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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
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Journal DOI :
The Korea Institute of Military Science and Technology
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Volume & Issues
Volume 9, Issue 4 - Dec 2006
Volume 9, Issue 3 - Sep 2006
Volume 9, Issue 2 - Jun 2006
Volume 9, Issue 1 - Mar 2006
Selecting the target year
A Kill-Assessment Technique Using Hypothesis Testing and Kalman Filter
Kim, Ho-Jeong ; Lee, Dong-Gwan ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 5~14
The correct and opportune decision of reengaging the intercepted target is required in order to enhance the engagement performance of the surface to air missile systems that has the ability to defense or attack against various targets at the same time. The engagement efficiency and success of these systems will be largely enhanced by assigning quickly its system resources to the intercepted target and minimizing the waste of system resources for the target which is not able to attack any more. The kill-assessment algorithm has to be able to evaluate automatically whether various targets intercepted by missiles are killed or not on the basis of the reasonable confidence level. The definition of kill assessment is discussed and the kill assessment algorithm is designed reliably by using Kalman filter and a probability theory. Finally its performance is evaluated and analyzed by the Monte Carlo simulation.
Full Scale Airframe Static Test of 4 Seater Canard Airplane
Shin, Jeong-Woo ; Kim, Sung-Chan ; Kim, Sung-Jun ; Chae, Dong-Chul ; Lee, Sang-Wook ; Kim, Tae-Uk ; Shim, Jae-Yeul ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 15~23
In this paper, full-scale airframe static test of 4-seater canard airplane(the Firefly) was explained. From the results of the structural analysis, 5 design limit loads test conditions and 11 design ultimate loads test conditions were selected. Test loads analysis was performed and test fixtures and load control system(LCS) were prepared to realize the test loads. To protect the test article during the test, the overload protection system was prepared. Strain and deflection values were acquired through the data acquisition system(DAS) to verify the structural analysis results.
A Frequency Resource Assignment Algorithm for FH Radio Using Isotropic Multi Dimension Array
Lee, Seong-Min ; Han, Joo-Hee ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 24~31
To reduce the interferences between the radio equipments which are operated in frequency hopping mode, the frequency resource should be assigned to each equipment without overlapping when several groups of radio equipments operate in the same area. If the radio equipments are in a different area, the partial frequency overlaying can be permitted. From the isotropic multi-dimensional array, several frequency assignment tables can be extracted for a same area. Also several tables can be extracted for different areas. Since there can be no overlapped frequencies between the tables for the same area, no interference between the radio equipments in an area is guaranteed. The frequencies overlapped between 2 tables for 2 different areas are pre-planed as required. The interference performance in frequency hopping radio can be controlled as desired using the proposed Frequency Resource Assignment Algorithm using Isotropic multi-dimensional Array.
CDMA Pilot Receiving Circuit Using Sequence Estimator
Lee, Seong-Min ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 32~38
In this paper a sequence estimator of CDMA communication system is suggested. A sequence estimator uses Galois Field operation. A sequence estimator can provide another CDMA pilot signal which is un-modulated spreaded signal. A estimated sequence signal and received signal have no correlation. Tow signals can be summed using MRC(maximal ratio combine) method. The stronger signal can be added as a larger ratio, but the weaker signal can be added as a smaller ratio. We can distinguish strong signal using SNR estimator. Therefore it is possible to receive an additional pilot signal, and to support more reliable communications by using sequence estimator.
A Study on Designing of LYNX Datalink
Lee, Young-Joong ; Park, Joo-Rae ; Lyu, Si-Chan ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 39~49
LYNX ESM has not only ESM function but Datalink function. The LYNX boarded equipment Interface and Channel coding is needed for LYNX Datalink to support the mother ship with tactical data included threat radar analysis data of LYNX ESM, navigation data, Radar and Sonar of LYNX. The interface of loaded equipments are various protocol like as ARINC419/429, RS232, Synchro, Sync Serial. The Channel coding of Convolution-Scrambler-Interleaver-Bit Stuffing is applied for recovering the transmission data mixed with propagation errors in sea environment.
Prospective Scheme of Network Based Battle Management System in AMD
Kwon, Yong-Soo ; Ham, Byung-Woon ; Kim, Ha-Chul ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 50~60
This work describes a basic concept of network based battle management system in AMD(Air & Missile Defense). The AMD operation inherently is joint concept that each single service do not satisfy the requirements of AMD theater operation. It is integrated system of joint forces that is operated simultaneously. The analysis of the future battlespace and air & missile threat is shown. From this analysis the prospective scheme of network based battle management system in building Korean future AMD is presented.
