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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 37, Issue 12 - Dec 2009
Volume 37, Issue 11 - Nov 2009
Volume 37, Issue 10 - Oct 2009
Volume 37, Issue 9 - Sep 2009
Volume 37, Issue 8 - Aug 2009
Volume 37, Issue 7 - Jul 2009
Volume 37, Issue 6 - Jun 2009
Volume 37, Issue 5 - May 2009
Volume 37, Issue 4 - Apr 2009
Volume 37, Issue 3 - Mar 2009
Volume 37, Issue 2 - Feb 2009
Volume 37, Issue 1 - Jan 2009
Selecting the target year
Improvement of the flow around airfoil/flat-plate junctures by optimization of the leading-edge fence
Cho, Jong-Jae ; Kim, Kui-Soon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 829~836
DOI : 10.5139/JKSAS.2009.37.9.829
3-Dimensional flow which is represented by horseshoe vortex is generated as a type of secondary flow about the main flow. As well, it causes the flow loss. The present study deals with the leading edge fence shape on a wing-body junction to decrease a horseshoe vortex, one of the main factors to generate the secondary flow losses. The shape of leading-edge fence was optimized with the design variables of the installed height, length, width, and thickness of the fence as the design variables. Approximate optimization design method is used as the optimization. The study was investigated using
. Total pressure coefficient of the optimized design case was decreased about 7.5 % compare to the baseline case.
Dynamic Modeling of a Satellite with Solar Array Flexible Modes
Kim, Dae-Kwan ; Park, Young-Woong ; Park, Keun-Joo ; Yang, Koon-Ho ; Yong, Ki-Lyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 837~842
DOI : 10.5139/JKSAS.2009.37.9.837
The efficient dynamic modeling of a satellite with flexible solar arrays is established by using the component mode synthesis technique. A flexible satellite model can be defined as the assembly of two sub-structures, central body and solar array. The reduced models of each substructure, which are expressed in each local frame, are coupled with respect to the satellite reference frame. The dynamic modeling method is applied to the numerical example of a satellite with a single solar array, and is verified by investigating the transfer function results with considering the solar array rotation.
Optimal Earth-Moon Trajectory Design using Constant and Variable Low Thrust
Song, Young-Joo ; Park, Sang-Young ; Choi, Kyu-Hong ; Sim, Eun-Sup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 843~854
DOI : 10.5139/JKSAS.2009.37.9.843
For preparing Korean lunar missions, optimal Earth-Moon transfer trajectory is designed using continuous low thrust. Using both constant and variable low thrusting method, "End-to-End" mission analysis is made from beginning of the Earth departure to the final lunar arrival. Spacecraft`s equations of motion is expressed using N-body dynamics including the gravitational effects due to the Earth, Moon, Sun and also with Earth`s
effects. Planets` exact locations are computed accurately with JPL`s DE405 ephemeris. As a results, optimal thrust steering angle`s characteristics are discovered which showed almost tangential direction burns at the near of central planets. Also, it is confirmed that variable low thrusting method is more efficient than constant thrusting method, and can save about 5% of fuel consumption. Presented algorithm and various results will give numerous insights into the future Korea`s Lunar missions using low thrust engines. Also, it is expected to be used as a basis of more detailed mission analyzing tool.
Development of Galileo E5 Signal Receiving Software for AltBoc Signal Modulation
Jeon, Sang-Hoon ; So, Hyoung-Min ; Lee, Taik-Jin ; Kim, Ghang-Ho ; Jeon, Seung-Il ; Kim, Chong-Won ; Kee, Chang-Don ; Lee, Sang-Uk ; Kim, Jae-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 855~862
DOI : 10.5139/JKSAS.2009.37.9.855
This paper contains the signal receiving algorithm for Galileo E5 AltBOC signal and the development of Galileo E5 signal receiving software. The software runs the process from signal acquisition to extracting measurement data to get navigation solution. It uses logged IF data file as an input. In signal acquisition stage, 1ms and delayed 1ms data are used for reducing correlation ross from secondary code and navigation bit conversion. Signal tracking stage is made of two stages which are coarse tracking and fine tracking. It is for taking advantage of AltBOC characteristic and resolving ambiguity problem due to BOC modulation. The functions of software are verified by signal processing using logged IF data from commercial GNSS simulator.
