Go to the main menu
Skip to content
Go to bottom
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
Editor in Chief :
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
An Out of Core Linear Direct Solution Method for Large Scale Structural Analysis
Kim, Min-Ki ; Kim, Seung Jo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 445~452
DOI : 10.5139/JKSAS.2014.42.6.445
This paper discusses the multifrontal direct solution method with out of core storage for large scale structural analysis in a limited computing resource. Large scale structural analysis requires huge amount of memory space and computation, so out of core solution method is needed in limited computing resource. In this research, out of core multifrontal solution algorithm which utilize the small size of physical memory and minimize the amount of access of low speed out of core storage is introduced. Three ideas, which are stack space in lower trianglar part of square factorization matrix, inverse stack data structure and selective data caching and recovery by data block size, are proposed.
Performance Analysis of GNSS Ephemeris Fault Detection Algorithm Based on Carrier-Phase Measurement
Ahn, Jongsun ; Jun, Hyang-Sig ; Nam, Gi-Wook ; Yeom, Chan-Hong ; Lee, Young Jae ; Sung, Sangkyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 453~460
DOI : 10.5139/JKSAS.2014.42.6.453
We analyze fault detection algorithm of ephemeris included in navigation message, which is one of the GNSS risk factors. This algorithm uses carrier-phase measurement and baseline vector of two reference stations and is alternative method for uncertainty condition of previous ephemeris. Even though same ephemeris fault is occurred, the geometry condition, between baseline vector of reference stations and satellites, effects on performance of algorithm. Also, we introduce the suitable geometry of reference stations, threshold and performance index (MDE : Minimum Detectable Error) in jeju international airport.
Optimal Positioning of Small UAVs for Communication Relay
Jeong, Junho ; Kim, Seungkeun ; Oh, Hyondong ; Suk, Jinyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 461~467
DOI : 10.5139/JKSAS.2014.42.6.461
This paper investigates using small UAVs as communications relay nodes for expanding communications links and improving communications quality, primarily for a fleet of ground or navy vessels. An airborne relay in ground/maritime space can effectively connect to units operating over the horizon, beyond normal communication range, or under limited satellite communication environment. Even if the equipment development is mature for communications relay, where to locate UAVs for efficient relay is still a pending question. With this background, this paper will develop high-level deployment algorithms to optimize the location of UAVs for improving the connectivity of a wireless network among a fleet of ground or navy vessels.
Initial Climb Mission Analysis of a Solar HALE UAV
Shin, Kyo-Sic ; Hwang, Ho-Yon ; Ahn, Jon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 468~477
DOI : 10.5139/JKSAS.2014.42.6.468
In this research, how a solar powered HALE (high altitude long endurance) UAV (Unmanned Aerial Vehicle) can climb and reach mission altitude, 18km, starting from the ground using only solar energy. A glider type aircraft was assumed as a baseline configuration which has wing area of
and aspect ratio of 25. Configuration parameters, lift and drag coefficients were calculated using OpenVSP and XFLR5 that are NASA open source programs, and climb flights were predicted through energy balance between available energy from solar power and energy necessary for a climb flight. Minimum time climb flight was obtained by minimizing flight velocities at each altitude and total time and total energy consumption to reach the mission altitude were predicted for different take off time. Also, aircraft moving distances due to westerly wind and flight speed were calculated.
Configuration and Performance Analyses for Conceptual Design of Small and Mid-Unmanned Aerial Vehicles
Jeon, Byung-Il ; Lee, Narae ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 478~487
DOI : 10.5139/JKSAS.2014.42.6.478
The simplified performance analysis and initial configuration design are required for the successful development of UAV during the conceptual design, in which empirical formulas and trend equations are utilized for the UAV performance analysis. In the conceptual design phase various UAV configurations may be considered, however, it is very inefficient and unnecessary to consider all configurations for the conceptual design. In this study, the database for the fixed wing UAVs whose MTOW is between 50kg and 1,500kg was also constructed for the selection of configuration frequently used. The parametric analyses were performed for major performance parameters, and trend equations were developed through regression analyses for these individual performance parameters.
