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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
Editor in Chief :
Volume & Issues
Volume 40, Issue 12 - Dec 2012
Volume 40, Issue 11 - Nov 2012
Volume 40, Issue 10 - Oct 2012
Volume 40, Issue 9 - Sep 2012
Volume 40, Issue 8 - Aug 2012
Volume 40, Issue 7 - Jul 2012
Volume 40, Issue 6 - Jun 2012
Volume 40, Issue 5 - May 2012
Volume 40, Issue 4 - Apr 2012
Volume 40, Issue 3 - Mar 2012
Volume 40, Issue 2 - Feb 2012
Volume 40, Issue 1 - Jan 2012
Selecting the target year
Study on the Design of High Speed Airfoil using the Geometric Interpolation and Optimization
Jung, Kyoung-Jin ; Lee, Jae-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 273~284
DOI : 10.5139/JKSAS.2012.40.4.273
In this paper, a study on the design of high speed airfoil is described. Various airfoils are investigated and existing airfoils are geometrically interpolated to generate new airfoils. An optimization method is applied to theses new airfoils and their aerodynamic performances are optimized. Through this study, it is demonstrated that the airfoil can be designed using the geometrical interpolation and the optimization method to exhibit good aerodynamic performances.
A performance analysis of terrain-aided navigation(TAN) algorithms using interferometric radar altimeter
Jeong, Seung-Hwan ; Yoon, Ju-Hong ; Park, Min-Gyu ; Kim, Dae-Young ; Sung, Chang-Ki ; Kim, Hyun-Suk ; Kim, Yoon-Hyung ; Kwak, Hee-Jun ; Sun, Woong ; Yoon, Kuk-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 285~291
DOI : 10.5139/JKSAS.2012.40.4.285
The paper experimentally verifies the performance of Terrain-Aided Navigation (TAN) using an interferometric radio altimeter, which is recently used due to its accuracy. First, we propose a TAN system that utilizes an interferometric radio altimeter as a measurement system. Second, we implement extended Kalman filter, unscented Kalman filter, and particle filter to evaluate the performance of TAN according to the selection of filters and the difference of environments.
RF Seeker LOS Rate Estimation Method using Covariance and Signal Management
Moon, Gwan-Young ; Jun, Byung-Eul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 292~299
DOI : 10.5139/JKSAS.2012.40.4.292
The line-of-sight(LOS) rate is estimated using Kalman filter in Radio-Frequency(RF) seeker. For the two axis gimbaled seeker, proper system modeling is considered and the basic filter structure is set up. The main issue for Kalman filter is choosing the proper process and measurement noise. For the measurement process, the signal to noise ratio(SNR) and other components are introduced. To cope with the eclipse problem or other abnormal seeker status, the pseudo input signal concept is proposed. By conditioning abnormal signals, the LOS rate estimation performance is increased. The process noise is also an important factor in the propagation phase. The analytical approach on a process noise component is performed and a reliable region for the filter is calculated based on the eigenvalue analysis. Some numerical simulations are performed to check the validity of suggested algorithm.
Procedure of Barometer Setting in Flight with On-board Navigation Data alone
Jung, Suk-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 300~308
DOI : 10.5139/JKSAS.2012.40.4.300
In GPS/INS/barometer navigation system for UAV, two procedures were proposed in order to set three reference parameters for the pressure altitude of QNH or QFE settings, using the navigation data from on-board system alone. These procedures yield required the reference parameters through mathematical process with the altitude and the atmosphere properties measured for a short duration of flight, of which a special pattern is requested according to the selected procedure. Dependency only upon the on-board navigation data can eliminate a requirement for the atmospheric measurement system in the ground support system and can expand a flight boundary to a remote area where the ground support is not available. Especially the procedure with the regression method uses altitude and pressure but temperature to produce the three reference parameters. No need of temperature measurement for the pressure altitude system can simplify the on-board air data system.
A Parametric Study on the Catalytic Combustion of Gaseous Methane, Ethane and Propane Fuels
Jung, Min-Seung ; Kim, Chong-Min ; Kim, Man-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 309~315
DOI : 10.5139/JKSAS.2012.40.4.309
Catalytic combustion is generally accepted as one of the environmentally preferred alternatives for heat and power from fossil fuels, as it has the advantage of stable combustion under very lean conditions with such low emissions as UHC, CO, and NOx. In this work, therefore, comparative numerical studies on the catalytic combustion behaviors over Pd-based catalysts have been conducted with the gaseous
. In the following, after introducing the governing equations with 1D channel and Langmuir-Hinshelwood models, numerical investigations on the catalyst performance are conducted by changing such various parameters as inlet temperature, excess air ratio, and space velocity. The numerical results show that outlet temperature and conversion of
are highest among others because of its chemical structure and reactivity.