A Research on the LYNX-ESM System Operating and Performance Prediction Simulation Based on DEVS
Shin, Dong-Cho ; Yun, Ki-Cheonn ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 61~70
This paper is to describe LYNX-ESM Simulation System to simulate for EW operating environment analysis and system performance verification of LYNX-ESM system using Discrete Event Simulation(DEVS) Methodology. This system consists of 3 PC with TCP/IP network. Each PC is loaded with Modeling & Simulation program based DEVS. Each connected program conducts EW simulation. As a result, we analyze the operating environment of the maritime EW threat, simulate the EW threat discrimination and geolocation capability, and estimate the LYNX-ESM system effectiveness before real LYNX-ESM system development.
Effects of Accelerometer Signal Processing Errors on Inertial Navigation Systems
Sung, Chang-Ky ; Lee, Tae-Gyoo ; Lee, Jung-Shin ; Park, Jai-Yong ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 71~80
Strapdown Inertial navigation systems consist of an inertial sensor assembly(ISA), electronic modules to process sensor data, and a navigation computer to calculate attitude, velocity and position. In the ISA, most gryoscopes such as RLGs and FOGs, have digital output, but typical accelerometers use current as an analog output. For a high precision inertial navigation system, sufficient stability and resolution of the accelerometer board converting the analog accelerometer output into digital data needs to be guaranteed. To achieve this precision, the asymmetric error and A/D reset scale error of the accelerometer board must be properly compensated. If the relation between the acceleration error and the errors of boards are exactly known, the compensation and estimation techniques for the errors may be well developed. However, the A/D Reset scale error consists of a pulse-train type term with a period inversely proportional to an input acceleration additional to a proportional term, which makes it difficult to estimate. In this paper, the effects on the acceleration output for auto-pilot situations and the effects of A/D reset scale errors during horizontal alignment are qualitatively analyzed. The result can be applied to the development of the real-time compensation technique for A/D reset scale error and the derivation of the design parameters for accelerometer board.
Identifying Friendly and Foe Using a Watermarking Technique During Military Communication
Lee, Jong-Kwan ; Choi, Hyun-Joo ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 81~89
In this paper, a watermark technique for identifying friendly and foe is proposed during communication. The speech signal is processed in several stages. First, speech signal is partitioned into small time frames and the frames are transformed into frequency domain using DFT(Discrete Frequency Transform). The DFT coefficients are quantized and the watermark signal is embedded into the quantized DFT coefficients. At the destination channel quantization errors of received signal are regarded as the watermark signal. Identification of friendly and foe are done by correlating the detected watermark and the original watermark. As in most other watermark techniques, this method has a trade off between noise robustness and quality. However, this is solved by a partial quantization and a noise level dependent quantization step. Simulation results in the various noisy environments show that the proposed method is reliable for identification between friendly and foe.
Effect of Tracer Composition on Spectrum and Intensity of Burning Flame
Kwon, Soon-Kil ; Hwang, Jun-Sik ; Lee, Sang-Mu ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 90~96
Computer simulation was carried out to develop the tracer composition of a high performance to be able to be observed by not only the naked eye but also the thermal imaging system attached to the weapon system. The results of computer simulation show that the optimum Mg content among the trace compositions is about 40% and the formulation consisted of Viton A has a higher flame temperature compared with that of chloride compound. But the only use of Viton A radiates a yellow light and the composition adding a chloride compound radiates the red light. The light intensity of the tracer composition involving Viton A is higher than that of chloride compound. The tracer composition involving Viton A shows more clear images in case of all tests.
Effect of the East Asian Reference Atmosphere on a Synthetic Infrared Image
Shin, Jong-Jin ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 97~103
A synthetic infrared image can be effectively utilized in various fields such as the recognition and tracking of targets as long as its quality is good enough to reflect the real situations. One way to improve its quality is to use the reference atmosphere which best describes atmospheric properties of regional areas. The east asian reference atmosphere has been developed to represent atmospheric properties of the east asia including Korean peninsula. However, few research has been conducted to examine the effects of this east asian reference atmosphere on the modeling and simulation. In this regard, this paper analyzes the effects of the east asian reference atmosphere on a synthetic infrared image. The research compares the atmospheric transmittance, the surface temperature, and the radiance obtained by using the east asian reference atmosphere with those of the midlatitude reference atmosphere which has been widely applied in the east asia. The results show that the differences of the atmospheric transmittance, the surface temperature, and the radiance between the east asian reference atmosphere and the midlatitude reference atmosphere are significant especially during the daytime. Therefore, it is recommended to apply the east asian reference atmosphere for generating a synthetic infrared image with targets in the east asia.
