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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
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The Slip-Wall Boundary Conditions Effects and the Entropy Characteristics of the Multi-Species GH Solver
Ahn, Jae-Wan ; Kim, Chong-Am ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 947~954
DOI : 10.5139/JKSAS.2009.37.10.947
Starting from the Eu`s GH(Generalized Hydrodynamic) theory, the multi-species GH numerical solver is developed in this research and its computatyional behaviors are examined for the hypersonic rarefied flow over an axisymmetric body. To improve the accuracy of the developed multi-species GH solver, various slip-wall boundary conditions are tested and the computed results are compared. Additionally, in order to validate the entropy characteristics of the GH equation, the entropy production and entropy generation rates of the GH equation are investigated in the 1-dimensional normal shock structure test at a high Knudsen number.
Detached Eddy Simulation of Base Flow in Supersonic Mainstream
Shin, Jae-Ryul ; Moon, Sung-Young ; Won, Su-Hee ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 955~966
DOI : 10.5139/JKSAS.2009.37.10.955
DES method is applied to an axisymmetric base flow at supersonic mainstream. The model is based on the Spalart-Allmaras (S-A) turbulence model in the RANS mode, and is based on the subgrid scale model in the Large-eddy simulation (LES) mode. Accurate predictions of the base flowfield and base pressure are successfully achieved by using the DES methodology which is less expensive than LES. Flow properties at the edge of base, such as boundary layer thickness, momentum thickness and skin fraction are compared with Dutton et al [experimental data to proper prediction of base flowfiled. From the present results, The DES accurately resolves the physics of unsteady turbulent motions, such as shear layer rollup, large-eddy motions in the downstream region and small eddy motions inside the recirculating region. Moreover, The present results of using an empirical constant
of 1.2 shows good agreement with experimental data than conventional empirical constant
Aerodynamic Measurement over a Protuberance in Hypersonic Flows Using Coaxial Thermocouple and TSP
Lee, Hyoung-Jin ; Lee, Bok-Jik ; Jeung, In-Seuck ; Kim, Seong-Lyong ; Kim, In-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 967~974
DOI : 10.5139/JKSAS.2009.37.10.967
Experiments were conducted to measure the heat flux and temperature over a protuberance, using an impulse hypersonic shock tunnel-coaxial thermocouples and a blowdown hypersonic wind tunnel-temperature sensitive paints(TSP). Experimental data were compared with the heat flux data using a blowdown hypersonic wind tunnel-heat flux gauges and it was confirmed data sets agreed well. The measured heat flux is large when the height of the protuberance is large. Also, the heat flux measurements at the upper positions are larger than at the lower positions. For high protuberances, a severe jump in the heat flux is observed, from about 0.6~0.7 of the height of the protuberances. However, when the protuberance is sufficiently short, a rise in the heat flux is rarely observed as the protuberance is submerged totally under the separation region.
Development and Verification of Small-Scale Rotor Hover Performance Test-stand
Lee, Byoung-Eon ; Seo, Jin-Woo ; Byun, Young-Seop ; Kim, Jeong ; Yee, Kwan-Jung ; Kang, Beom-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 975~983
DOI : 10.5139/JKSAS.2009.37.10.975
This paper presents the work being carried out in order to deduce hover performance of a small-scale single rotor blade as a preliminary study of a small coaxial rotor helicopter development. As an initial research, a test stand capable of measuring thrust and torque of a small-scale rotor blade in hover state was constructed and fabricated. The test stand consists of three parts; a rotating device, a load measuring sensor and a data acquisition system. Thrust and torque were measured with varying collective pitch angle at fixed RPM. Through this research, hover performance tests were conducted for a small-scale single rotor blade operating in low Reynolds number (
), as well as for verifying the test stand itself for acquiring hover performance.
Aeroelastic Response Analysis for Wing-Body Configuration Considering Shockwave and Flow Viscous Effects
Kim, Dong-Hyun ; Kim, Yu-Sung ; Hwang, Mi-Hyun ; Kim, Su-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 984~991
DOI : 10.5139/JKSAS.2009.37.10.984
In this study, transonic aeroelastic response analyses have been conducted for the DLR-F4(wing-body) aircraft configuration considering shockwave and flow separation effects. The developed fluid-structure coupled analysis system is applied for aeroelastic computations combining computational structural dynamics(CSD), finite element method(FEM) and computational fluid dynamics(CFD) in the time domain. It can give very accurate and useful engineering data on the structural dynamic design of advanced flight vehicles. For the nonlinear unsteady aerodynamics in high transonic flow region, Navier-Stokes equations using the structured grid system have been applied to wing-body configurations. In transonic flight region, the characteristics of static and dynamic aeroelastic responses have been investigated for a typical wing-body configuration model. Also, it is typically shown that the current computation approach can yield realistic and practical results for aircraft design and test engineers.
Verification of Missile Angular Velocity Calculation Using FMS
Park, Eo-Jin ; Kim, Wan-Shik ; Park, Chan-Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 992~997
DOI : 10.5139/JKSAS.2009.37.10.992
This paper focuses on the calculation of the missile angular velocity under the reduced sensor condition and its verification using the Flight Motion Simulator(FMS). The missile angular velocity is usually measured by the body gyroscopes, but we assume that the inertial sensors on the missile body are in the absence of pitch and yaw gyroscopes. Under this reduced sensor condition, this paper shows the missile angular velocity can be calculated by using the gimbal seeker gyroscope, the roll body gyroscope, the gimbal angle and its rate. The FMS experiment was carried out to verify the proposed algorithm.
