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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
Effects of opening distance on liquid-gas spray of pintle injector under atmospheric condition
Yu, Kijeong ; Son, Min ; Koo, Jaye ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 585~592
DOI : 10.5139/JKSAS.2015.43.7.585
Effects of opening distance on liquid-gas spray of pintle injector were experimentally investigated under atmospheric condition by using water and air as simulants of propellants. Discharge coefficients(
) and mass flow rates were calculated with various injection conditions; 0.1 bar - 1.0 bar for water pressures and 0.2 mm - 1.0 mm for the pintle opening distances. Spray angles were measured from the spray images that were obtained by a shadowgraphy method. When opening distance is 0.2 mm, liquid sheet is not formed properly and it show non-uniform spray. than it can result in combustion instability. it has a weak correlation between the momentum flux ratio and the spray angle, while it has a strong correlation between the momentum ratio and spray angle. Finally the spray angles reduced exponentially when the momentum ratio increased and the spray angles converged to about 40 degrees.
Fuel-Rich Combustion Characteristic of a Combined Gas Generator
Lee, Dongeun ; Lee, Changjin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 593~600
DOI : 10.5139/JKSAS.2015.43.7.593
In this study, a combined hybrid rocket system is newly introduced which has characteristics of both gas generators and afterburner type hybrid rockets. In particular, a combined gas generator utilizing solid fuel and liquid/gas oxidizer was designed as a primary combustor of the system. Combustion tests were carried out with various equivalence ratio affected by parameters such as fuel length, oxidizer flow rate, fuel port diameter and fuel type. In general, fuel-rich gas generator produces low combustion gas temperature to meet the temperature requirement and the target temperature was transiently set less than 1600 K. Since it was found that controlling parameters showed limited effects on the change of equivalence ratio, mixture of
as an oxidizer was additionally introduced. As a result, a combined gas generator successfully produced combustion gas temperature of less than 1600 K Future studies will carry out more combustion tests to attain fuel-rich combustion gas temperature less than 1200 K, which was a temperature requirement of a gas generator system in the previous studies.
Multi-Objective Optimization of Flexible Wing using Multidisciplinary Design Optimization System of Aero-Non Linear Structure Interaction based on Support Vector Regression
Choi, Won ; Park, Chan-Woo ; Jung, Sung-Ki ; Park, Hyun-Bum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 601~608
DOI : 10.5139/JKSAS.2015.43.7.601
The static aeroelastic analysis and optimization of flexible wings are conducted for steady state conditions while both aerodynamic and structural parameters can be used as optimization variables. The system of multidisciplinary design optimization as a robust methodology to couple commercial codes for a static aeroelastic optimization purpose to yield a convenient adaptation to engineering applications is developed. Aspect ratio, taper ratio, sweepback angle are chosen as optimization variables and the skin thickness of the wing. The real-coded adaptive range multi-objective genetic algorithm code, which represents the global multi-objective optimization algorithm, was used to control the optimization process. The support vector regression(SVR) is applied for optimization, in order to reduce the time of computation. For this multi-objective design optimization problem, numerical results show that several useful Pareto optimal designs exist for the flexible wing.
Attitude Determination Algorithm Design and Performance Analysis for CNUSAIL-1 Cube Satellite
Kim, Gyeonghun ; Kim, Seungkeun ; Suk, Jinyong ; Kim, Jong-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 609~618
DOI : 10.5139/JKSAS.2015.43.7.609
This paper discusses the attitude determination of the CNUSAIL-1 cube-satellite. The primary mission of the CNUSAIL-1 is sail deployment and operation in low Earth orbit, and the secondary mission is to look into influence of the sail deployment on satellite attitude and orbit. The attitude determination strategy is proposed depending on three mission phases, and its performance and applicability are verified through numerical simulations. This study considers the following sensors: Sun sensors and a three-axis magnetometer as attitude reference sensors, and a three-axis MEMS gyroscope as an inertial attitude sensor. Because sensors used for cube satellites have relatively low performances and worse noise characteristics, an Extended Kalman filter (EKF) is applied to attitude determination. Additionally, it has the merits to deal with the Gaussian noises and to predict the attitude even with no measurements from reference attitude sensors, especially in the eclipse of the cube satellite. The performance of the EKF is compared to a deterministic attitude determination technique, QUEST(QUaternion ESTimation).