Aeroelastic Analysis in Frequency Domain for Wings with Double-Folding Mechanism
Kang, Myung-Koo ; Kim, Ki-Un ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 104~113
To identify aeroelastic characteristics of wings with double-folding mechanism, aeroelastic analyses are performed. There are four wing models which consist of one linear model and three nonlinear models. The nonlinear models have one or two freeplay nonlinearties. The describing function method is used to approximately examine nonlinear effects. The aeroelastic module in MSC/NASTRAN is used to study the aeroelastic characteristics of the considered wing models. The effects of the folding mechanism and amplitude ratio are examined. As the amplitude ratio increases, the flutter speeds approach to those of the wing model with only one nonlinearity. The numerical results show that the flutter speeds of the wings with double-folding mechanism can be lower or higher than those of the wing model with only one folding mechanism depending upon the direction of the second folding mechanism.
Three-Dimensional Data Visualization Program Combined with Position Tracking System Using Stereo Cameras
Kim, Byoung-Soo ; Seo, Jin-Won ; Lee, Bong-Ju ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 114~119
Data post-processing programs are used for analysis and visualization of the data obtained from computational fluid methods or flow field experiments. In this paper 3D data visualization system which combines a data visualization program with position tracking system using stereo cameras is introduced. This system offers virtual environment for visualization and analysis of three dimensional data.
An Experimental Study on the Lift and Thrust Generation of a Dragonfly-type Model
Kim, Song-Hak ; Chang, Jo-Won ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 120~127
An experimental study was carried out in order to investigate the effects on the fore- and hind-wings of a dragonfly-type model. A model with two pairs of wing was developed to measure the lift and thrust of a dragonfly-type model. The fore-wing and hind-wing had incidences angle of
. The freestream velocity is 1.6m/sec and the corresponding chord Reynolds number was
. Also, these experiments were carried out with a phase difference of
between the fore- and hind-wing, aerodynamic forces caused by fore-wing only and two pairs of wings were investigated according to the reduced frequency. The results show that the model with fore-wings only generates a thrust component; however, the dragonfly-type model with hind-wings with an incidence angle of
generates a drag component. The total drag is also increased with reduced frequency due to the increased lift of hind-wings.
Effect of Reduced Frequency on the Flow Pattern of Pitch Oscillating Elliptic Airfoil
Lee, Ki-Young ; Chung, Hyong-Seok ; Sohn, Myong-Hwan ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 128~136
The purpose of this paper is to examine the dynamic stall characteristics of an elliptic airfoil when subject to constant pitch motions. In this study, which was motivated by the pressing need for a greater understanding of the reduced frequency
effects on flow patterns of elliptic airfoil, the various reduced frequencies were considered. The result confirms that the reduced frequency has a profound effects on the flow patterns. The increase of
accelerate the separation bubble bursting process up to
, then diminish with further increase in
. Compared with static condition, the dynamic pitching airfoil delays stall angle approximate
during pitch-up stroke for
. Results from this qualitative analysis provided valuable insight Into the control of dynamics stall.
Experimental Investigation for Multi-Element Dual Swirl Coaxial Injector
Shin, Hun-Cheol ; Lee, Seock-Chin ; Park, Hee-Ho ; Kim, Sun-Jin ;
Journal of the Korea Institute of Military Science and Technology, volume 9, issue 4, 2006, Pages 137~144
The basic data obtained in this research for single element performance were directly applied to the design of injector head(7 elements). Designed performance of the 7-element Swirl Coaxial injector was
sea level thrust with 20bar combustion chamber pressure. Numerical analysis were performed to obtain the change of spray pattern for the design of injector head, and we confirmed the feasibility and application of those results. Hot tests were performed for the multi-element injector to compare with the performance of the single element injector and those can be applied to the design of scaled liquid rocket engine. The basic data obtained in this research can be directly applied to the real liquid rocket injector design.