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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
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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
Prediction of Spring-in of Curved Laminated Composite Structure
Oh, Jae-Min ; Kim, Wie-Dae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 1~7
DOI : 10.5139/JKSAS.2015.43.1.1
This paper predicts the spring-in effect of curved laminated composite structure for various stacking sequence using finite element analysis(ABAQUS). In composite manufacturing process, large temperature difference, different coefficient of thermal expansion and chemical shrinkage effect cause distortion of composite parts such as spring-in and warpage. Distortion of composite structure is important issue on quality of product, and it should be considered in manufacturing process. In finite element analysis, a CHILE(Cure Hardening Instantaneously Linear Elastic) model and chemical shrinkage effects are considered developing user subroutine in ABAQUS and some cases are simulated.
SPH Code Development and Validation for Numerical Simulation of Liquid-Liquid Swirl Coaxial Injector
Kim, You-Cheon ; Sirotkin, Fedir V. ; Yoh, Jai-Ick ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 8~22
DOI : 10.5139/JKSAS.2015.43.1.8
Most jet spray and atomization simulations are done with the Eulerian method which has inherent disadvantage in representing jet breakups and droplets. Full Lagrangian particles method called Smoothed Particle Hydrodynamics(SPH) is used in this work. We develop the SPH code and perform validations that confirm the suitability of our SPH method for simulating liquid jet atomization problem. Then, we conduct the simulation of liquid-liquid swirl coaxial injector for comparison against the experimental data.
A Study on Modeling of Fighter Pilots Using a dPCA-HMM
Choi, Yerim ; Jeon, Sungwook ; Park, Jonghun ; Shin, Dongmin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 23~32
DOI : 10.5139/JKSAS.2015.43.1.23
Modeling of fighter pilots, which is a fundamental technology for war games using defense M&S (Modeling & Simulation) becomes one of the prominent research issues as the importance of defense M&S increases. Especially, the recent accumulation of combat logs makes it possible to adopt statistical learning methods to pilot modeling, and an HMM (Hidden Markov Model) which is able to utilize the sequential characteristic of combat logs is suitable for the modeling. However, since an HMM works only by using one type of features, discrete or continuous, to apply an HMM to heterogeneous features, type integration is required. Therefore, we propose a dPCA-HMM method, where dPCA (Discrete Principal Component Analysis) is combined with an HMM for the type integration. From experiments conducted on combat logs acquired from a simulator furnished by agency for defense development, the performance of the proposed model is evaluated and was satisfactory.
Development and Application of the Super High Temperature Thermal Test Equipment
Jun, Joon-Tak ; Kang, Hui-Won ; Yang, Myung-Seog ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 33~39
DOI : 10.5139/JKSAS.2015.43.1.33
This paper describes test result of the Supersonic Wing Structure and the utility of thermal test equipment, which is possible to heat rapidly and continuously above
, the durability and reliability of which are improved compared with the existing equipment. Through the test, we could predict the amount of strength reduction of the wing due to aerodynamic heating, caused by exposure of high temperature. Recently the aerodynamic heating temperature of the supersonic flying object is rapidly increased. It is possible to carry out the High Temperature Strength Test on the hypersonic speed flying object with the newly designed thermal test equipment. Because of that, we can upgrade the High Temperature Strength Structure Test technique and test reliability.
RF Seeker Measurement modeling using ISAR Image
Ha, Hyun-Jong ; Park, Woosung ; Jung, Ki-Hwan ; Park, Sang-Sup ; Koh, Il-Suek ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 40~48
DOI : 10.5139/JKSAS.2015.43.1.40
In this paper, we suggest a measurement modeling of the RF seeker using the ISAR(Inverse Synthetic Aperture Radar) image. Reference scattering points are extracted first from ISAR images which are changed according to target attitude. And then uncertainties included in RF seeker measurement such as noise strength, blink, and boresight error are added to the reference scattering points. The proposed measurement model of the RF seeker can be used to develop various kinds of target tracking algorithms.
