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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 43, Issue 12 - Dec 2015
Volume 43, Issue 11 - Nov 2015
Volume 43, Issue 10 - Oct 2015
Volume 43, Issue 9 - Sep 2015
Volume 43, Issue 8 - Aug 2015
Volume 43, Issue 7 - Jul 2015
Volume 43, Issue 6 - Jun 2015
Volume 43, Issue 5 - May 2015
Volume 43, Issue 4 - Apr 2015
Volume 43, Issue 3 - Mar 2015
Volume 43, Issue 2 - Feb 2015
Volume 43, Issue 1 - Jan 2015
Selecting the target year
Monocular Vision based Relative Position Measurement of an Aircraft
Kim, Jeong-Ho ; Lee, Chang-Yong ; Lee, Mi-Hyun ; Han, Dong-In ; Lee, Dae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 289~295
DOI : 10.5139/JKSAS.2015.43.4.289
This paper describes a ground monocular vision-based measurement algorithm measuring relative range and position of aircraft using the information of wingspan and optical parameters for the camera. A technique obtaining an aircraft image is also described in this paper. This technique can be used as external measurement for autonomous landing instead of ILS. To verify the performance of these algorithms, flight experiment is performed using light sport aircraft with GPS and monocular camera. Finally we obtained the reasonable RMSE of 1.85m is obtained.
Performance Evaluation of Hydrogen Generation System using NaBH
Hydrolysis for 200 W Fuel Cell Powered UAV
Oh, Taek-Hyun ; Kwon, Sejin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 296~303
DOI : 10.5139/JKSAS.2015.43.4.296
The concentration of solute in a
solution is limited due to the low solubility of
. The performance of a hydrogen generation system was evaluated using various concentrations of
solution. First, a self-hydrolysis test and a hydrogen generation test for 30 min were performed. The composition of
solution was selected to be 1 wt% NaOH + 25 wt%
by considering the amount of hydrogen loss, stability of hydrogen generation,
precipitation, conversion efficiency, and the purpose of its application. A hydrogen generation system for a 200 W fuel cell was evaluated for 3 h. Although hydrogen generation rate decreased with time due to
precipitation, hydrogen was produced for 3 h (conversion efficiency: 87.4%). The energy density of the 200 W fuel cell system was 263 Wh/kg. A small unmanned aerial vehicle with this fuel cell system can achieve 1.5 times longer flight time than one flying on batteries.
Performance Analysis of the Pintle Thruster Using 1-D Simulation -I : Steady State Characteristics
Kim, Jihong ; Noh, Seonghyeon ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 304~310
DOI : 10.5139/JKSAS.2015.43.4.304
Pintle thrusters use pintle stroke to change nozzle throat area, and this controls thrust. Using MATLAB, one-dimensional simulation has been investigated and the results are compared to those of cold flow tests and computational fluid dynamics for the pintle thruster of Chungnam National University. The prediction based on one-dimensional flow theory shows good agreement with measurements for chamber pressure, but deviates for thrust, partly because of nozzle wall separation. Computational results show that nozzle wall separation occurs at an early stage of nozzle expansion, near the design nozzle throat, for the course of pintle strokes. Empirical thrust prediction incorporates nozzle wall separation, and thus 1-D simulation using empirical thrust prediction showed good results for an early stage of pintle stroke.
Performance Analysis of the Pintle Thruster Using 1-D Simulation-II : Unsteady State Characteristics
Noh, Seonghyeon ; Kim, Jihong ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 311~317
DOI : 10.5139/JKSAS.2015.43.4.311
This paper describes how to apply one-dimensional simulation to predict unsteady state characteristics of the cold-gas pintle thruster. Mass flow rate, chamber pressure, and nozzle exit pressure are key parameters for thrust control. Chamber pressure rose and fell monotonously with the pintle stroke variation, while thrust variation was different from chamber pressure variation. During the forward pintle stroke operation, the thrust value tended to decrease initially and returned to increase when pintle speed and chamber free volume exceed some specified value. Even though one-dimensional simulation has the limitations to predict unsteady state characteristics, it is still useful for initial performance assessment of various thrusters which adopt an altitude compensation nozzle such as a dual-bell nozzle, prior to experiment or numerical analysis.
On-orbit Analysis of Power Generation Efficiency of Concentrating Photovoltaic System Using Commercial Fresnel Lens for Pico Satellite Applications
Park, Tae-Yong ; Chae, Bong-Geon ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 318~325
DOI : 10.5139/JKSAS.2015.43.4.318
Pico satellite has limited surface to install the solar cells due to its extremely limited size. Also, the sun incidence angle with respect to the solar panel continuously varies according to the attitude control strategy and its important parameter for the power generation. In this study, a concentrating photovoltaic system for pico satellite application has been proposed that can enhance the power generation efficiency in case of the unfavorable condition of the sun incidence angle with respect to the solar panel of the satellite using the fresnel lens. To prove the possibility of maximizing the power generation efficiency of the proposed concentrating power system, we have performed the power measurement test using a solar simulator and commercial fresnel lens. And on-orbit analysis of the power generation efficiency using the STK which is a commercial S/W has also been performed based on the test results.
