Go to the main menu
Skip to content
Go to bottom
REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
Journal of the Korean Society for Aeronautical & Space Sciences
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
Editor in Chief :
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
Dynamic Stall Control via Airfoil Thickness Variation
Joo, Wan-Don ; Yee, Kwan-Jung ; Lee, Bo-Sung ; Lee, Dong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 1~1
A series of numerical experiments are conducted to investigate the effects of control route in the dynamic stall control via active thickness variation, thereby to clarify the dominant 'control parameters for optimal thickness variation route. To achieve these goals, the effects of possible control parameters on the stall angle and maximum lift coefficient are thoroughly observed. The results indicate that dynamic stall characteristics have a dependency on the thickness variation route of down stroke phase as well as on that of upstroke phase. In general, stall angle is more dependent on variation route of upstroke phase, whereas maximum lift coefficient is sensitive to the down stroke thickness variation route. It is also found that the thickness and thickness variation rate are two major parameters in thickness variation concept. On the contrary to thickness, the thickness variation rate has negative effects once the separation occurs.
A Robust Three-Dimensional Navier-Stokes Solver
Lee, Seung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 9~9
A three-dimensional Navier-Stokes solver which can be run on multi-block grid systems has been developed. The code uses the
turbulence model which is known to behave numerically better than the
turbulence model because of the bounded source terms. The
turbulence model equations are solved with the Navier-Stokes equations in strongly coupled manner, which brings robustness to the code. All viscous terms except cross-derivative terms are treated implicitly to increase numerical stability. The turbulent source terms are also treated implicitly. A number of computational results are chosen to validate the accuracy and the robustness of the code. The turbulent flow over a wing-body configuration is also analyzed to show the multi-block capability of the code.
A Numerical Study of the Stagnation Point Heat Transfer Rate Characteristics around the Blunt-Body
Seo, Jung-Il ; Kwon, Chang-Oh ; Song, Dong-Joo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 20~20
In this paper the CSCM upwind flux difference splitting method, Viscous Shock Layer method and Fay-Riddell equation have been applied to study the stagnation point heat transfer rate characteristics of the blunt-body in hypersonic flow regime. A numerical experiments have been performed to construct the database of the thermal protection material design by using Mach numbers, wall temperatures, nose radius and nose bluntness. The differences in predicted heat transfer rate among the methods were approximately 10%. The stagnation point heat transfer rates were linearly proportional to wall temperature, the cubic power of free-stream Mach number and inverse square root of nose radius of curvature. The heat transfer rate characteristics around stagnation point would be useful for hypersonic vehicle design.
A Study on the Performance Analysis of STKKU I
Tak, Jeong-Soo ; Huh, Choul-Jun ; Byun, Yung-Hwan ; Lee, Jae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 28~28
STKKU I, a shock tube at Konkuk university, is enhanced by altering the single diaphragm to double one. Double diaphragm method makes it possible to maintain constant pressure ratio and to acquire the repeatability without respect to bursting nature. By bursting the diaphragm at a specified time, the time of burst can be measured accurately. Hence, the viscous effects in experiment can be shown from the x-t diagram. By comparing with the experiment results, the accuracy of the numerical analysis is validated and it is demonstrated that the properties which can hardly be obtained through the experiment can be estimated.
Aerodynamic Design of a Space Launch Vehicle Using Numerical Optimization and Inverse Method
Lee, Jae-Woo ; Lee, Young-Ki ; Byun, Yung-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 37~37
The inverse method and the numerical optimization technique are developed and implemented for the design of space launch vehicles, which satisfy prescribed heat transfer rate, fineness ratio constraints and show minimum drag characteristics. With the proper specification of the target pressure distribution, the inverse method is successfully applied to the design of a body with considerably less drag than the initial shape. Several gradient approximations, shape functions, and approximate analysis methods are utilized for the design of optimum nose fairing shapes with heat flux, fineness ratio and volume constraints. Several strategies are implemented to the design examples in hypersonic speeds including KSR-III, a Korean three-stage sounding rocket project. The designed bodies have less drag than the initial bodies while maintaining the surface heat transfer rate at the nose. These methods are demonstrated to be efficient design tools for the high speed vehicle design.
Steady Aerodynamic Analysis of WIG Effects for the Wings Moving Near Ground
Han, Cheol-Heui ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 46~46
A numerical method to simulate wing-in-ground(WIG) effects for the wings moving near ground is developed. The aerodynamic analysis scheme for the wings is based on a compressible non-planar lifting surface panel method and the WIG effect was included by images. The numerical simulation is done for the various planform shapes with respect to the parameters such as the aspect ratio, the sweep back angle, the dihedral angle, the angle of attack, and the pound proximity. The present method is validated by comparing the calculated aerodynamic coefficients with exact solutions, other numerical results and measured data, showing good agreements.
