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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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Journal of the Korean Society for Aeronautical & Space Sciences
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Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 43, Issue 12 - Dec 2015
Volume 43, Issue 11 - Nov 2015
Volume 43, Issue 10 - Oct 2015
Volume 43, Issue 9 - Sep 2015
Volume 43, Issue 8 - Aug 2015
Volume 43, Issue 7 - Jul 2015
Volume 43, Issue 6 - Jun 2015
Volume 43, Issue 5 - May 2015
Volume 43, Issue 4 - Apr 2015
Volume 43, Issue 3 - Mar 2015
Volume 43, Issue 2 - Feb 2015
Volume 43, Issue 1 - Jan 2015
Selecting the target year
Aerodynamic Design of a Canard Controlled 2D Course Correction Fuze for Smart Munition
Park, Ji-Hwan ; Bae, Ju-Hyeon ; Song, Min-Sup ; Myong, Rho-Shin ; Cho, Tae-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 187~194
DOI : 10.5139/JKSAS.2015.43.3.187
Course correction munition is a smart projectile which improves its accuracy by the control mechanism equipped in the fuze section with canard. In this paper, various aerodynamic configurations of the fuze section were analysed by utilizing a semi-empirical method and a CFD method. A final canard configuration showing the least drag was then determined. During the CFD simulation, it was found that the k-
SST turbulence model combined with O-type grid base is suitable for the prediction of the base drag. Finally, the aerodynamic characteristics of the smart munition and the change of drag due to the canard installation were analysed.
Dynamic Response of Triangular Solar Sail with Wrinkles
Bae, Hongsu ; Woo, Kyeongsik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 195~203
DOI : 10.5139/JKSAS.2015.43.3.195
In this paper, the dynamic behavior of wrinkled triangular solar sail was studied by finite element analysis. The analysis was proceeded first by performing static wrinkle analysis under tensile corner load on sail membrane, and then performing modal analysis. The membrane element method with wrinkle algorithm and the shell element post-buckling analysis method were used to account for the wrinkle deformation and the results were compared for analysis methods throughly. The comparison was also made to that without wrinkle consideration to investigate the effect of wrinkle deformation on the results. Cases with various loading cable angles were analyzed and the results were systematically examined.
Investigation of the Effects of UAV Nozzle Configurations on Aircraft Lock-on Range
Kim, Min-Jun ; Kang, Dong-Woo ; Myong, Rho-Shin ; Kim, Won-Cheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 204~212
DOI : 10.5139/JKSAS.2015.43.3.204
The infrared lock-on range of target aircraft plays a critical role in determining the aircraft survivability. In this investigation, the effects of various UAV engine nozzle configurations on the aircraft lock-on range were theoretically analyzed. A virtual subsonic aircraft was proposed first, based on the mission requirement and the engine performance analysis, and convergent-type nozzles were then designed. After determining thermal flow field and nozzle surface temperature distribution with the CFD code, an additional analysis was conducted to predict the IR signature. Also, atmospheric transmissivity for various latitude and seasons was calculated, using the LOWTRAN code. Finally, the lock-on and lethal envelopes were calculated for different nozzle configurations, assuming the sensor threshold of the given IR guided missile. It was shown that the maximum 55.3% reduction in lock-on range is possible for deformed nozzles with the high aspect ratio.
A Study on Establishment of the Helicopter Initial Design Model Using the Modified Weight Estimation Equations
Kim, Seung Bum ; Choi, Jong Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 213~223
DOI : 10.5139/JKSAS.2015.43.3.213
The helicopter initial design model was established by using the latest weight estimation equations based on the Tishchenko`s methodology through the study existing initial design tools. The sequential decomposition method is used to reduce analysis time in the sizing. Empirical parameters of the weight estimation equation were also extracted from numerical and regression analysis for a helicopter database. Design input and output values were compared with the RISPECT design tool. Finally, comparison of the re-design resulting for several existing helicopters was presented and showed the good agreement within less than 5% in the weight estimation and main rotor sizing. Established initial design model was proved to be effectively used as initial design tool.
An Experiment Study on Sideslip Angle Effect of Lambda Wing Configuration
Shim, HoJoon ; Park, Seung-O ; Oh, Se-Yoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 224~231
DOI : 10.5139/JKSAS.2015.43.3.224
An experimental study on aerodynamic coefficients of a lambda wing configuration was performed at the low speed wind tunnel of Agency for Defense Development. The main purpose of this study was to investigate the effects of sideslip angle on various aerodynamic coefficients. In the case of
sideslip angle, nose-up pitching moment rapidly increases at a specific angle of attack. This unstable pitching moment characteristic is referred to as pitch break or pitch up. As the sideslip angle increases, the pitch break is found to be generated at a higher angle of attack. Rolling moment is found to show similar behavior pattern to `pitch break` style with angle of attack at non-zero sideslip angles. This trend gets severer at greater sideslip angles. Yawing moment also shows substantial variation of the slope and the unstable directional stability with sideslip angles at higher angles of attack. These characteristics of the three moments clearly implies the difficulty of the flight control which requires efficient control augmentation system.
