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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 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
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Parallelized Aerodynamic Design Optimization of 3-dimensional Wing
Sung, Chun-Ho ; Kwon, Jang-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 1~1
An efficient aerodynamic design optimization method for 3-dimensional wing is developed. A gradients-based optimization is adopted to find optimum, and adjoint equations are used for sensitivity calculations. The computational efficiency is improved by using a tightly coupled approach with step size estimation, multigrid DADI flow analysis and parallel computing. To show the efficiency of present method, a drag minimization problem of ONERA M6 wing under transonic flow conditions is presented.
Numerical study on swirling turbulent flows with primary and secondary dilution flows in a can type of gas turbine combustor
Lee, Seong-Hyuk ; Ryou, Hong-Sun ; Chae, Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 9~9
We simulated the three-dimensional swirling turbulent flows with primary and secondary dilution flows in a simplified CAN type of gas turbine combustor. The main objective is to investigate the characteristics of swirling turbulent flows with dilution flows and give better understanding of turbulent flows. The governing equations were discretized on Finite Volume Method, and solved with SIMPLE algorithm to couple the velocity field with pressure field. The Reynolds-Stress-Model was used to effectively predict anisotropy of turbulent flows in a primary zone. The results showed that the anisotropy exists in the primary zone due to swirl velocity and injected air from primary injector, and then gradually decays due to turbulent mixing and consequently near-isotropy occurs in the region between primary and dilution zones. The results were generally in good agreements with experimental data.
Analysis of Unsteady Viscous Flows Past Pitching Airfoils on Unstructured Meshes
Oh, U-Seop ; Kim, Ju-Seong ; Gwon, O-Jun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 17~17
A 2-D Navier-Stokes flow solver is developed for the simulation of unsteady, high Reynolds number flows on unstructured meshes. The solver is based on a cell-centered finite-volume method with Roe's flux-difference splitting. In order to relieve the numerical inaccuracy in evaluating the fluxes on hi씽Y-stretched, high-aspect ratio triangular cells, a hybrid mesh is used. The Spalart-Allmaras and
turbulence models are employed in order to model the effect of the fluid turbulence in the mean flow equations. The governing equations and the turbulence model are integrated in time using an implicit time-marching method. The point Gauss-Seidel relaxation and a dual-time stepping method have been incorporated. The numerical method is applied to a low angle-of-attack oscillatory airfoil motion and ramp motions. The results are compared with experimental data for validations.
Calculation of Inviscid Flows over an Oscillating 3-D Wing Using an Unstructured Implicit Parallel Solver
Park, Yeong-Min ; Gwon, O-Jun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 27~27
Three-dimensional computations are performed for steady and unsteady transonic flows over a F-5 wing using a parallel implicit solver. The numerical scheme is based on a cell-centered finite-volume method with implicit Gauss-Seidel time integration and Roe's flux-difference splitting. For parallel computation, local sub-domains are decomposed using MeTiS library Considering the balance of the number of cells. Parallel implementation is made using MPI library. Steady computation of a F-5 wing is performed to validate the capability of Parallel computation. A case of an oscillating F-5 wing is also compared with experimental data for the validation of time accurate computations.
Analysis of Rarefied and MEMS Gas Flows Using Thermodynamically Consistent Nonequilibrium Hydrodynamic Models
Myong, Rho-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 35~35
Considerable parts of gas flows arising in aerospace vehicles, rocket nozzles, MEMS channels, and thin film growth process are characterized by high thermal nonequilibrium, so that new equations beyond the continuum Navier-Stokes equations are necessary, Owing to the low-density and small scale of the characteristic length, the flowfields belong to various flow regimes; continuum, slip, transitional, and free-molecular. Many computational methods--either fully kinetic (DSMC) or fluid dynamic (moment equations)--have been proposed, but it turned out that some have difficulty in solving low-speed MEMS flows and others fail to satisfy the second law of thermodynamics. Towards solving this dilemma, an innovative nonequilibrium hydrodynamic computational model is studied that can cover almost all flow regimes in real geometry. Through a critical review of the previous models, the advantages of the new model are identified. finally, to check its validity, it is applied to some acid test problems; shock structure and internal flow in MEMS channel.
Transonic/Supersonic Load-Distribution Analaysis of a Composite Wing
Kim, Dong-Hyun ; Lee, Gi-Su ; Lee, In ; Kwon, Oh-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 48~48
In this study, the load distribution analysis of a composite wing has been studied in the transonic and supersonic flow regime. The effects of fiber orientation on the deformation pattern and the aerodynamic coefficients have been also investigated. finite element method and computational fluid dynamics using transonic small disturbance equation have been applied for the present coupled aeroelastic analysis. The static aeroelastic analysis of isotropic and composite aircraft wing with two different airfoil shapes have been conducted to consider the nonlinear shock waves in the transonic and supersonic flow regime. The deformation shape and aerodynamic coefficient of a composite wing have been compared for the various laminate angle sets. Analyses conditions have been set up to give the useful data which can be compared with the results of wind tunnel test in the future.