Comparison Study of Flutter Analysis for the Wings with Wind Tunnel Test Data
Kim, Dong-Hyun ; Kwon, Hyuk-Jun ; Lee, In ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 53~53
In this study, a comparison study of flutter analysis for the wings with wind tunnel test data has been conducted in the subsonic, transonic and supersonic flow regime. The frequency and time domain analysis method for aeroelastic governing equations are applied to obtain the flutter solution. The Doublet Lattice Method(DLM) in subsonic flow and the Doublet Point Method(DPM) in supersonic flow are used to calculate unsteady aerodynamics in the frequency domain. For all speed range, the time-domain nonlinear unsteady Transonic Small Disturbance code has been incorporated into the coupled-time integration aeroelastic analysis(CTIA) to calculate flutter speeds. Three-types of wings with experimental data have been considered in this paper. MSC/NASTRAN is used for natural free vibration analyses of wing models and calculated flutter velocities and frequencies are compared with the experimental data from wind tunnel tests.
Dynamic Analysis of a Composite Laminated Panel Considering Transverse Matrix Cracks
Park, Jung-Sun ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 64~64
The natural frequencies are investigated for composite laminated panels which contain transverse matrix cracks. The self-consistent methods based on micro-mechanics theory is applied to calculate reduced stiffness from elastic moduli, Poisson's ratio, and crack density of a composite laminated panel. The degraded composite stiffness which has nonlinear relation with the crack density is calculated by an iterative numerical algorithm. In this study, dynamic analysis has been performed to evaluate natural frequency of various composite laminated panels such as cantilevered, tapered cantilevered, two-edge simply supported, two-edge clamped panels. Natural frequency analysis of the composite panels is pursued for various laminated angles and crack density. The numerical results show that the matrix cracks may cause natural frequencies change and should be considered in the dynamic analysis of the composite laminated panels.
Optimal Design of Compressively Loaded Stiffened Composite Panels using Genetic Algorithm
Kang, Ji-Ho ; Kim, Jung-Seok ; Kong, Cheol-Won ; Kim, Chun-Gon ; Hong, Chang-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 72~72
The objective of this study is to obtain the optimal design of stiffened composite panels subjected to uniaxial compression. To accomplish this objective, a finite element analysis program which calculates the critical buckling load by solving an eigenvalue problem was developed. Genetic algorithm was implemented for the optimization method to manipulate the discrete ply angles as the design variables and to utilize its high reliability to find the global optimum. The optimal design of stiffened composite panels with two stiffeners was performed by the genetic algorithm to minimize the weight of the stiffened panel for the given design buckling load limit. The weight of the optimal stiffened composite panels was compared with that of the stiffened quasi-isotropic panels.
Study of Thermal Distortion Behaviors of Solar Array due to Degradation of Composite Materials in LEO Environments
Shin, Kwang-Bok ; Kim, Chun-Gon ; Hong, Chang-Sun ; Lee, Ho-Hyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 82~82
In this study, transient analyses were done for the thermal distortion of orbiting KOMPSAT solar array. MSC/PATRAN was used for solar array modeling, and ABAQUS was used for temperature distribution and thermal distortion analysis. KOMPSAT solar array consists of five honeycomb sandwich panels with aluminum facesheet. Temperature distribution and thermal distortion analysis were performed for the solar arrays with aluminum facesheet and quasi-isotropic composite facesheet. And In order to evaluate thermal distortion behaviors of the solar array with quasi-isotropic composite facesheet due to material degradations induced by the attack of LEO environmental factors such as vacuum, ultraviolet radiation and thermal environments, composite materials were tested in simulated low earth orbit environments. The results shows that the solar arrays with quasi-isotropic composite facesheet are advantageous in view of weight saving, temperature distribution and thermal distortion during mission when compared to those with aluminum facesheet.
An Improved Newton-Raphson Iterative Method based on the Neural Network Prediction
Kim, Jong-Hoon ; Kim, Yong-Hyup ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 93~93
An improved Newton-Raphson iterative method based on the neural network prediction is presented. The key idea of the method lies on the modification of starting point of the conventional Newton-Raphson scheme. The conventional method begins iteration for the current load step from the previously converged point. Instead, in the present method, an approximated converged solution for the current load step is predicted by the neural network and the Newton-Raphson scheme starts iteration at the predicted point. The number of iterations required for convergence decreases because the distance between the starting point and the converged Point is effectively shorter than that in the conventional method. The converged solution of the present method is identical to that of the conventional Newton-Raphson scheme. Multilayer neural network is exploited to predict the converged solution. The training data for learning of the neural network is constructed on the vector plane spanned by the mean and complementary vectors obtained from the previously converged solutions. Numerical test demonstrates that the present method saves about
percent of total CPU time yielding identical converged solution to the conventional Newton-Raphson method.