Unsteady Three-Dimensional Analysis of Transverse Fuel Injection into a Supersonic Crossflow using Detached Eddy Simulation Part I : Non-Reacting Flowfield
Won, Su-Hee ; Jeung, In-Seuck ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 863~878
DOI : 10.5139/JKSAS.2009.37.9.863
Unsteady three-dimensional flowfield generated by transverse fuel injection into a supersonic mainstream is simulated with a DES turbulence model. Comparisons are made with experimental results in terms of the temporal eddy position and eddy formation frequency. The vorticity field around the jet exit is also analyzed to understand the formation mechanism of the large eddy structures. Results indicate that the DES model correctly predicts the convection characteristics of the large scale eddies. However, it is also observed that the numerical results slightly over-predict the eddy formation frequency. The large eddy structures are generated as the counter-rotating vortices are detached alternately in the upstream recirculation region.
Unsteady Three-Dimensional Analysis of Transverse Fuel Injection into a Supersonic Crossflow using Detached Eddy Simulation Part II : Reacting Flowfield
Won, Su-Hee ; Jeung, In-Seuck ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 879~888
DOI : 10.5139/JKSAS.2009.37.9.879
Unsteady three-dimensional reacting flowfield generated by transverse hydrogen injection into a supersonic mainstream is numerically investigated using DES and finite-rate chemistry model. Comparisons are made with experimental results to investigate the turbulent reacting flow physics. The numerical OH distribution describes well the experimental OH-PLIF result, while the numerical ignition delay time shows some disparity due to the restricted available experimental data. The intermittency phenomena are identified by the comparative analysis between RANS and DES. Those effects are also quantified by the temperature distributions along streamlines and superimposed OH mass fraction along with time.
Performance Characteristics of a Partially Admitted Small Mixed-Type Turbine
Cho, Chong-Hyun ; Kim, Chae-Sil ; Paeng, Jin-Gi ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 889~898
DOI : 10.5139/JKSAS.2009.37.9.889
A mixed-type turbine was adopted and the rotor outer diameter was 108 mm. Turbine rotors were designed to the axial-type blade because the turbine operated at a low partial admission rate of 1.7-2.0% with two stages. Performance characteristics were studied when the spouting from the nozzle was toward radially inward or outward direction. Additionally, the effect at each stage of the rotor was measured. For comparing with each turbine performance, properties were measured based on various rotational speeds. Measured net specific torque was used to compare with the turbine system performance. On the mixed-type turbine, better performance was obtained when the operating air spouted toward radially inward direction. The specific torque was increased by 7.8% from using the second stage although its effect depended on the rotational speed.
Design and Experimental Verification of Two Dimensional Asymmetric Supersonic Nozzle
Kim, Chae-Hyoung ; Sung, Kun-Min ; Jeung, In-Seuck ; Choi, Byoung-Il ; Kouchi, Toshinori ; Masuya, Goro ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 899~905
DOI : 10.5139/JKSAS.2009.37.9.899
Most supersonic-flow test facility has axisymmetric nozzles or two-dimensional symmetric nozzles. Compared to these nozzles, a two-dimensional asymmetric nozzle has advantages of reducing low cost for various Mach number testing and undesirable flow structure such as shock wave reflection because the nozzle part can be directly connected to the test section part in this type of nozzle. The two-dimensional asymmetric nozzle, which was Mach number 2, was designed for supersonic combustion experiment. And it was verified with the numerical analysis and visualization of Mach wave. This study suggested the practical method for design and verification of supersonic two dimensional asymmetric nozzles.
Study on Small Thruster Plume using Preconditioned Continuum Scheme and DSMC Method in Vaccum Area
Lee, Kyun-Ho ; Lee, Sung-Nam ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 906~915
DOI : 10.5139/JKSAS.2009.37.9.906
To study the plume effects in the vacuum area, the Direct Simulation Monte Carlo(DSMC) method is usually adopted because the plume field usually contains the entire range of flow regime from the near-continuum in the vicinity of nozzle exit through transitional state to free molecular at far field region from the nozzle. The objective of this study is to investigate the behaviors of a small monopropellant thruster plume in the vacuum area numerically using DSMC method. To deduce accurate results efficiently, the preconditioned scheme is introduced to calculate continuum flow fields inside thruster to predict nozzle exit properties used for inlet conditions of DSMC method. By combining these two methods, the vacuum flow characteristics of plume such as strong nonequilibrium near nozzle exit, large back flow area, etc, can be investigated.
