Sep 2003
Volume 6, Issue 2 - Jul 2003
Volume 6, Issue 1 - May 2003
Selecting the target year
A Calibration Technique and its Error Analysis for the Position of Seabed Sonar Target
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 15~21
This paper contains a precise calibration technique for the position of seabed acoustic target and theoretical error analysis of calibration results. The target is deployed on seabed as a standalone transponder. The purpose of target is performing accuracy test for active sonar as well as position calibration itself. For the position calibration, relative range between target and test vessel should be measured using target's transponder function. The relative range data combined with vessel position can be converted into a estimated position of target by the application of nonlinear LSE method. The error analysis of position calibration was divided into two stages. One is for relative range estimator and the other for target position estimator. Numerical simulations for position calibration showed good matching between results and developed CRLB.
System Requirement Definition Process from Operational Concept and The Application Case-Study of ATACMS
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 22~35
This paper describes system technical requirement development process from operational concept using computer-aided Systems Engineering tool(CASysE Tool-CORE). The army tactical missile system-ATACMS's technical requirements are developed by the process as a case-study The scope of the work is context analysis and requirement definition process. The proposed process is as follows. At first, an integrated architecture could be developed from the operational concept. From the integrated architecture a capability needs, which includes KPPs, are generated. And the capability needs expanded according to the Mil-Std-961D format. Lastly, a system technical requirement could be generated automatically from the CASysE Tool-CORE.
Development of Target Signal Simulator for Towed Line Array Sonar
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 36~43
Multi-target away signal simulator which can simulate the radiated noises of maneuvering targets in a specified ocean range is an essential equipment for the validation of developed towed array sonar system. This simulator should provide realistic multi-channel signals those are required for beamforming on the signal processing unit of towed away system. This paper describes the overall system configuration and signal synthesis techniques for the target radiated noise. And this paper considers why the time delays between target and individual sensors are caused and how to compensate these time delays to individual sensors output. This multi-purpose target simulator could be used for the training of TASS operators.
Characteristics of copper/C films on PET substrate prepared by ECR-MOCVD at room temperature
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 44~53
Cu/C films were prepared at room temperature under
atmosphere in order to obtain metallized polymer by using ECR-MOCVD(Electron Cyclotron Resonance Metal Organic Chemical Vapor Deposition) coupled with a DC bias system. The room temperature MOCVD on polymer substrate could be possible by collaboration of ECR and a DC bias. Structural analysis of the films by ECR was found that fine copper grains embedded in an amorphous polymer matrix with indistinctive interfacial layer. The increase in
contents brought on copper-rich film formation with low electric resistance. On the other hand carbon-rich films with low sheet electric resistance were prepared in argon atmosphere. The electric sheet resistance of Cu/C films with good interfacial property were controlled at
Ohm/sq. ranges by the
/Ar mole ratio and the shielding effectiveness of the film showed maximum up to 45dB in the our experimental range.
Gas Sensor added by Metal Oxide for DMMP
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 54~61
gas sensor for the detection DMMP, simulant of nerve gas was fabricated and its characteristics were examined. Sensing materials were
added by TEX>$\alpha$-
with 0∼20wt.% and
with 0∼3wt.% and were physically mixed each material. They were deposited by screen printing method on alumina substrate. The sensor was consisted of sensing electrode with interdigit(IDT) type in front and a heater in back side. Its dimension was 7
. Crystallite size 8t phase identification, specific surface area and morphology of fabricated
powders were analyzed by X-ray diffraction(XRD), surface area analyzer(BET) and by a scanning electron microscope(SEM), respectively. Sensor was measured as flow type and sensor resistance change was monitored as real time using LabVIEW program. The best sensitivities were 75% at adding 4wt.% TEX>$\alpha$-
, operating temperature
and 87% at adding 2wt.%
, operating temperature
to DMMP 0.5ppm. Response and recovery times were about 1 and 3 min., respectively. Repetition measurement was very good with
3% in full scale. As a result, operating temperature was lower TEX>$\alpha$-
, but sensitivity was higher
Characteristics of Constitutive Equations under Rod Impact Analysis by Smoothed Particle Hydrodynamics
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 62~73
The characteristics of constitutive equations, for hydrocodes, were Investigated by the comparison between the smoothed particle hydrodynamcis simulation and the experiment of rod impact test which resulted in a deformation history of impacting front where high strain and high strain rate dominate. The constitutive equations used in the simulation Is J-C(Johnson-Cook) model, Z-A(Zerilli-Armstrong) model, and S-C-G(Steinberg-Cochran-Guinan) model. The modification of Z-A model, based on the increased effect of strain-rate hardening, showed better correlation with expriment.
