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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 39, Issue 12 - Dec 2011
Volume 39, Issue 11 - Nov 2011
Volume 39, Issue 10 - Oct 2011
Volume 39, Issue 9 - Sep 2011
Volume 39, Issue 8 - Aug 2011
Volume 39, Issue 7 - Jul 2011
Volume 39, Issue 6 - Jun 2011
Volume 39, Issue 5 - May 2011
Volume 39, Issue 4 - Apr 2011
Volume 39, Issue 3 - Mar 2011
Volume 39, Issue 2 - Feb 2011
Volume 39, Issue 1 - Jan 2011
Selecting the target year
Design and Analysis of Wing-Tip and Wing-Body Fairings
Park, Sang-Il ; Kwak, Ein-Keun ; Lee, Seung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 289~296
DOI : 10.5139/JKSAS.2011.39.4.289
In this study, fairing configurations for an aircraft are designed and the aerodynamic analyses of the fairings are performed to find the best choice for the aircraft. Fairings considered are wing-tip fairing and wing-body fairing. Wing alone analyses are done for the wing-tip faring selection, while wing-body-tail analyses are done for the wing-body fairing selection. A 3-D RANS solver with Menter`s
SST turbulence model are used for the aerodynamic analyses. The effects on the drag of the aircraft are examined by comparing the analysis results with and without the farings.
Aeroelastic Analysis of Rotorcraft in Forward Flight Using Dynamic Inflow Model
Lee, Joon-Bae ; Yoo, Seung-Jae ; Jeong, Min-Soo ; Lee, In ; Kim, Deog-Kwan ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 297~305
DOI : 10.5139/JKSAS.2011.39.4.297
In this study, the aeroelastic analysis of rotorcraft in forward flight has been performed using dynamic inflow model to handle unsteady aerodynamics. The quasi-steady airload model based on the blade element method has been coupled with dynamic inflow model developed by Peters and He. The nonlinear steady response to periodic motion is obtained by integrating the full finite element equation in time through a coupled trim procedure with a vehicle trim for stability analysis. The aerodynamic and structural characteristics of dynamic inflow model are validated against other numerical analysis results by comparing induced inflow and blade tip deflections(flap, lag). In order to validate aeroelastic stability of dynamic inflow model, lag damping are also compared with those of linear inflow model.
Damage Tolerance Analysis Using Surrogate Model
Jang, Byung-Wook ; Im, Jae-Hyuk ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 306~313
DOI : 10.5139/JKSAS.2011.39.4.306
The damage tolerance analysis is required to guarantee the structural safety and the reliability for aircraft components. The damage tolerance method, which evaluate the life considering the initial crack, considers a fatigue design model of the aircraft main structure. The fatigue crack growth life should be calculated in damage tolerance analysis and the inspection time to define the replacement cycle. In this paper, the damage tolerance analysis is performed for a turbine wheel which has complex geometry. The equation of the stress intensity factor for complex geometry is hard to know, so that they are usually processed by finite element analysis which takes long time. To solve this problem, the stress intensity factors at specified crack are obtained by the FEA and the crack growth life is evaluated using the surrogate model which is generated by the regression analysis of the FEA data. From the results, the efficiency of the crack growth life calculation and the damage tolerance analysis could be increased by taking the surrogate model.
Sequential Approximate Optimization of Shock Absorption System for Lunar Lander by using Quadratic Polynomial Regression Meta-model
Oh, Min-Hwan ; Cho, Young-Min ; Lee, Hee-Jun ; Cho, Jin-Yeon ; Hwang, Do-Soon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 314~320
DOI : 10.5139/JKSAS.2011.39.4.314
In this work, optimization of two-stage shock absorption system for lunar lander has been carried out. Because of complexity of impact phenomena of shock absorption system, a 1-D constitutive model is proposed to describe the behavior of shock absorption system. Quadratic polynomial regression meta-model is constructed by using a commercial software ABAQUS with the proposed 1-D constitutive model, and sequential approximate optimization of two-stage shock absorption system has been carried out along with the constructed meta-model. Through the optimization, it is verified that landing impact force on lunar lander can be considerably reduced by changing the cell size and foil thickness of honeycomb structure in two-stage shock absorption system.
The Analysis of Creep characteristics for Turbine blade using Theta projection method
Lee, Mu-Hyoung ; Han, Won-Jae ; Jang, Byung-Wook ; Lee, Bok-Won ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 321~331
DOI : 10.5139/JKSAS.2011.39.4.321
The present work is aimed to analyze the creep characteristics of a turbojet engine turbine blade using the theta projection method. The theta projection method has been widely used due to its advantages and flexibility. For the creep characteristic analysis of the turbine blade, tests are performed considering the operating conditions and the non-linear material properties. Results from the creep test are fitted using the four theta model. The predicted proprieties using the four theta model are compared with the prediction model and creep test results. To obtain an optimum value of the four theta parameters in non-linear square method, a number of computing processes in the non-linear least square method were carried out to obtain full creep curves. Results using the theta model has more than 0.95 value of
. The results between the experimental values and predicted four theta model has about 90.0% accuracy. The theta projection method can be utilized for a design purpose to predict the creep behavior.
