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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 42, Issue 12 - Dec 2014
Volume 42, Issue 11 - Nov 2014
Volume 42, Issue 10 - Oct 2014
Volume 42, Issue 9 - Sep 2014
Volume 42, Issue 8 - Aug 2014
Volume 42, Issue 7 - Jul 2014
Volume 42, Issue 6 - Jun 2014
Volume 42, Issue 5 - May 2014
Volume 42, Issue 4 - Apr 2014
Volume 42, Issue 3 - Mar 2014
Volume 42, Issue 2 - Feb 2014
Volume 42, Issue 1 - Jan 2014
Selecting the target year
CFD Analysis of Aerodynamic Characteristics of a BWB UCAV configuration with Transition effect
Jo, Young-Hee ; Chang, Kyoungsik ; Sheen, Dong-Jin ; Park, Soo Hyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 535~543
DOI : 10.5139/JKSAS.2014.42.7.535
A computational simulation for a nonslender BWB UCAV configuration with rounded leading edge and span of 1.0m was performed to analyze its aerodynamic characteristics. The freestream is 50m/s over -4 to 26 degree A.o.A.s. Reynolds number based on the mean chord length is
. 3D multi block hexahedral grids are used which allow good grid quality and ease to capture boundary layer.
model as well as
SST model is employed to assess the effect of transition for flow behavior. Drag and lift of the UCAV were well predicted while
is under predicted at high angle of attacks and influenced by the turbulence models strongly. After assessing pressure distribution, skin friction lines and velocity field around the UCAV configuration, it was found that transition effect should be considered to enhance the prediction of aerodynamic behavior by a vortical flowfield.
Performance Analysis of KSLV-II Launch Vehicle with Liquid Rocket Boosters
Yang, Won-Seok ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 544~551
DOI : 10.5139/JKSAS.2014.42.7.544
A program of launch vehicle performance analysis is composed for the education of the conceptual design of launch vehicles and the requirement analysis for the propulsion system design. The program is applied for the mission analysis of space launch vehicles based on KSLV-II with liquid rocket boosters. The 75-ton class liquid rocket engine is assumed for the boosters by referring the mass ratio of KSLV-II second stage. The launch performance analysis is carried out for KSLV-II with 2, 3 and 4 boosters by targeting the circular orbit of 700 km altitude. The trajectory is assumed as two-dimension considering the variation of the flight environment. Payload of advanced KSLV-II could be increased to maximum 3 tons, though it is limited by the thrust performance of the upper stage.
Theoretical Performance Prediction Program of Pulse Detonation Engines
Kim, Tae-Young ; Kim, Ji-Hoon ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 552~560
DOI : 10.5139/JKSAS.2014.42.7.552
Pulse Detonation Engine(PDE) has been investigated as a next generation propulsion system with the advantages of the higher thermal efficiency by the compression effect and the wide operation ranges from zero speed at ground. In the present study, an efficient theoretical PDE performance prediction program was developed for realistic propellants based on the Endo`s theory combining the Chapman-Jouguet detonation theory and expansion process of burnt gas in a constant area tube. The program was validated through the comparison with the experimental data obtained by a ballistic pendulum measurement. PDE performance analyses were carried out for various hydrocarbon fuels and oxidizer compositions by changing the mixture equivalence ratio and initial conditions. Theoretical PDE performance database could be established as a result of the analyses.
The Analysis of Wind Hole Effect for The Bangpae Kite
Kang, Chi-Hang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 561~566
DOI : 10.5139/JKSAS.2014.42.7.561
Our Korean traditional cultural inheritance Bangpae Kite has the stable rectangular shield shape decorated with artistic paint or poem and a good flight performance due to the central wind hole. In this paper, to analyse the wind hole effect to kite performance we performed the wind tunnel testing of the various design factor of kite model and air flow visualization passing through the wind hole. As the result of aerodynamic analysis, we knew that the wind hole of kite displays similar function of slot system for the wing high lift device. This fact demonstrates that our ancestor understood the function of slot system and applied effectively to the development of kite flight performance.
Flight Demonstration Test of a Smart Skin Antenna for Communication and Navigation
Kim, Min-Sung ; Park, Chan-Yik ; Cho, Chang-Min ; Yoon, Jong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 567~575
DOI : 10.5139/JKSAS.2014.42.7.567
This paper suggests an installation procedure of a smart skin prototype into an aircraft, flight demonstration test procedures and test results. Four communication and navigation antennas are embedded into one Conformal Load-bearing Antenna Structure(CLAS). Log periodic patch type antenna was designed as a multi-band antenna to cover four antenna frequency bands. The requirements of CLAS were verified by ground tests before aircraft installation. A CLAS speed-brake was installed into KT-1 aircraft and performances of dual antennas were verified as multi-antenna tests on the ground. Electromagnetic compatibility tests were conducted to check compatibility between the CLAS and all existing equipments. Flight demonstration tests were conducted by one sortie of flight test for one antenna. The activeness and continuity of communication and navigation signal during the flight, null area of antenna signal along the circling flight were monitored. The embedded antennas worked better than expected during four sorties of flight tests.
A Survey on Moving Target Indication Techniques for Small UAVs : Parametric Approach
Yun, Seung Gyu ; Kang, Seung Eun ; Ko, Sang Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 576~585
DOI : 10.5139/JKSAS.2014.42.7.576
In this paper, we survey the Moving Target Indication(MTI) techniques for small UAVs. MTI consists of image alignment phase and frame differencing correction phase, and image alignment has two ways of parametric approach which is mainly focused in this paper and non-parametric approach. Since small UAVs are operated in the low altitude, the parallax is considerable and the epipolar geometry is applied to compensate the parallax. The related works and future works are presented.