Study on the Dynamic Characteristics of Open Type Swirl Injector with Varyng Swirl Chamber Geometry
Kim, Hyuntae ; Chung, Yunjae ; Jeong, Seokkyu ; Yoon, Youngbin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 619~625
DOI : 10.5139/JKSAS.2015.43.7.619
Swirl injectors are widely used for Liquid Rocket Engine(LRE) as fuel injection system and following researches are also being carried out throughout the world. Especially, solving combustion instability problem is essential for every type of LREs. In this study, cold test was carried out for open type swirl injector as a fundamental research to solve combustion instability problem. Pressure fluctuation was applied to the inlet flow coming into the injector and the following response characteristics were observed. The effect of swirl chamber geometry was also studied by changing both swirl chamber length and diameter.
Application of Radiation Databases for the Prediction of CO
Nam, Hyun Jae ; Kwon, Oh Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 626~634
DOI : 10.5139/JKSAS.2015.43.7.626
In the present study, numerical predictions of infrared spectra for
molecule were conducted. Absorption coefficients of
which are required for simulating the spectra, were calculated by using a line-by-line method and by adopting spectroscopic parameters from the radiation databases, HITEMP2010 and CDSD-4000. Simulations were made in the 2.7, 4.3, and
band regions, and the results were compared with the measurements of other researchers. It was found that the calculated results are well matched with the various measurements. However, in the
band region, the CDSD-4000 based calculation yields a better fit to the measurement than the HITEMP2010 based calculation does.
Performance evaluation on the separation device activated by shape memory alloy actuator
Choi, Junwoo ; Lee, Dongkyu ; Hwang, Kukha ; Lee, Minhyung ; Kim, Byungkyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 635~640
DOI : 10.5139/JKSAS.2015.43.7.635
In this paper, we report a non-explosive separation device for a small satellite which utilize a shape memory alloy actuator. Based on previous research, we try to increase the reliability of the proposed device by changing some components. It enables the proposed device to activate under high preload. Also, we confirm it generates low shock which is main advantage of non-explosive separation device. Finally, vibration test which mimics launching environment and thermal vacuum test which mimics space environment are carried out respectively. After each environment test, we confirm the proposed device is successfully activated. Conclusively, we develop a non-explosive separation device which can activate with low shock under high preload after shock and environment tests(vibration and thermal vacuum tests).
A Study of multi-channel signal processing algorithm suitable for Digital-transponder
Lee, Jung-sub ; Hong, Keun-pyo ; Jin, Byoung-il ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 641~647
DOI : 10.5139/JKSAS.2015.43.7.641
In this paper, Analyzed the multi-channel signal processing algorithms for digital-transponder. To analyze suitable multi-channel signal processing algorithms, compare algorithms about four criteria. Four criteria are as follows, perfect reconstruction, interference rejection, resource usage and power consumption. Analysis for each algorithm in accordance with these four criteria. then propose the multi-channel signal processing algorithms for digital satellite communication system.
A Study on Active SAR Satellite Maneuver Time Reduction through Sequential Rotation
Son, Jun-Won ; Park, Young-Woong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 648~656
DOI : 10.5139/JKSAS.2015.43.7.648
Active SAR satellite`s main maneuver is roll axis maneuver to change SAR antenna direction. In addition, yaw steering is required to minimize the doppler centroid variation. Thus, it is resonable to assign the torque/momentum capacity mostly to roll axis and then yaw axis. In this case, the pitch axis shows low agility performance. However, due to orbit maintenance, large angle maneuver about pitch axis is sometimes required. In this paper, we study the pitch axis maneuver time reduction through sequential rotation about roll and yaw axis. Since these two axes have high agility performance than pitch axis, maneuver time reduction is possible when large angle rotation about pitch axis is required.
A Study of Civil Unmanned Aerial System Category Classification
Ahn, Hyojung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 7, 2015, Pages 657~667
DOI : 10.5139/JKSAS.2015.43.7.657
With development of technology and increase of commercial demand for unmanned aerial system(UAS), the related regulation has been prepared and complemented with the advanced countries such as Unite States and European Union(EU). However it is difficult for regulation to cover all areas of UASs practically since UASs have been developed in a variety of configurations and performance depending on their purpose. Therefore the reasonable criteria for the classification of UASs and their category should be suggested before development of the regulation. For this reason, many countries have been studying the standard for UASs classification and International Civil Aviation Organization(ICAO) makes an effort to prepare the international standards. In this paper, the new classification scheme which can complement domestic regulation is suggested based on investigation of the global trend of UAS classification and their researches.