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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
> Journal Vol & Issue
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 44, Issue 9 - Sep 2016
Volume 44, Issue 8 - Aug 2016
Volume 44, Issue 7 - Jul 2016
Volume 44, Issue 6 - Jun 2016
Volume 44, Issue 5 - May 2016
Volume 44, Issue 4 - Apr 2016
Volume 44, Issue 3 - Mar 2016
Volume 44, Issue 2 - Feb 2016
Volume 44, Issue 1 - Jan 2016
Selecting the target year
Numerical Analysis on the Tow Point of Gaori Kite
Sah, Jong-Youb ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 195~202
DOI : 10.5139/JKSAS.2016.44.3.195
There is two popular kites, Bangpae and Gaori. While the Bangpae kite is being widely loved by experts, the Gaori kite is popular for kids and beginners. Three types of Gaori kite product have been survayed on the tow point. The aerodynamic force on Gaori kite is numerically calculated by using Fluent. Through flight simulations at the tow point of each kite type, the new tow point, at which the required minimum velocity is lower than those of existing tow points, has been proposed as a standard. The required minimum velocity is the threshold wind velocity at which the kite begins to fly.
A Feedback-Form of Terminal-Phase Optimal Guidance Law for BTT Missiles Considering Autopilot Dynamics
Yoo, Seong-Jae ; Hong, Jin-Woo ; Ha, In-Joong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 203~211
DOI : 10.5139/JKSAS.2016.44.3.203
In contrast with STT missiles, the guidance law design for BTT missiles should be based on 3-dimensional pursuit kinematics, since the pitch and roll channels of BTT missiles are coupled dynamically. More generally than the prior works, the dynamics of pitch and roll channels, as well as 3-dimensional pursuit kinematics are considered in the design of our terminal-phase optimal guidance law for BTT missiles proposed in this paper. Thereby, the proposed optimal guidance law guarantees high capturability with small miss distance without significant performance degradation due to time-lag effect even in case of relatively slow autopilot dynamics. Moreover, the resulting optimal guidance law is expressed explicitly in feedback-form with the coefficients given as the functions of time-to-go. The effectiveness and practicality of our work is demonstrated through various simulation results.
Development of the S-band receiver for LEO satellite
Park, In-Yong ; Jin, Hyun-Peel ; Lee, Soon-Cheon ; Sirl, Young-wook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 212~217
DOI : 10.5139/JKSAS.2016.44.3.212
The S-band receiver for Low Earth Orbit satellite is designed and fabricated as engineering model. Demodulator is implemented by using FPGA for extension of demodulator method. The receiver consists of RF Block, Digital demodulator and Power stage and has a Doppler tracking function to compensate a frequency shift that occur on the operation. The measured results of fabricated receiver show BER of less than
at -110dBm RF input power and equipped a frequency tracking of
relative to the center frequency. TID test was satisfied with the results of the test criterion is 10krad.
A Study on the Analysis of Visibility between a Lunar Orbiter and Ground Stations for Trans-Lunar Trajectory and Mission Orbit
Choi, Su-Jin ; Kim, In-Kyu ; Moon, Sang-Man ; Kim, Changkyoon ; Rew, Dong-young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 218~227
DOI : 10.5139/JKSAS.2016.44.3.218
Korean government plans to launch a lunar orbiter and a lander to the Moon by 2020. Before launch these two proves, an experimental lunar orbiter will be launched by 2018 to obtain key space technologies for the lunar exploration. Several payloads equipped in experimental lunar orbiter will monitor the surface of the Moon and will gather science data. Lunar orbiter sends telemetry and receives tele-command from ground using S-band while science data is sent to ground stations using X-band when the visibility is available. Korean deep space network will be mainly used for S and X-band communication with lunar orbiter. Deep Space Network or Universal Space Network can also be used for the S-band during trans-lunar phase when korean deep space network is not available and will be used for the S-band in normal mission orbit as a backup. This paper analyzes a visibility condition based on the combination of various ground antennas and its mask angles according to mission scenario to predict the number of contacts per day and to build an operational scenario for the lunar orbiter.
Development and Performance Test of Solar Sail System for CNUSAIL-1 Cube Satellite
Song, Su-A ; Kim, Seungkeun ; Suk, Jinyoung ; Roh, Jin-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 228~239
DOI : 10.5139/JKSAS.2016.44.3.228
CNUSAIL-1 is a 3U-sized cube satellite with
small solar sail which is currently being developed at the Chungnam National University. The primary purpose of the CNUSAIL-1 is successful sail deployment in LEO and its operation for investigating its effect on satellite orbit and attitude as well as performing de-orbiting using the sail membranes as drag sail at the final phase. The system design and mechanism of solar sail deployment is introduced, and optical and tensile tests are carried out for the material of membranes and booms for its safety and performance verification. The ground test is carried out to verify its performance for sail deployment and satellite through comparison between folding methods by determining its folding patterns, thickness of spiral spring and angular velocity measurement in a low-friction environment.