Mission and Conceptual System Design of Solar Sail Testing Cube Satellite CNUSAIL-1
Koo, Soyeon ; Kim, Gyeonghun ; Yoo, Yeona ; Song, Sua ; Kim, Sungkeun ; Oh, Bockyoung ; Woo, Beomki ; Han, Chang-Gu ; Kim, Seungkeun ; Suk, Jinyoung ; Han, Sanghyuck ; Choi, Gi-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 586~593
DOI : 10.5139/JKSAS.2014.42.7.586
The CNUSAIL-1 project aims to develop and operate a 3U-sized cube satellite with solar sail mechanism. The primary mission is to successfully deploy the solar sail in a low earth orbit, and the secondary mission is to collect the scientific data for the effect of the solar sail deployment and operation on orbit maneuver and attitude change of the cube satellite. For this, the bus system will collect and transmit the dynamic data of the satellite and the visual images of the solar sail operation. This paper describes solar sail mission and conceptual design of CNUSAIL-1. The actuation/operation of the solar sail and the bus system are preliminarily designed in terms of attitude control system, communication system, electrical power system, command and data handling system, structure and thermal control system is designed.
Design and Implementation of Interference-Immune Architecture for Digital Transponder of Military Satellite
Sirl, Young-Wook ; Yoo, Jae-Sun ; Jeong, Gun-Jin ; Lee, Dae-Il ; Lim, Cheol-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 594~600
DOI : 10.5139/JKSAS.2014.42.7.594
In modern warfare, securing communication channel by combatting opponents` electromagnetic attack is a crucial factor to win the war. Military satellite digital transponder is a communication payload of the next generation military satellite that maintains warfare networks operational in the presence of interfering signals by securely relaying signals between ground terminals. The transponder in this paper is classified as a partial processing transponder which performs cost effective secure relaying in satellite communication links. The control functions of transmission security achieve immunity to hostile interferences which may cause malicious effects on the link. In this paper, we present an efficient architecture for implementing the control mechanism. Two major ideas of pipelined processing in per-group control and software processing of blocked band information dramatically reduce the complexity of the hardware. A control code sequence showing its randomness with uniform distribution is exemplified and qualification test results are briefly presented.
Mechanism Modeling and Analysis of Deployable Satellite Antenna
Lee, Seung-Yup ; Jeong, Suk-Yong ; Choi, Yoon-Hyuk ; Cho, Ki-Dae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 601~609
DOI : 10.5139/JKSAS.2014.42.7.601
Large number of SAR(Synthetic Aperture Radar) satellites, one type of earth observation satellite, have been developed as they have the advantage of not being affected by surrounding environment during the earth image acquisition. In order to gain high image quality, SAR antenna should have large diameter. However, internal space of satellite launch vehicle is limited and this leads SAR antenna to be designed deployable so that it can be folded in launch vehicle and unfolded in space. In this research, values of various design factors of deployable satellite antenna were chosen considering satellite`s target mission. Configuration of deployable satellite antenna was designed by applying the chosen values of design factors, and variation in deployable satellite antenna during satellite maneuver was observed through simulation.
Analysis on the transient response of Polyphase DFT filter banks in the frequency hopping communication satellite transponder
Lee, Daeil ; Joo, Jaikwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 610~615
DOI : 10.5139/JKSAS.2014.42.7.610
Filterbanks have been widely used in the field of multi-channel signal processing for their simple efficient implementation architectures. Especially, the polyphase DFT(Discrete Fourier Transform) filterbank is the most preferred filterbank for the uniform spaced multi-channel processing due to its simplicity. In frequency hopped communication systems, however, the use of the polyphase DFT filterbank is limited due to its undesirable transient response from hop-to-hop transitions. In this paper, the transient response of polyphase DFT filterbanks in the hop-to-hop transition was analyzed, and the efficient methods to overcome such a problem was proposed. Simulation results showed that the proposed schemes could resolve this issue efficiently.
Prediction of Parabolic Antenna Satellite Drag Force in Low Earth Orbit using Direct Simulation Monte Carlo Method
Shin, Somin ; Na, Kyung-Su ; Lee, Juyoung ; Cho, Ki-Dae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 616~621
DOI : 10.5139/JKSAS.2014.42.7.616
Consumption of the fuel on the satellite operating in low earth orbit, is increased due to the air resistance and the amount of increase makes the satellite lifetime decrease or the satellite mass risen. Therefore the prediction of drag force of the satellite is important. In the paper, drag force and drag coefficient analysis of the parabolic antenna satellite in low earth orbit using direct simulation monte carlo method (DSMC) is conducted according to the mission altitude and angle of attack. To verify the DSMC simulated rarefied air movement, Starshine satellite drag coefficient according to the altitude and gas-surface interaction are compared with the flight data. Finally, from the analysis results, it leads to appropriate satellite drag coefficient for orbit lifetime calculation.
Experimental Investigation of Concentrating Photovoltaic System Applying Commercial Multi-array Lens for Space Applications
Park, Tae-Yong ; Chae, Bong-Geon ; Lee, Yong-Geun ; Kang, Suk-Joo ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 7, 2014, Pages 622~627
DOI : 10.5139/JKSAS.2014.42.7.622
A pico-class satellite has limitation to generate power from the solar cells due to its limited accommodation area to install the solar cells. The variation of incidence angle between solar panels and sunlight induced by the revolution and rotation of the satellite is one of the key parameters to determine the power generation. In this study, we proposed a concentrating photovoltaic system for pico-class satellite applications to enhance power generation when the
angle between the sunlight and the solar panel is zero by effectively concentrating solar energy on solar panels. The feasibility of the conceptual idea has been demonstrated by power measurement test using solar simulator and commercial multi-array lens system.