Multi-Objective Optimization of Turbofan Engine Performance Using Particle Swarm Optimization
Choi, Jaewon ; Chung, Wonchul ; Sung, Hong-Gye ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 326~333
DOI : 10.5139/JKSAS.2015.43.4.326
A turbo fan engine performance analysis program combined with a particle swarm optimization(PSO) has been developed to optimize the major design parameters of the combat aircraft gas turbine engine. The optimized parameters includes bypass ratio, fan pressure ratio, high pressure compression ratio and burner exit temperature. The objective parameters have been determined using a multi-objective function consisting of the net thrust and specific fuel consumption along a weight function. The basic model for the combat aircraft gas turbine engine has been selected as the F404 turbofan engine which is widely used in the combat aircraft, F-18 and Korean high level training aircraft, T-50. The optimal conditions of four parameters have been obtained for various design conditions.
The Effect of Overdesign on Titan Rocket Engine Reliability and Development Cost
Kim, Kyungmee O. ; Hwang, Junwoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 334~340
DOI : 10.5139/JKSAS.2015.43.4.334
Engine derating is often considered for reliability benefits because lower power operation reduces its failure probability. To be derated during operation, however, the engine must be initially overdesigned. The engine overdesign is cost effective only if reliability increased from derating is enough to offset the initial increase in the development cost caused from the overdesign. The purpose of this paper is to provide an analytical model to consider a trade-off between the engine overdesign and derating. We use a logistic regression model to explain reliability growth in the number of hot firing tests for a fixed power level. Using the Transcost model with the reliability growth model, we show that 10% overdesign of Titan rocket engine decreases its development cost by about 9% and 23% depending on the reliability requirement. We also point out that such a cost reduction depends on the fuel type a rocket uses.
Stage Separation Analysis of Launch Vehicle Using Monte Carlo Simulation
Oh, Choong-Seok ; Sun, Byung-Chan ; Park, Yong-Kyu ; Roh, Woong-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 341~348
DOI : 10.5139/JKSAS.2015.43.4.341
This paper addresses Monte-Carlo simulation analyses for the stage separation of the general launch vehicle. The stage separation event of the launch vehicle occurs during a very short time and is related with many dynamic parameters. The stage separation is a critical event in that the launch fails if there is a collision during the stage separation. The stage separation analyses was conducted for the general launch vehicle to confirm the separation without collision within the designed clearance in case of the random input parameters. This paper presents the stochastic results of the stage separation of the launch vehicle using the Monte-Carlo simulation.
Research/Development Trend and Technical Enablers of Trajectory-based Operations in Air Traffic Management
Eun, Yeonju ; Jeon, Daekeun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 349~358
DOI : 10.5139/JKSAS.2015.43.4.349
The research and development trend of Trajectory-based Operations(TBO), which is considered as a key concept of future Air Traffic Management(ATM), is presented in this paper. The operational concepts of TBO in ASBU(Aviation System Block Upgrade) from ICAO(International Civil Aviation Organization) have been summarized, and the detailed operational concepts and procedures, which can be realized in the near future, are described through the investigations of operational concept development and related research/development activities of TBO in USA and Europe. The technical enablers, which have been identified based on understanding of TBO operational concepts, are introduced, and related research/development status of each technical enabler has been presented.
Development of Educational Program for Rocket Science for High School Students
Moon, Young Joo ; Lee, Dong Eun ; Lee, Sul Ha ; Lee, Eun Joo ; Lee, Changjin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 359~367
DOI : 10.5139/JKSAS.2015.43.4.359
This paper aims to design an educational science program based on rocket propulsion for high school students. Curriculum in high school physics and chemistry were evaluated to find out scientific match with basic principles in rocket propulsion. Also model rocketry was implemented as a part of the educational program. Solid propellants were prepared by the combination of sorbitol and candy after a selection process for solid propellant from several high caloric food candidates. Specially, this program was intended to give an opportunity to organize basic knowledge of high school science with model rocketry by measuring combustion temperature, thrust level of developed propellants. A pilot operation of the program was done with four high school students to evaluate the achievement of final goals of the program both in technical and educational aspect.
A Sensitivity Analysis and Parametric Study for the Establishment of the Helicopter Initial Design Model
Kim, Seung Bum ; Choi, Jong Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 368~376
DOI : 10.5139/JKSAS.2015.43.4.368
This paper is the study on the establishment of design model to improve design efficiency using modified weight estimation equation on the initial design stage for development of a helicopter. The methodology to extract coefficients of the weight estimation equation was proposed through the influence investigation for the weight of components and the parameter study and sensitivity analysis for design variables such as the rotor disk loading, the number of blade and the aspect ratio of blade were also performed. As a result of study, the relation of parameters and degree of sensitivity of parameters on helicopter design are considerable points for optimization of helicopter characteristics, and it is necessary for designer to consider the complex relation of main parameters.
Orbit Evolution Analysis of DubaiSat-2 using Hall-effect Thruster
Kim, Eun-Hyouek ; Kim, Youn-Ho ; Park, Jong-Soo ; Koh, Dong-Wook ; Jeong, Yun-Hwang ; Lee, Hyun-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 4, 2015, Pages 377~386
DOI : 10.5139/JKSAS.2015.43.4.377
DubaiSat-2 is the first satellite developed in Korea equipped with a hall-effect thruster. In this paper, the performance of the DubaiSat-2 hall-effect thruster is verified by analyzing the orbit information of DubaiSat-2. The preparation and performance of orbit operations during 8 months after launch (2013.11.21., UTC) is emphasized and the effects of solar activity on orbit evolution is analyzed. In particular, the hall-effect thruster`s thrust is estimated by analyzing difference between observed orbit evolution and predicted orbit. As a result, the estimated thrust is similar to the ground experiment result of 11 mN. The summarized result in this paper would be important reference to improve the stability and effectiveness of satellite operation during the early operation and normal mission lifetime in case of low Earth orbit satellites.