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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
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 28, Issue 7 - Oct 2000
Volume 28, Issue 6 - Sep 2000
Volume 28, Issue 5 - Aug 2000
Volume 28, Issue 4 - Jun 2000
Volume 28, Issue 3 - Apr 2000
Volume 28, Issue 2 - Mar 2000
Volume 28, Issue 1 - Feb 2000
Volume 28, Issue 8 - 00 2000
Selecting the target year
An Improved Method of Body Surface Representation in Shape Design Optimization of Transonic Airfoils and Wings
Sohn, Myong-Hwan ; Lee, Kyu-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 1~1
This paper presents a new method of applying the Bezier parametric curve to the shape optimization of transonic airfoils and wings. first, a semi-analytical algorithm is developed to determine the control points of the Bezier curve which can reproduce the initial shape accurately with a minimum number of control points, and new sets of design variables are proposed to overcome the dependency of the side constraints on the initial geometry. Those sets are tested for several cases of the shape optimization in transonic flow conditions. Second, the body shape generation method and the optimization design program of the transonic airfoils are extended to the 3-dimensional wing design problem. Sweepback, dihedral, and twist angles are used as the design variables in the shape optimization of wing planform. The camberline method developed in the airfoil design is successfully extended to 3-D wing section design.
A Study on the Measurement for the Pitch Dynamic Stability Derivatives of Standard Dynamic Model
Cho, Hwan-Kee ; Baek, Seung-Woock ; Hur, Won-Wooc ; Park, Jae-Hyean ; Chang, Jo-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 11~11
This paper presents the measuring method for dynamic stability derivatives in the pure pitching motion of a standard dynamic model using the free oscillation technique in the low-speed md tunnel. It was released for standard dynamic model to be oscillated without any excitations after initial displacement by the compressed air jet. Angular displacements were measured by the dynamic stability balance, and the data was processed to determine the pitch dynamic stability derivatives using the method of logarithmic decrement. Test results are compared with the one in the literature. It confirms the validity of experimental technique and data reduction procedure and it also shows the reliability for the stability derivatives up to 36 degrees of the angle of attack
Crush Energy Absorbing Characteristics of Composite Square Tubes
Choi, Youn-Ho ; Park, Hoon-Cheol ; Yoon, Kwang-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 17~17
Crush energy characteristics of graphite/epoxy square tubes are experimentally studied. Effect of the ply orientation on the peak load and the average load is investigated by applying compressive load on the top of the composite square tubes under the stroke control with crosshead speed of 0.003mm/sec and 0.3mm/sec. In addition to the experimental survey, the finite element analysis is used to estimate the peak load of the composite square tubes with
. The first buckling mode of the tube is superimposed to the perfect geometry and the distributed compressive load is applied on the top of the tubes. The applied compressive load that makes Tsai-Wu criteria equal to one is regarded as the peak load of the tubes. The experimental data shows that the square tube with
has the highest peak load and the square tube with
has the highest average sustained load. The measured peak loads of the composite tubes with
. approximately agree with the estimated peak load using the finite element analysis.
Spar Structure Optimization of Composite Rotor Blade with Flapping and Lagging Natural Frequency Constraints
Lee, Jong-Chan ; Kwon, Jung-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 27~27
The present paper is concerned with the application of optimization method to find an optimal spanwise distributions of the spar section characteristics of composite rotor blade under flapping and lagging natural frequency constraints. The computation processes of the section properties and natural frequencies for rotating blades using discrete method, were combined with the optimization procedure. The integrated computer program was applied to calculate the preliminary sizing of an advanced hingeless rotor blade. The results of the section charateristics and the natural frequencies were compared with those of the commercial computer codes such as CATLA and CAMRAD, respectively.
Mass Matrix Enhancement by Dispersion Analysis
Cho, Maeng-Hyo ; Yoo, Seung-Woo ; Kim, Ki-Ook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 37~37
A method of dispersion analysis is proposed for the eigenvalue problem in the finite element method. A nonconsistent mass matrix was obtained as a linear combination of the lumped and consistent masses. In the example problems with rod and beam elements, better accuracy can be achieved for the frequency analysis of intermediate and higher ranges. In addition, the approach can provide a reference for the error analysis.
A Study on the Strain Measurement of Laminated Composite Structures Using Fiber Bragg Grating Sensors
Ryu, Chi-Young ; Park, Joong-Wan ; Kang, Hyun-Kyu ; Kim, Dae-Hyun ; Koo, Bon-Yong ; Hong, Chang-Sun ; Kim, Chun-Gon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 44~44
In order to be used for the primary structures, composite structures must ensure structural reliability and durability. It is therfore desirable to carry out real-time health monitoring of composite structures as loading history. In the present study, fiber Bragg grating(FBG) sensors which have the advantage of multiplexing based on wavelength division multiplexing(WDM) technology were used for the sensing part of the smart composite structures. The FBG sensor system was constructed by use of a wavelength-swept fiber laser(WSFL). The strains of the laminated composites under various loading conditions were measured real-timely by bonded and embedded FBG sensors. From the experimental results, it was confirmed that FBG sensors could be effectively used to monitor the internal behavior of the structures with complex geometry which was inaccessible to the other existing sensors.