Analysis on Optimality of Proportional Navigation With Time-Varying Velocity
Jeon, In-Soo ; Lee, Jin-Ik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 998~1001
DOI : 10.5139/JKSAS.2009.37.10.998
This paper shows that the conventional proportional navigation guidance(PNG) law with a constant navigation gain is an optimal solution strictly also when the velocity is varying during engagement. Especially, PNG with navigation constant, 3, is an optimal solution minimizing a closing velocity weighted induced-drag. While most of previous studies on optimality of PNG were relied on the linear formulation and the constant speed assumption, this study presents more general analysis results on optimality of PNG based on the nonlinear formulation and the time-varying velocity assumption.
Guidance Filter Design Based on Strapdown Seeker and MEMS Sensors
Yun, Joong-Sup ; Ryoo, Chang-Kyung ; Song, Taek-Lyul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 1002~1009
DOI : 10.5139/JKSAS.2009.37.10.1002
Precision guidance filter design for a tactical missile with a strapdown seeker aided by low-cost strapdown sensors has been addressed in this paper. The low-cost strapdown sensors consist of an IMU with 3-axis accelerometers and gyroscopes, 3-axis magnetometers, and a barometer. Missile`s position, velocity, attitude, and bias error of the barometer are considered as state variables. Since the state and measurement equations are highly nonlinear, we adopt UKF(Unscented Kalman Filter). The proposed guidance filter has a function of a navigation filter if target position error is not considered. In the case that the target position error is introduced, the proposed filter can effectively estimate the relative states of the missile to the true target. For specific engagement scenarios, we can observe that observability problems occur.
A Study on Technique of Development Test by an Aircraft Captive Flight Test in Weapon System
Yeom, Hyeong-Seop ; Oh, Jong-Hoon ; Sung, Duck-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 1010~1016
DOI : 10.5139/JKSAS.2009.37.10.1010
In this paper, we have described an aircraft captive flight test for the development test of weapon systems. We have conducted a captive flight test for the development of core onboard parts and sensors of airborne weapons and guided missiles. We have used KTX-1/XKO-1 aircraft as a platform for the captive flight test. In order to perform a captive flight test, we have made a captive test pod as a shape of external fuel tank in the XKO-1 and have modified XKO-1 aircraft for a system interface. We have taken a development test about all kinds of seekers, navigation & guidance systems, and core part of guided missile through the aircraft captive flight test.
Multi-Junction Space Solar Cell Health Checking Method using Electroluminescence Phenomena
Park, Je-Hong ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 1017~1026
DOI : 10.5139/JKSAS.2009.37.10.1017
The solar cell system operates by facing the sun-light. Minor cracks, static discharge, and thermal shock that can happen during production/testing phase can lead to degradation in performance during operation, since solar cells are exposed to extreme thermal/mechanical environment in space. In order to detect small cracks and internal damages in the solar cells due to thermal shocks, which are the core units of a solar cell system, expensive equipment, complicated test process, and much time are required. Therefore, a qualitative method for easily and quickly testing the `health` of solar cell functionality is required. This dissertation describes a theoretical and technical grounds for quickly and easily evaluating the health of solar cells using electroluminescence effect of Gallium-Arsenide solar cells that are most widely used by spacecrafts in recent years. Also described in the dissertation is the technical issues and constraining factors for applying the proposed method to actual space-rated solar cell systems.
Development of 30-Ton
LOx/Kerosene Rocket Engine Combustion Devices(I) - Combustion Chamber
Choi, Hwan-Seok ; Han, Young-Min ; Kim, Young-Mog ; Cho, Gwang-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 1027~1037
DOI : 10.5139/JKSAS.2009.37.10.1027
The development of a combustion chamber for a 30-
regeneratively-cooled space liquid rocket engine is described. Starting from the development of bi-propellant swirl coaxial injectors, essential technologies were verified through subscale combustion chambers and afterwards applied to the full-scale combustion chambers. A total of 5 full-scale combustion chambers have been utilized to verify ignition, combustion efficiency and stability, cooling, and duration requirements. A total of 46 combustion tests were performed among which 23 tests were parallely performed with stability rating tests using a pulse gun device. The test results have revealed that the 30-
regeneratively-cooled combustion chamber fully complies to the performance and combustion stability requirements and thus concluded that the development is successfully completed.
Development of 30-Ton
LOx/Kerosene Rocket Engine Combustion Devices(II) - Gas Generator
Choi, Hwan-Seok ; Seo, Seong-Hyeon ; Kim, Young-Mog ; Cho, Gwang-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 1038~1047
DOI : 10.5139/JKSAS.2009.37.10.1038
The development process of a gas generator for a 30-tonf pump-fed space liquid rocket engine is described. Starting from the development of an injector, followed by subscale and full-scale test specimens, the development of LOx/kerosene fuel-rich gas generator has been concluded successfully. Various analytical methods have been utilized in the course of design and the performance requirements have been verified experimentally through ignition tests, combustion performance and stability assessment tests and duration tests. The gas generator has proven its workability and stability within a defined operation window of varying chamber pressure and mixture ratio and demonstrated compliance to the performance and life time requirements.
A Propellant Loading Analysis Program of Bipropellant Propulsion System
Chae, Jong-Won ; Han, Cho-Young ; Yu, Myoung-Jong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 10, 2009, Pages 1048~1053
DOI : 10.5139/JKSAS.2009.37.10.1048
It proposes an simple and intuitive method that calculates the equilibrium pressures of a propellant tank by appling the mass conservation principle on the helium in the liquid propellant and in an ullage volume of the propellant tank. A propellant loading analysis program is developed and validated against the existing reference data. And it has applied to the present developing program, COMS Chemical Propulsion Subsystem and the results are compared, it may use to develop a technology of the next geostationary complex satellite`s propulsion system.