Stability Analysis of Missiles with Strapdown Seeker
Kim, Tae-Hun ; Park, Bong-Gyun ; Kwon, Hyuck-Hoon ; Kim, Yoon-Hwan ; Tahk, Min-Jea ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 332~340
DOI : 10.5139/JKSAS.2011.39.4.332
A missile with a strapdown seeker should properly estimate line-of-sight(LOS) rate using its attitude information and the look angle of the seeker because LOS rate information in an inertial coordinate system, which is used for a proportional navigation(PN) homing guidance, can not be obtained directly. However, an unnecessary feedback loop(Parasite Loop) is formed in the guidance and control loop, and it may cause the guidance performance degradation or even the unstability of the system(Parasite Effect). This paper presents estimation methods for the LOS rate information and effective ways to minimize the parasite effect using Routh-Hurwitz stability criterion. Various numerical simulations are also included to verify the proposed methods.
Study on Spray Phenomena and Optimal Design of Injector for Improving Small Thruster Performance
Kim, Ki-Ro ; Kim, Su-Kyum ; Byun, Do-Young ; Lee, Se-Min ; Jung, Kang-Su ; Park, Soo-Hyung ; Kim, Sung-Kyun ; Yu, Myoung-Jong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 341~347
DOI : 10.5139/JKSAS.2011.39.4.341
This work studies the performance of an injector for a monopropellant thruster, comparing a conventional and new injector types. The conventional injector consists of 8 nozzles on a convex surface allowing the jet to be diverged. The new injector, we suggested, is an impinging type with nozzle holes on a concave surface. The fuel streams through the nozzle holes are collide at a point on an axial direction, which allow to atomize the liquid streams and to spray more uniformly along circular direction. The performance of the injectors is investigated by using computational fluid dynamics, particle image velocimetry and high speed camera visualization.
Effect of Injector Geometry on Cryogenic Jet Flow
Cho, Seong-Ho ; Park, Gu-Jeong ; Khil, Tae-Ock ; Yoon, Young-Bin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 348~353
DOI : 10.5139/JKSAS.2011.39.4.348
Characteristics of cryogenic single jet flow were investigated. Liquid nitrogen was injected into a high-pressure chamber and formed single jet. Ambient condition around jet was changed from subcritical to superctirical condition of nitrogen. Injector geometries also were changed. A shape of the jet and core diameter were measured by flow visualization technique, and core spreading angle was calculated. Flow instability was found at atmospheric pressure condition. As ambient pressure increased, core spreading angle was increased and maintained after certain pressure.
Defense Strategy against Multiple Anti-Ship Missiles using Anti-Air Missiles
Kim, Do-Wan ; Yun, Joong-Sup ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 354~361
DOI : 10.5139/JKSAS.2011.39.4.354
In this paper, an efficient defense strategy of single naval ship using short range anti-air missiles against the threat of multiple anti-ship missiles is suggested. The defense logic is based on the estimated future trajectory of anti-ship missiles by using current radar information. The logic is designed to maximize the range of interception of anti-ship missiles so that the chance of interception can be increased although the prior tries turn out to be fail. Basically, the decision making for the allocation of a defense missile is achieved by comparing the total kill probability and the estimated intercepting point. Performance of the proposed logic is investigated by nonlinear planar numerical simulations.
Implementation and Flight Test Performance Analysis of vSLAM Aided Integrated Navigation System for Rotary UAV
Yun, Suk-Chang ; Lee, Byoung-Jin ; Yun, Suk-Hwan ; Lee, Young-Jae ; Sung, Sang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 362~369
DOI : 10.5139/JKSAS.2011.39.4.362
In this paper, vSLAM aided integrated navigation system is implemented and performance analysis of the system is completed via flight test. The system can suppress divergence of position error of INS only system by updating vSLAM correction information when temporary GPS signal outage occurs in bad radio condition. In the flight test, integrated hardware containing GPS, IMU and camera is loaded under RC electric helicopter. Performance of the integrated navigation system is verified by comparing estimated position of INS/vSLAM system with that of INS only system.
A study on tracking method and normal point formation algorithm of new mobile SLR system in Korea
Seo, Yoon-Kyung ; Rew, Dong-Young ; Lim, Hyung-Chul ; Kirchner, Georg ; Park, Jong-Uk ; Youn, Cheong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 370~377
DOI : 10.5139/JKSAS.2011.39.4.370
Korea Astronomy and Space Science Institute(KASI) has been developing one mobile SLR system since 2008 named as ARGO-M. Control logic in real-time laser ranging and data processing for normal point from the ranging data are key elements in the operation system of ARGO-M. KASI operation system team performed software logic analysis and related operations for SLR observation with help of Graz SLR station in Austria. This paper describes the algorithm required for SLR operation based on the method in Graz station. We figured out the essential logic for SLR operation and the remedy for the observation quality enhancement through this study.
Temperature and Pressure Measurement on the Flame Deflector during KSLV-I Flight Tests
Jung, Il-Hyung ; Moon, Kyung-Rok ; Kang, Sun-Il ; An, Jae-Chel ; Ra, Seung-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 39, issue 4, 2011, Pages 378~384
DOI : 10.5139/JKSAS.2011.39.4.378
During the flight test of KSLV-I, various sensors are installed in the launch pad and the flame deflector to measure the flame characteristics and their influences on the launch complex when a launch vehicle lifts off. Parameter Measurement System is responsible for acquiring the above flight test data. The measurement methodology such as the configuration of measurement system, sensor locations and data acquisition procedures are presented. And this paper compares and explains the characteristics of data sets measured during two flight tests.