Estimation of Longitudinal Dynamic Stability Derivatives for a Tailless Aircraft Using Dynamic Mesh Method
Chung, Hyoung-Seog ; Yang, Kwang-Jin ; Kwon, Ky-Beom ; Lee, Ho-Keun ; Kim, Sun-Tae ; Lee, Myung-Sup ; Reu, Taekyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 232~242
DOI : 10.5139/JKSAS.2015.43.3.232
For stealth performance consideration, many UAV designs are adopting tailless lambda-shaped configurations which are likely to have unsteady dynamic characteristics. In order to control such UAVs through automatic flight control system, more accurate estimation of dynamic stability derivatives becomes essential. In this paper, dynamic stability derivatives of a tailless lambda-shaped UAV are estimated through numerically simulated forced oscillation method incorporating dynamic mesh technique. First, the methodology is validated by benchmarking the CFD results against previously published experimental results of the Standard Dynamics Model(SDM). The dependency of initial angle of attack, oscillation frequency and oscillation magnitude on the dynamic stability derivatives of a tailless UAV configuration is then studied. The results show reasonable agreements with experimental reference data and prove the validity and efficiency of the concept of using CFD to estimate the dynamic derivatives.
Sub-Orbital Hypersonic Flight Test Programs using Sounding Rockets and Small Launch Vehicles
Kim, Hye-Sung ; Yang, Won-Seok ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 243~256
DOI : 10.5139/JKSAS.2015.43.3.243
As a part of the R&D efforts for the hypersonic vehicles, various flight test programs has been carried out using small launch vehicles or sounding rockets. Australian HyShot program is a representative case of the flight test program for scramjet engines carried by international collaborations. A number of hypersonic flight test programs has followed in a similar way. In USA, Falcon HTV-2 was carried by DARPA, X-51A by AFRL and HyFly by ONR. HyCAUSE and HIFiRE were carried in collaboration with Australia. In France, LEA program is on the way similarly to X-51A. Russia, China and India seems like carrying out flight test programs for the development of hypersonic defense system. The goals, technical elements, the status and the relation between the programs were summarized in this paper as a reference for the similar program of the country in the future.
Design and Analysis of Structure for SpaceEye-1
Jeon, Jae-Sung ; Jeong, Sumin ; Choi, Woong ; Kang, Myungseok ; Jeong, Yunhwang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 257~264
DOI : 10.5139/JKSAS.2015.43.3.257
The structure of SpaceEye-1 developed by Satrec Initiative is designed to carry out various earth observation missions in harsh launch and orbit environments. This paper describes methodology of the structure design and analysis performed during the SpaceEye-1 development. The SpaceEye-1 structure is designed not only to endure the static/dynamic loads but also to protect a main payload and all other components under the launch environments. The structural design requirements were derived from the requirements of the launch vehicle, payload, and other subsystems from the initial development phase. Three-dimensional modeling process was used to verify geometric compatibility of the structure with the other subsystems, and finite element analysis was used to confirm whether the designed structure satisfied all the mechanical requirements derived from the launch vehicle and payload.
Optical Design for Satellite Camera with Online Optical Compensation Movements
Jo, Jeong-Bin ; Hwang, Jai-Hyuk ; Bae, Jae-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 265~271
DOI : 10.5139/JKSAS.2015.43.3.265
In this study, optical design for small satellite camera equipped with online optical compensation movements has been conducted. Satellite camera equipped with compensation movements at M2 mirror and focal plane can guarantee the MTF performance through the focal plane image stabilization and the on-orbit optical alignment. The designed optical system is schmidt-cassegrain type that has M1 mirror of a diameter 200mm, GSD 3.8m at an altitude of 700km, and 50 % MTF performance. The performance of the designed optical system has been analyzed through the method of ray aberration curve, spot diagram, and MTF. It has been found by the optical performance analysis that the designed optical system satisfies the optical requirements of satellite camera equipped with online optical compensation movements.
Recent Status on Miniature Smart-bullet Techniques
Lee, Seongheon ; Cho, Hanjin ; Cho, Youngki ; Bang, Hyochoong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 272~281
DOI : 10.5139/JKSAS.2015.43.3.272
Miniature smart-bullet is a human-carrying guided missile designed to hit a target easily while having a miniature size. Contrary to the normal missiles, miniature smart-bullet is highly expected to enhance the military strength and survival rate of troops by its compact size readily carriable to a single soldier. In this paper, previously developed techniques, activities and patents of miniature smart-bullet, particularly its structural shape and actuators are surveyed. Furthermore, analysis of required techniques to develop a miniature smart-bullet are also discussed for upcoming conceptual design.
Experimental Validation of Multiple UAVs with Vector Field Guidance for SEAD(Suppression of Enemy Air Defense)
Jung, Wooyoung ; Kim, Ki-Duck ; Lee, Seongheon ; Bang, Hyochoong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 3, 2015, Pages 282~287
DOI : 10.5139/JKSAS.2015.43.3.282
In modern warfare, the importance of SEAD(Suppression of Enemy Air Defense) mission is being emphasized. However, this mission runs the risk of hull damage or casualties of our friendly air forces. Because of these risks, research on the way of minimizing damages and enhancing mission capability is under active discussion. As a part of this research, SEAD mission planning with multiple UAVs has been covered using vector field guidance. This guidance method not only applies to various forms of flight path but also requires less computational power than other guidance methods. Therefore, in this paper, planning methods of SEAD mission for multiple UAVs using vector field guidance and experimental data from flight experiments regarding designed mission has been covered.