Load Calculation for Full-Scale Airframe Static Test
Koo, Kyo-Nam ; Kang, Wang-Gu ; Stiouart, Andrei ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 100~100
Methods of load calculation were studied for full-scale airframe static test and implemented into a software with a convenient user interface. The software determines the pad loads and zones for each actuator to apply loads for two or more conditions with no change in whippletree set-up as well as the pad loads for a particular test case. It helps the design of the whippletree system and determines the location and load capacity of hydraulic actuators to be used. Test loads were calculated for the wing load conditions of Twin Bee aircraft. Shear force, bending moment, and torque by the pad loads were verified by comparison with the resultant loads by theoretical loads.
Design of Missile Guidance Law via Variable Structure Control
Moon, Jong-Ki ; Kim, You-Dan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 108~108
New missile guidance law is proposed via variable structure control. The acceleration command is determined considering the target acceleration information as uncertainty. Target and missile are assumed to be point masses moving in the two dimensional plane. According to the property of the missile acceleration command, the proposed guidance laws are classified into IPN type and RTPN type. Moreover, it is shown that the conventional proportional guidance laws can be derived from the proposed guidance law. Numerical simulation results show that the proposed guidance law exhibits better performance compared to the conventional proportional guidance laws.
Mathematical Formulation of Integrated Equations of Motion for Flexible Aircraft (I) : Nonlinear Model
Ro, Kap-Seong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 124~124
The integrated equations of motion of flexible aircraft, which simultaneously describe both flight dynamic and structural dynamic motion, are derived based on the combined use of Newtonian and Energy Approach. Typically, those equations are developed using the energy approach because the complicated motion of an unrestrained elastic body in three dimensional space is easily captured in the form of kinetic and potential energy. However, it is difficult to capture the details that rationalize the final set of equations of motion which are widely used for the dynamic analysis and control system design. On the other hand, combined use of Newtonian and energy approach provides the excellent rationale behind these equations. The complete set of equations of motion, which are kinematically decoupled but kinetically coupled, can be grouped into two sets. These equations are valid only if certain assumptions and constraints are satisfied. The objective of this paper is to delineate necessary assumptions, constraints and limitations of these equations by deriving them via combined use of Newtonian and Energy Approach.
Two Phase Flow and Heat Transfer Characteristics in a Solid Rocket Nozzle
Yu, Man-Sun ; Kim, Wan-Sik ; Cho, Hyung-Hee ; Bae, Joo-Chan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 133~133
Aluminum oxide (
) particles are included in solid rocket propelant. These particles make ablative the rocket motor nozzle and imped the expansion processes of propulsion. This study conducted numerical analysis of two phase flow in the solid rocket nozzle. Stoke number is defined over the various aluminum oxide particle sizes and particle trajectories are treated by Lagrangian approach. Particle stability is considered by definition of Weber number in rocket nozzle. It is certified that the nozzle wall of converge section and nozzle throat might be damaged severely by the particles. Heat transfer and impact phenomenon is studied in the case of that aluminum oxide particles collided with nozzle internal surface. The result of numerical analysis shows that Heat transfer to the nozzle surface by particle energy is greater than that by the mechanical kinetic energy.
Sine Vibration Test of a Large Communication Satellite Using Notching Input
Park, Jeong-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 142~142
This paper presents experimental results of sine vibration test of a large communication satellite using notching input. The objectives of the sine vibration test are to measure the modal parameters of a satellite and its components for the model update of final coupled loads analysis(CLA) and to evaluate structural integrity of secondary structure under the sine vibration environment of a launch vehicle. In the natural frequency lesion of the large satellite, however, the notching input should be considered to avoid inducing unrealistic dynamic loads in the satellite, which is generally ignored in the test of a small satellite. This is accomplished by notching the input levels to restrict critical responses to specified limit levels. This paper also presents a method of determinating the notching input to test most components to their original target levels.
On the Static Test of Aileron Control System for a Basic Trainer
Jun, Chan-Won ; Park, Keum-Yong ; Kang, Q-Seap ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 150~150
This report was based on the aileron static test results for the KTX-1 #05 aircraft. The test was performed for the same aircraft parts which is used in the real aircraft. The limit loads were applied up to the design and ultimate load. In the case of simultaneously engaging front and rear control stick, the dual factor was considered. MIL-A-8865(USAF) was used for the requirements of the test load and test results met the requirement of the aileron system.
Analysis on Safety of Solar Panel for Science Satellite-I subjected to Impact of Pyrotechnic Separation Device
Chung, Soon-Wan ; Kim, Seung-Jo ; Jang, Young-Soon ; Lee, Sang-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 3, 2000, Pages 156~156
The safety subjected to the impact of the pyrotechnic separation device is analyzed in the solar panel for the first model of Science Satellite-I using ALGOR which is the commercial finite element program. To obtain the result similar to the experimental data, the panel, hinge and solar panel holding bracket are modeled and the applied forces are determined by analytic method and trial-and-error technique. The shear stress is compared with the shear strength of the adhesive to make sure of the safety of the solar cell, and changes of analysis results are compared as the finite element modelings are modified.