Crack growth analysis and testing for the plates with the reinforcing panel
Lee, Seok-Soon ; Wi, Yong-Chul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 53~53
The damage tolerance analysis of the aircraft structure is based on the prediction of fatigue crack growth, which requires knowledges of flight load spectrum, da/dN characterization for the material, and stress intensity factor of the specified crack geometries. Thus, The assurance of the structural safety requires the analysis to control crack growth. In this study, The crack growth in a center-holed aluminum plate was tested and simulated with an increment crack extension analysis using the dual boundary element method. Another plates with a reinforcing panel, which was riveted, was tested and simulated with the finite element method. The results of the crack propagation are compared with those of the analysis, The crack growth testing was performed with the fatigue testing machine (Instron 8516).
Orbit Determination of KITSAT-3 satellite Using GPS Navigation Solutions
Yoon, Jae-Cheol ; Chang, Young-Keun ; Choi, Kyu-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 61~61
KITSAT-3 satellite loaded the GPS receiver for the purpose of performance test. GPS navigation solutions, which consist of position and velocity components, are calculated in on-board system and are transferred from KITSAT-3 to ground station by telemetry. In this study, The GPS navigation solutions of KITSAT-3 were compared with the results of TLE/SGP4 orbit propagator which is used in KITSAT-3 tracking system and then the differences between them were analyzed. The KITSAT-3 orbit was determined using GPS navigation solutions as observation data on the base of precise perturbation model. YSODSv2 orbit determination system that had been developed by Center for Astrodynamics in Yonsei university was used for the precise orbit determination. In the process of orbit estimation, the position components of GPS navigation solutions were inputted as observational data and Bayesian least square method was applied. Since KITSAT-3 GPS navigation solutions include the large errors and in particular the error of velocity components is the larger than that of position components, it is improper to utilize them in the tracking system. But in the KITSAT-3 mission, TLE/SGP4 algorithm can be replaced by the orbit determination system using CPS navigation solutions.
Flight Dynamic Characteristics and Recovery Enhancement of Helical Divergence
Ha, Cheol-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 71~71
In this paper the helical divergence characteristics for a specific airplane with relatively small angle of attack and roll rate are analyzed analytically and numerically. Also recovery enhancement from the helical divergence, which is a nonrecoverable flight condition, is studied. From this study, it is told for the associated airplane with low angle of attack and relatively small roll rate that the helical divergence takes place in the process of alternate occurrence of yaw rate and roll rate due to pitching moment, which in him produces steeper flight path angle. In addition, feedback of angle of attack and its rate to the elevator input is more effective to recovery from helical divergence flight.
Ambiguity Resolution Method using Increased Redundant Measurement of L2 (AIM/L2)
Son, Seok-Bo ; Park, Chan-Sik ; Lee, Sang-Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 82~82
In general, the wide lane technique is used for resolving the integer ambiguity when using dual-frequency GPS measurements. The wide lane technique has such advantages as reduced search space and increased probability of resolving the integer ambiguity. It requires, however additional searching procedure in order to mitigate the effect of magnified noise covariance which is inevitable when generating the wide lane measurements. Furthermore, the wide lane technique does not work if L1 and L2 carrier phase measurements are not available simultaneously. This paper proposes a new integer ambiguity resolution method for dual-frequency GPS measurements, which can avoid the above-mentioned problem of the wide lane technique. The proposed method uses L2 carrier phase measurement as a redundancy. It is shown that only three among the integer ambiguities are independent as in the single frequency case. From the experimental results, it can be seen that the proposed method is .un efficient in resolving the integer ambiguity than the wide lane technique.
A Study on Dynamic Modeling of Gas Turbine Engine Using ICV Method
Kong, Chang-Duk ; Kim, Sog-Kyun ; Pilidis, Pericles ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 89~89
Using SIMULINK software, a dynamic model of a gas turbine engine is developed to predict transient behaviour of the gas turbine engine. The SIMULINK model consists of subsystems in order to represent engine components such as compressor, turbine, etc. This model uses the inter-component volume (ICV) method to estimate the rate of pressure changes at various engine stations and to calculate the torque unbalance following the variation of fuel flow rate. In order to validate the SIMULINK model, a modified FORTRAN dynamic model using the continuity of mass flow (CMF) method has been chosen and compared with the. SIMULINK model. As a result, the SIMULINK model can be used to simulate normal operating condition as well as severe conditions such as a fuel cut-off in flight and a starting in windmilling condition. It can be revealed that an effect of altitude on transient behaviour of the gas turbine engine is more serious than that of Mach number. In addition, a fuel schedule for acceleration to idle needs to be adjusted along a variation of altitude and flight Mach number to prevent the engine damage.