Synthesis and Characterization of N-Butyl-N-(2-nitratoethyl) nitramine
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 74~85
NENA(nitratoethyl nitramine) compounds, especially BuNENA(N-butyl-N-(2-nitratoethyl)-nitramine), are of high interest to both rocket propulsion and military high explosives because of low sensitivity to many forms of stimuli, although they are less energetic than conventional nitrate ester plasticizers. One of advantages in using NENAs is that they provide higher impulse at any given flame temperature than conventional propellants do. BuNENA has better thermochemical characteristics(low melting point and low glass transition temperature), therefore has less tendency to crystallize out of matrices. BuNENA was successfully synthesized in a high yield by reaction of n-butyl aminoethanol and 98% nitric acid followed by dehydrogenation of salt mixture by
A Review of the Theoretical Prediction of Nitrogen Clusters
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 86~102
Polynitrogen molecules are of great interest as potential high energy-density materials, and hence such structures of various isomers of nitrogen clusters have been calculated using molecular modeling techniques by the researchers from various sectors of scientific institutions. In this article, the predicted meta-stable structures of these hypothetical molecules have been thoroughly reviewed.
Performance Analysis of Air Turbo Ramjet using
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 103~110
The present work was conducted to achieve the better understanding of the performance analysis technique for the expander type air turbo ramjet engine. For this purpose, the performance analysis was carried out using a small engine(8.0kN thrust) with two types of fuels. From this analysis, at the same input condition, the thrust of methane-fueled engine was 25% lower than that of hydrogen. In addition, the case of methane shows the inapplicable engine performance cycle.(i.e., The compressor work exceeds the turbine output power) These results come mainly from the different heating value of each fuel and specific heat. This analysis also shows that, to build a same performance cycle as the hydrogen case, the methane-fueled engine requires increased air and fuel flow rates, increased turbine expansion ratio, and decreased compressor pressure ratio.
The Multi-Aperture Transmit Horn Antenna for Radar Space Feeder
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 113~121
In this paper, the transmit antenna for the space feeder used for the phased array antennas is investigated. The multi-aperture horn antenna is proposed as the transmit antenna and the characteristics are verified with the Matlab coding, HFSS of Ansoft Corp., and MWS of CST Corp., The E-plane and H-plane beam patterns of the multi-aperture horn antenna are nearly symmetrical and the sidelobe level of the I-plane beam pattern is lower than that the of general pyramidal horn antenna. The fabricated multi-aperture horn antenna is measured using the near-field measurement system. The measured results show good agreement with the simulated ones.
Mixed Control of Agile Missile with Aerodynamic Fin and Thrust Vectoring Control
Journal of the Korea Institute of Military Science and Technology, volume 6, issue 3, 2003, Pages 122~130
This paper is concerned with a control allocation strategy using the dynamic inversion and the pseudo inverse control which generates the nominal control input trajectories, and autopilot design using time-varying control technique which is time-varying version of pole placement of linear time-invariant system for an agile missile with aerodynamic fin and thrust vectoring control. Control allocation of this paper is capable of extracting the maximum performance from each control effector, aerodynamic fin and thrust vectoring control, by combining the action of them. Time-varying control technique for autopilot design enhance the robustness of the tracking performance for a reference command. The main results are validated through the nonlinear simulation.