A Study on the Development of Fiber Bragg Grating Sensor System for the Strain Monitoring of Smart Structures
Ryu, Chi-Young ; Koo, Bon-Yong ; Hong, Chang-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 58~58
Fiber Bragg grating(FBG) sensors based on the wavelength division multiplexing(WDM) technology are ideally suitable for structural health monitoring. Proper monitoring of measurands in FBG sensor systems requires accurate measurement of the Bragg center wavelength. Thus we constructed a FBG. sensor system by use of a wavelength-swept fiber laser(WSFL) in the present study. The Fabry-Perot filter, an element of WSFL, may have an intrinsic nonlinearity, so the compensation method of the nonlinearity was developed. In addition a real-time signal processing program was made to measure strains. The quasi-static and dynamic strains were measured by the constructed FBG sensor system for investigation of the system performance. Experiments showed that the constructed FBG sensor system and the real-time signal processing program could successfully measure the strains of structures.
Robust Flight Control Law Parametric Optimization of Aircraft with Stability and Controllability Augmentation System
Yoo, Chang-Sun ; Kim, Jong-Chul ; Tunik, A.A. ; Bograd, V.M. ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 67~67
Parameter optimization of Flight Control Law(FCL), based on
control theory, is very important problem in the area of aviation maintenance technology as well as in the flight control systems manufacturing. In more realistic situation it is necessary to be aware that real flight Control System(FCS) contains subsystems Which are used in manual as Well as in automatic modes. These include diverse Stability and Controllability Augmentation System(SCAS) whose structure mostly depends on the flight characteristics of given aircraft and requirements to its piloting. These used to make up Primary flight Control Systems(PFCS). In this case the application of optimization technique based on the modem methods of optimal control synthesis is essentially restricted. This paper is devoted to the solution of FCL parametric optimization problem on the basis of combination of requirements to SCAS in manual modes as well as methods to finding FCL parameters in automatic modes
Analysis of Estimation Characteristics According to Target Maneuvering Patterns
Choi, Jae-Weon ; Fang, Tae-Hyun ; Hong, Keum-Shik ; Choi, Sung-Lin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 76~76
In this paper, three kinds of maneuvering patterns (Waver, Pop-Up, and High-Diver maneuvers) are basically considered for a target motion to evaluate the estimation characteristics of the tracking filters according to the maneuvering patterns. The employed tracking filters we Interacting Multiple Model (IMM) filler, which is known as the most cost-effective estimation scheme, and other filters are stemmed from it. The simulation results show the estimation characteristics of the employed filters according to the given maneuvering patterns of a target.
Dynamic-Window Search for Real-time Simulation of Dynamic Systems
Yoon, Sug-Joon ; Kang, Hyun-Joo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 86~86
Various parameter values are provided in the form of tables, where data keys are ordered and unevenly spaced in general, for real-time simulation of system components or dynamics of vehicles such as airplanes, automobiles, ships, and so on. The main purpose of this study is to find or develop the most efficient searching method under constraint of real-time simulation, especially hardware-in-the-loop simulation. If a parameter value has certain dynamics because of its relation with the state variables of the simulated system, the integration algorithm and the step size, a searching region at a given time frame can be reduced dramatically from the entire data table taking advantage of the information The size of the reduced searching region, named dynamic-searching window, varies and the window moves by its own dynamics as simulation time runs. Numerous numerical tests yielded the conclusion that the searching speeds of conventional searches became substantially faster when combined with the dynamic-window search. The effect is enormous for interpolation searches, which locate searching parameter values in 1 probe for data tables with linear data distribution, because reduced searching-windows make the data distribution nearly linear in the region.
Spray Characteristics of an Unlike-Impinging Injector(F-O-O-F)
Kang, Shin-Jae ; Rho, Byung-Joon ; Oh, Je-Ha ; Kwon, Ki-Chul ; Park, Sang-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 93~93
This paper presents the spray characteristics of an impinging F-O-O-F type injector, which makes propellant impinge on each other to atomize, under the different momentum ratio. Water was used as the inert simulant liquid instead of fuel and oxidizer The droplet size and velocity in the impinging spray flowfield were measured using a PDPA. The droplet size of F-O-O-F type injector was expressed as a third-order function of the momentum ratio. The spray halfwidth in the long-axis direction declined throughout the entire spray flowfield, as the momentum ratio increased. However, the halfwidth in a short-axis direction increased near the spray front end but it gradually decreased with being far from the front end, as momentum ratio increased. The turbulance intensity and the turbulance kinetic energy were converged at the center of the spray front end with increasing the momentum ratio. The results of this study can be used for the design of an impinging type injector for liquid rockets.