The Correlation of Satellite Thermal Mathematical Model using Results of Thermal Vacuum Test on Structure-Thermal Model
Lee, Jang-Joon ; Kim, Hui-Kyung ; Hyun, Bum-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 916~922
DOI : 10.5139/JKSAS.2009.37.9.916
Because thermal design of satellite carrying out mission in space is performed by thermal analysis result using thermal mathematical model, accuracy of thermal mathematical model is important and it can be improved by model correlation. Correlation steps of satellite thermal math model are composed of modeling of satellite configuration placed in thermal vacuum chamber, verification of correspondence between thermal math model and real satellite configuration, and adjustment of modeling parameters from major part to minor part etc. In this study, correlation success criteria was established and correlation for satellite thermal math model was performed using result of thermal vacuum test of satellite structure-thermal model to meet the success criteria. The overall results satisfied the criteria and this correlated thermal model was applied for detailed thermal design of satellite.
Development of Satellite Conceptual Design Software
Park, Woo-Sung ; Yun, Joong-Sup ; Ryoo, Chang-Kyung ; Choi, Kee-Young ; Kim, Hee-Seob ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 923~930
DOI : 10.5139/JKSAS.2009.37.9.923
In this paper, we introduce a satellite conceptual design software which can be used for outlining a new satellite as well as for educational purpose. This software consists of three commercial tools: MATLAB, STK(Satellite Tool Kit), and Excel. The management of the design software is done by MATLAB which provides basic calculations, GUI(Graphical User Interface), Excel data base management, and STK control. STK, an orbital simulation software developed by AGI, takes a part of obtaining accurate orbital information of a satellite. Excel, a product of Microsoft, is used for the data base of previous satellites and for the saving place of temporary and final results of the software. The conceptual design of a satellite is to roughly estimate power system and mass. In the power system design, the sizes of solar array and battery are determined. Based on the database of existing satellites, we can estimate the subsystems`s mass fraction of a target satellite. Design examples for Kompsat 1 and 2 are suggested for verification of the developed software.
Comparison Study on Take-Off and Landing Flight Test Using Ground Observation and DGPS Method
Lee, Sang-Jong ; Chang, Jae-Won ; Jeon, Byoung-Ho ; Seong, Kiej-Jeong ; Yeom, Chan-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 931~938
DOI : 10.5139/JKSAS.2009.37.9.931
The flight test is last means of compliance to satisfy airworthiness standards and important to evaluate the performance and safety of the developed aircraft. The flight test technologies are obtained from great numbers of experiences and know-hows and protected. In addition, flight test should be conducted efficiently since its various test conditions and items. Therefore, it is requisite to secure efficient flight test methods. This paper discusses the flight test methods for take-off and landing performance and two kinds of techniques are proposed. By performing real flight tests, they are compared with each other and analyzed through the flight analysis.
Formability Evaluation of a Copper Alloy for Regenerative Cooling Thrust Chamber
Ryu, Chul-Sung ; Lee, Keum-Oh ; Choi, Hwan-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 9, 2009, Pages 939~945
DOI : 10.5139/JKSAS.2009.37.9.939
The dome stretching tests and tension tests have been performed to obtain a forming limit curve(FLC) for the copper alloy which is used for manufacturing the regenerative cooling thrust chamber. For experimental investigation of the forming limit curve, we have used in-plane tension specimen to obtain tension-compression strain state as well as out-of-plane specimen to obtain tension-tension strain state through dome stretching test. All specimens were divided into longitudinal and transverse directions according to the orientation of test specimen. The test results showed that in the tension-tension region, copper alloy revealed a maximum major strain of 62.3% and a maximum minor strain of 58.6%. In the tension-compression region, the maximum major strain and the maximum minor strain were measured to be 60.5% and 25.8%, respectively.