GBAS Flight Testing and Performance Assessment using Flight Inspection Aircraft at Gimpo International Airport
Jeong, Myeong-Sook ; Bae, Joongwon ; Jun, Hyang-Sig ; Lee, Young Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 49~61
DOI : 10.5139/JKSAS.2015.43.1.49
Ground Based Augmentation System(GBAS) is a system that offers an aircraft within 23 NM radius from the airport precision positioning service and precision approach service using the concept of Differential Global Positioning System(DGPS). After GBAS ground equipment installing at the airport, functionalities and performances of GBAS should be verified through the GBAS ground and flight testing. This paper describes the methods and results for GBAS flight test using the flight inspection aircraft at Gimpo International Airport. From the test results, we confirmed that the VDB data was received without misleading within the VDB coverage of Gimpo International Airport, and VDB field strength, protection level, and course alignment accuracy met the evaluation`s criteria.
COMS GTO Injection Propellant Estimation using Monte-Carlo Method
Park, Eungsik ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 62~71
DOI : 10.5139/JKSAS.2015.43.1.62
Geostationary satellites use the thruster in order to control the location change and mount the suitable amount of liquid propellant depending on the operating lifetime. Therefore the lifetime of the geostationary satellite depends on the residual propellant amount and the precise residual propellant gauging is very important for the mitigation of economic losses arised from premature removal of satellite from its orbit, satellites replacement planning, slot management and so on. The propellant gauging methods of geostationary satellite are mostly used PVT method, thermal mass method and bookkeeping method. In this paper, we analysis the modeling of COMS(Communication, Ocean & Meteorological Satellite) bipropellant system for bookkeeping method and COMS GTO(Geostationary Transfer Orbit) injection propellant estimation using Monte-Carlo method.
Study on Thermal Vacuum Test Result of DCAMP by the Analysis of Derating & Gain Control
Jin, Byoung-Il ; Ko, Hyun-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 72~78
DOI : 10.5139/JKSAS.2015.43.1.72
Recently, the usage of the satellite is increased more and more in the areas that are communication, weather, marine, optical, radar etc. The functions of the Satellite are evolving from passive transponder to active transponder by the developing of a technology. Advanced countries in satellites install the DCAMP for increase of bandwidth efficiency, improvement of QoS by interference rejection. DCAMP includes many digital components in order to implement functions. Thus, these kinds of active transponders consume much more power compared to passive transponder and then increase the heat. In this paper, we discuss the TVAC test result of DCAMP in EQM(Engineering Qualification Model) level. The paper shows the test results of digital gain control in order to verify DCAMP status under the TVAC test. In addition, the temperature and heat condition of main components from viewpoint of derating will be treated through the official environment test for qualification.
Real Time On-board Orbit Determination Performance Analysis of Low Earth Orbit Satellites
Kim, Eun-Hyouek ; Koh, Dong-Wook ; Chung, Young-Suk ; Park, Sung-Baek ; Jin, Hyeun-Pil ; Lee, Hyun-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 79~87
DOI : 10.5139/JKSAS.2015.43.1.79
In this paper, a real time on-board orbit determination method using the extended kalman filter is suggested and its performance is analyzed in the environment of the orbit. Considering the limited on-board resources, the
orbit propagate model and the GPS navigation solution are used for on-board orbit determination. The analysis result of the on-board orbit determination method implemented in DubaiSat-2 showed that position and velocity error are improved from 70.26 m to 26.25 m and from 3.6 m/s to 0.044 m/s, respectively when abnormal excursion errors is removed in the GPS navigation solution.
Optimal Selection of Fuel Bias and Propellant Residual Analysis of a Liquid Rocket
Song, Eun-Jung ; Cho, Sangbum ; Roh, Woong-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 1, 2015, Pages 88~95
DOI : 10.5139/JKSAS.2015.43.1.88
This paper considers the effects of propellant mixture ratio and loading errors on the performance of a liquid rocket. Propellant residuals generated by error sources are analyzed for a launch vehicle model whose first stage consists of a cluster rocket of four 75-tonf class engines using a statistical Monte-Carlo approach and then the optimal fuel biases minimizing residuals are computed. The results are validated through comparison with analytic method using approximate formula, which have been applied for other space launch vehicles.