Tunnel entry flow analysis of high speed train with wedge shaped nose
Shin, Chang-Hoon ; Park, Warn-Gyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 99~99
The three-dimensional unsteady compressible Navier-Stokes equation solver with sliding multi-block method has been applied to analyze the flow field around the high speed train which is entering into a tunnel. The numerical scheme of AF+ADI was used to efficiently solve Navier-Stokes equations in the curvilinear coordinate system. In order to handle the relative motion of the moving train and the stationary tunnel, the sliding multi-block technique was implemented. From the present study, the generation of compression wave was observed ahead of the train in the form of plane wave and the high pressure in the gap between the train and the tunnel was also found due to the blockage effects. The variation of pressure of tunnel surface and velocity profile of the train are identified as the train enters into a tunnel. The dramatic changes in aerodynamic forces are also discussed.
Conceptional Thermal Design and Numerical Verification of Geosynchronous Communication Satellite
Kim, Taig-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 106~106
Thermal subsystem of geosynchronous communication satellite providing wide band (Ka-band) multi-media services is designed, numerically analyzed, and verified. The satellite configuration and positions of each components and modules are determined under consideration of thermal point of view, such as their operating temperature ranges, heat dissipation, and space environment. The thermal control hardware is designed by means of the trade-off studies and its degradation throughout the mission life considered. To verify the component operating temperature meets the design requirement, the thermal math models are established and numerically analyzed under worst case conditions. The thermal math model provides not only an analytical verification of overall thermal design but inputs to component design, test requirements and other subsystem operational requirements, heater power requirements, and thermal environmental boundaries for detailed thermal models of the subassemblies.
Effects of a Mechanical Flight Control System on the Lateral Stability and Control
Kim, Byoung-Soo ; Lee, Kwang-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 116~116
During design, manufacturing, flight test, and evaluation processes for the KT-1 development, some lessons about flying qualities were learned. When the differences between estimates and flight test results of stability and control were analyzed, flight control system(FCS) parameters(free-play, stiffness, mass balance, friction, etc.) which are not generally considered in design phase were found to play a key role on the differences in reversible flight control system. This paper focuses only on lateral stability and control aspects of the FCS, that is, the effects of FCS mass unbalance on lateral stability and the effects of FCS stiffness and aileron free-play on roll performance. This paper describes how the FCS properties to satisfy the design target were identified from the analysis of the flight test results, and were applied to KT-1 upgraded version to establish the design.
Structural Sizing and Optimization of Aerospace Vehicle Fuselage
Kim, Kwang-Soo ; Lee, Yeong-Moo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 123~123
An efficient software tool was developed for fuselage structural sizing and optimization of aerospace vehicle. The fuselage structural model contains skin, stringer, frame and floor support structure. The program is applicable to fuselage with general geometry such as tapered non-circular cross-section and variable structural size in longitudinal and circumferential directions under combined loading with axial, bending, torsion and internal pressure. The various section type of primary components also incorporated in structural model and the effect on strength calculation and sizing are considered. The primary structures are sized iteratively for minimum weight using each of stress-ratio algorithm and optimization algerian or the both. The strength, buckling and minimum gage constraints are included in the structural sizing. The example problems show that the best selection of cross-section dimension and spacing of structural components can be obtained using the developed program.
The Design and Analysis of KOMPSAT SDM
Kim, Jin-Hee ; Kim, Sung-Hoon ; Rhee, Ju-Hun ; Hwang, Do-Soon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 133~133
The major role of the spacecraft structure is to keep and support the spacecraft safely in all the launch environment, on-orbit condition and ground-transportation period. Before developing the flight model of satellite structure, structural development model and/or protoflight model is generally constructed. The purpose of SDM is to verify the static/dynamic characteristics between finite element model and fllight model in the initial stage of development and identify the major load path of the structure. Using the acquired data, the finite element model for flight model is tuned and structural safety can be verified. In this paper, the design/manufacturing and assembly process of KOMPSAT SDM are described. Also, the comparisons between experiments and finite element analysis for mass properties and natural frequencies are performed.
F-22 Design Evolution (Part II)
Lee, Kyung-Tae ; Lee, Ki-Hak ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 141~141
Status and Future Outlook on Nano-Pico Satellites Development
Bang, Hyo-Choong ; Park, Hoon-Cheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 153~153
The Development and Application of KOMPSAT Series
Ryoo, Jang-Soo ; Kim, Byoung-Kyo ; Paik, Hong-Yul ; Lee, Joo-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 5, 2000, Pages 161~161