Analysis of effectiveness of solar system internet to deep space exploration
Koo, Cheolhea ; Kim, Changkyun ; Rew, Dongyoung ; Choi, Gihyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 240~246
DOI : 10.5139/JKSAS.2016.44.3.240
The hottest news and achievements of space science and research in recent years may be NASA Curiosity rover`s exploration (2013) of Mars, China Chang`e 3`s exploration (2013) of Moon, ESA Rosetta`s exploration (2014) of Comet 67P/Churyumov-Gerasimenko, and NASA New Horizons` exploration (2015) of Pluto, which are very astonishing achievement since such a deep space journey was possible with current technology. In contrast the wonderful cruise and navigation technologies evolution of explorer in deep space, there are no remarkable changes in deep space data communication, it is still in conservative area, of which much changes are reluctantly accepted so far. But there are some movements of deep space exploration in order to allow ground brilliant technologies to deep space. One of those experiments is internet, whose main topic of this paper. In this paper, we will present the analysis of effectiveness of solar system internet to deep space exploration.
Experimental Study on Unsteady-state Characteristics of a Pintle Thruster with Variable Pintle Speeds
Hwang, Heuiseong ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 247~255
DOI : 10.5139/JKSAS.2016.44.3.247
The purpose of this study is to investigate unsteady-state characteristics of a pintle thruster with various pintle speed. Based on steady state experimental results, non-linear pintle stroke equation is obtained and applied to the unsteady state experimental system. For the unsteady state experiments, three different pintle speeds are used: 3.10 mm/s, 5.65 mm/s, 10.83 mm/s, respectively. Results show that backward pintle stroke results in faster convergence time because of high chamber pressure during backward pintle stroke sequence. During the forward and backward process, thrust curve shows singular points. These phenomenons is caused by variation of mass flow rate, which is mainly due to changes of both chamber pressures and nozzle throat area. This behavior becomes distinctive for a faster pintle speed case.
A Study on Software Based Fault-Tolerance Techniques for Flight Control Computer
Yoon, Hyung-Sik ; Kim, Yeon-Gyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 256~265
DOI : 10.5139/JKSAS.2016.44.3.256
Software based fault tolerance techniques are designed to allow a system to tolerate software faults in the system. Fault tolerance techniques are divided into two groups : software based fault tolerance techniques and hardware based fault tolerance techniques. We need a proper design method according to characteristics of the system. In this paper, the concepts of software based fault tolerance techniques for Dual Flight Control Computer are described. For software based fault tolerance design, we classified software failure, designed a way for failure detection and the way of recovery. Eventually the effectiveness of software based fault tolerance techniques was verified through the Software Test Environment(STE).
Research of the Signal Processing techniques applied to the Command Link Receiver of High Speed Aircrafts
Yun, Jung-Kug ; Jung, Won-Hee ; Kim, Kyun-Hoe ; Yun, Myung-Han ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 266~273
DOI : 10.5139/JKSAS.2016.44.3.266
In this paper, we propose the signal processing techniques for the command link receiver mounted to aircrafts flying at a high speed. In order to acquire the various information transmitted from ground through radio frequency links, the wide received signal range must be guaranteed as well as the carrier synchronization and symbol synchronization be performed correctly within short pulse sections. After the synchronization step, we should be able to achieve theoretical performance of the modulation and demodulation scheme applied as deciding bit and symbol at the time appointed. By test results, we make sure that the proposed signal processing techniques can be effectively applied command link receiver mounted to aircrafts.
Launch and On-orbit Environment Verification Test of Flight Model of Hinge Driving Type Holding and Release Mechanism based on the Burn Wire Release
Lee, Myeong-Jae ; Lee, Yong-Keun ; Kang, Suk-Joo ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 3, 2016, Pages 274~280
DOI : 10.5139/JKSAS.2016.44.3.274
Hinge driving type holding and release mechanism based on the burn wire release for application of cubesat is main payload of STEP Cube Lab. (Cube Laboratory for Space Technology Experimental Project) to be launched at 2015. It has high constraint force, low shock level as well as surmounting drawbacks of conventional nichrome burn wire release method that has relatively low constraint force and system complexity for application of multi-deployable systems. In this paper, we have proposed a flight model of holding and release mechanism for the verification of the constraint force and deployment status signal acquisition. To validate the effectiveness of the flight model, launch and on-orbit environment verification test have been performed.