Optimum design analysis of ICP(Inductively Coupled Plasma) torch for high enthalpy thermal plasma flow
Seo, Jun-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 316~329
DOI : 10.5139/JKSAS.2012.40.4.316
In this paper, optimum design process of ICP (Inductively Coupled Plasma) torch, which has been used widely in aerospace application, such as supersonic plasma wind tunnel, is presented. For this purpose, the behaviors of equivalent circuit parameters (equivalent resistance and inductance, coupling efficiency) were investigated according to the variations of torch design parameters (frequency,
, confinement tube radius,
and coil turn numbers,
) in the basis of analytical and numerical MHD (Magneto Hydro-Dynamics) models combined with electrical circuit theory. From the results, it is found that equivalent resistance is increased with the increase of
values but vice versa for equivalent inductance. For elevated values of
, however, both parameters tend to increase. Based on these observations, ICP torch with a power level of 10 kW can be optimized at the design ranges of
=17~25 mm and
=3~4 to maximize the electrical coupling efficiency, which is the ratio of equivalent resistance to equivalent inductance.
Structure Analysis of KHP Main & Nose Wheel
Kim, Yong-Hwan ; Lee, Sea-Wook ; Ju, Young-Chan ; Chi, Chong-Ho ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 330~335
DOI : 10.5139/JKSAS.2012.40.4.330
This study performed the structure analysis for development and localization of main and nose wheel in Korean Helicopter Program(KHP). Structural stability of wheel is evaluated using ANSYS. Considering wheel and tire interface, Stress analysis was conducted by applying pneumatic of tire, static load, radial load and combined load on main and nose wheel. Considering yield strength at which plastic deformation occurs, simulation results suggest the method which increases structure stability after comparing maximum stress and yield strength.
Reliability Estimation for Crack Growth Life of Turbine Wheel Using Response Surface
Jang, Byung-Wook ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 336~345
DOI : 10.5139/JKSAS.2012.40.4.336
In crack growth life, uncertainties are caused by variance of geometry, applied loads and material properties. Therefore, the reliability estimation for these uncertainties is required to keep the robustness of calculated life. The stress intensity factors are the most important variable in crack growth life calculation, but its equation is hard to know for complex geometry, therefore they are processed by the finite element analysis which takes long time. In this paper, the response surface is considered to increase efficiency of the reliability analysis for crack growth life of a turbine wheel. The approximation model of the stress intensity factors is obtained by the regression analysis for FEA data and the response surface of crack growth life is generated for selected factors. The reliability analysis is operated by the Monte Carlo Simulation for the response surface. The results indicate that the response surface could reduce computations that need for reliability analysis for the turbine wheel, which is hard to derive stress intensity factor equation, successfully.
Characteristics of Laser-Induced Breakdown Spectroscopy (LIBS) at Space Environment for Space Resources Exploration
Choi, Soo-Jin ; Yoh, Jai-Ick ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 346~353
DOI : 10.5139/JKSAS.2012.40.4.346
The Laser-Induced Breakdown Spectroscopy (LIBS) has great advantages as an analytical technique, namely real-time analysis without sample preparation, ideal for mobile chemical sensor for space exploration. The LIBS plasma characteristics are strongly dependent on the surrounding pressure. In this study, seven types of target (C, Ti, Ni, Cu, Sn, Al, Zn) were investigated for their elemental lifetime. The target was located in vacuum chamber which has the pressure range of 760 to
torr. As the pressure is decreased, the elemental lifetimes of carbon and titanium declined, while all other targets showed increased lifetimes until reaching 1 torr and declined with continued pressure decrease. The boiling point and electronegativity amongst the physicochemical properties of the samples are used to explain this peculiarity.
Removal trajectory generation for LEO satellites and analysis collision probability during removal maneuver
Seong, Jae-Dong ; Min, Chan-Oh ; Jeong, Soon-Woo ; Lee, Dae-Woo ; Cho, Kyeum-Rae ; Kim, Hae-Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 354~363
DOI : 10.5139/JKSAS.2012.40.4.354
Now there are a lot of expired satellites or space debris around the earth orbit and they threaten the operating satellites and manned space missions. KOMPSAT-2 that scheduled to operate the mission by July, 2013 also has to consider the space debris. This paper introduces the '25 years rules' that must be re-entered within 25 years after the space mission for LEO satellites and describes the removal trajectory design that satisfies the '25 years rules' and minimizes fuel consumption. And this paper suggests monte-carlo simulation for risk analysis that causes the approaching object to the removal trajectory. The result shows that the collision probability of worst case presents 6.0741E-07 and it need to more analysis about precise satellite safety during removal maneuver because there is no information about the object size that approaching to the satellites.
Studies for Reliability-corrected Cost Estimation Methodology of Launch Vehicle Development
Kim, Hong-Rae ; Yoo, Dong-Seo ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 4, 2012, Pages 364~374
DOI : 10.5139/JKSAS.2012.40.4.364
The purpose of this study is to perform the reliability-corrected development cost estimation of the launch vehicle at the conceptual design phase. In order to estimate the launch vehicle development cost, the estimation method based on the independent variable such as the rocket performance and dry mass has been mainly implemented up to now. This approach has made the approximate cost estimation possible, however, the cost variation according to the reliability requirement could not be reflected. In this paper, the cost estimation methodology that introduces the reliability factor in addition to the performance and mass in the TRANSCOST model is presented in order to improve the limitation of current cost estimation method. The development cost of KSLV(Korea Space Launch Vehicle)-II is estimated on the basis of this newly implemented concept with reliability as an added parameter.