Reliability Analysis of Payload Subsystem of a Communication Satellite HSTAR
Park, Jeong-Seok ; Kim, Jung-Ho ; Song, Jae-Kwan ; Woo, Hyung-Je ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 104~104
This paper presents the results of reliability analyses prepared for the preliminary design review of HSTAR satellite which was designed for the voice, video, and data transmission/distribution services at C-band(6/4GHz) and Ku-band(14/11GHz). The HSTAR spacecraft design utilized flight-proven hardware designs from previous Space Systems/Loral programs as much as possible. New hardware and subsystems had been designed for effective redundancy and cross-strapping to meet the numerical reliability requirements of the program, to minimize single point failure risks, to comply with part derating and application requirements, and to meet the design life specifications. The reliability numerical assessments which had been prepared for the payload subsystem included functional models, reliability block diagrams, mathematical models and numerical results. The final reliability assessment for the spacecraft met the numerical reliability requirements for 6 months and 10 years.
A Study on Design and Ground Test of KOMPSAT Flight Operation
Baek, Myung-Jin ; Choi, Hae-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 113~113
KOMPSAT(Korea Multi-Purpose Satellite) flight operation consists of solar array deployment and attitude stabilization operation, initial activation and checkout operation, routine mission operation, contingency operation and recovery operation. Solar array deployment and attitude stabilization operation and contingency operation are executed by on-board autonomous function without ground station intervention. On the other hand, initial activation and checkout operation, routine mission operation and recovery operation are executed only by ground command. KOMPSAT flight operation has been designed to meet the operational requirements for each operational state. Also, flight operation design has been verified by ground test using KOMPSAT ground station and KOMPSAT flight model. Namely, compatibility between ground and satellite segments has been verified and ground command capability to control the satellite has been verified. In this paper, KOMPSAT flight operation design and its ground test are discussed.
Analysis of Magnetic Field and Force for Koreasat-3 Silicon Solar Array
Ma, Keun-Su ; Lee, Jae-Deuk ; Hong, Jung-Pyo ; Kim, Yang-Mo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 124~124
In this paper, the magnetic field of Koreasat-3 silicon solar array and the force exerted on it are analyzed to consider the influence of them on the attitude of Koreasat-3. Since the solar panels of Koreasat-3 consist of seven silicon solar array panels and one gallium arsenide solar array panel, only silicon solar arrays are chosen for the analysis. The distribution of the flux density produced by current of the solar array, the one of the force produced by solar array current and the flux density due to its current, and the one of the force produced by solar array current and earth's magnetic field are analyzed in detail.
Numerical Study on the Selection of Airfoils for a Scaled Model Aircraft
NamGoong, Ho-Woong ; Koo, Sam-Ok ; Lee, Jang-Yeon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 131~131
As a preliminary study on the selection of low Reynolds number airfoil for the 1/8 scale aircraft of 30-Pax-Multipurpose-Transport, the aerodynamic characteristics of S8037 airfoil which is designed for model aircraft were calculated numerically and compared to a full scale NACA
airfoil. To maintain its controllability and flight safety of scaled aircraft, it is important to choose or design an airfoil adequate for a scaled model aircraft.
Configuration Design and Evaluation of a Fixed-Wing Micro Air Vehicle
Reu, Tae-Kyu ; Chung, In-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 136~136
The configuration concept of Micro Air Vehicle (MAV) being studied recently in USA, has been analyzed and a fixed-wing type flying wing configuration, having maximum dimension less than 15cm, has been designed. The successful flight of a small engine version of MAV based on the final configuration showed the possibility of domestic development of fixed wing type MAV. The DATCOM method was used to predict aerodynamic characteristics of each configuration, though it is not proper approach and a better analysis method should be developed.
The Technology of KOMPSAT 1
Kim, Zeen-Chul ; Kim, Hak-Jeong ; Rhee, Seung-Woo ; Sim, Eun-Sup ; Youn, Heong-Sik ; Lee, Sang-Seol ; Choi, Hae-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 143~143
F-22 Raptor Design Evolution (Part I)
Lee, Kyung-Tae ; Lee, Ki-Hak ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 28, issue 4, 2000, Pages 163~163