A Study on Impact of an Adjacent Structure by a Rocket Plume
Yang, Young-Rok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 488~494
DOI : 10.5139/JKSAS.2014.42.6.488
Rocket Plumes can cause serious damage to launch vehicles and adjacent structures. This paper describes the impact of an adjacent structure by a rocket plume. Each parameter related with dynamic behavior of a missile is modeled with probabilistic distributions of variables. Flyout analyses of initial behavior of a vertically launched missile are performed using Monte-Carlo simulation and flow-motion analyses were conducted by using CFD. In this way, when a missile is fired by a ship, the impact of an adjacent structure by a rocket plume was analyzed.
Status of the Solar Sail Technologies
Cho, Hyeong-Sun ; Kim, Hak-In ; Lee, Soo-Yong ; Roh, Jin-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 495~504
DOI : 10.5139/JKSAS.2014.42.6.495
Solar sail spacecrafts can gain propulsion using the momentum change through reflecting the photon packets of energy from the Sun. The sail slowly but continuously accelerates to accomplish a wide-range of potential missions. To develop the potential mission of the solar sail, the configuration, the film characteristics and the deployment devices should be carefully considered. In this paper, recent development and activities of the solar sail are introduced and design technology of the sail subsystem is investigated.
A Study on the Effects and the Countermeasure of Sea Surface Reflection Waves in Pseudolite Navigation Systems
Park, Jun-Pyo ; Suk, Jinyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 505~514
DOI : 10.5139/JKSAS.2014.42.6.505
The effects of reflected wave of the sea on pseudolite ranging accuracy are analysed in this paper, when a pseudolite navigation system is used for wide area outdoor applications such as aircraft and vessels positioning. Methods for minimizing the influence of sea surface reflection wave were proposed. The methods include the appropriate correlator in pseudolite navigation system through the correlation performance comparison analysis in receiver design, the use of the technology of multiple antennas, and locating the transmitting station antenna on an appropriate position. From the results of experiments, the method of locating the antenna position shows the most reliable performance against the effect of surface reflection wave. The analysis results of the ranging accuracy improvement are addressed, when the multipath caused by sea surface reflection exists.
The Axial-displaced gregorian antenna design using Ray-tracing Method
Kim, Chun-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 515~521
DOI : 10.5139/JKSAS.2014.42.6.515
In this paper, we designed axis-displaced Gregorian antenna by using Ray-tracing method. This antenna improves gain, VSWR by rotating the axis of the sub-reflector to get rid of E-field wave returned from sub-reflector to feed horn. Therefore it reduce the sub-reflector size and the volume of antenna. This method is used to track the propagation path for radiation pattern of feed horn from feed horn to sub-reflector, main-reflector and air. We get E-field distribution of this antenna aperture and calculate antenna radiation pattern and optimize the antenna performance. The Ray-tracing Method was verified because the gain, radiation patterns, side lobe level, beam width and return loss of the designed antenna are very similar to CST simulation result and a measured result of the fabricated antenna.
Development of Cube Satellite`s Communication System Using Commercial UHF Half-Duplex Antenna
Chae, Bong-Geon ; Ha, Heon-Woo ; Jang, Su-Eun ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 522~528
DOI : 10.5139/JKSAS.2014.42.6.522
A UHF/VHF full-duplex communication using monopole and dipole antenna has been widely used for cube satellite applications. This kind of communication system requires a dedicated structure panel for antenna integration, which is the one of the disadvantages of the conventional communication system from the accommodation point of view considering the extremely limited volume of the cube satellite. In this study, to maximize the accommodation efficiency of the cube satellite, the commercial UHF half-duplex antenna combined with buck converter for communication modes transition has been considered in the communication system design. Its effectiveness has been verified through link budget analysis based on the antenna specifications and satellite`s operation conditions. In addition, the antenna deployment mechanism for the synchronous release of multi-antennas has also been introduced.
Performance Verification of Hinge Driving Segmented Nut Type Holding and Release Mechanism for Cube Satellite Applications
Oh, Hyun-Ung ; Lee, Myeong-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 6, 2014, Pages 529~534
DOI : 10.5139/JKSAS.2014.42.6.529
Pyrotechnic devices are widely used for space appendages. However, a cube satellite requirements do not permit the use of explosive pyrotechnic device. A nichrome burn wire release has typically been used for holding and release of deployable appendages of the cube satellite due to its simplicity and low cost. However, relatively low mechanical constraint force and system complexity for application of multi-deployable systems are disadvantages of the conventional mechanism. To overcome these drawbacks, we developed a hinge driving segmented nut type holding and release mechanism based on the nichrome burn wire release. The functional performance of the mechanism has been verified through release function test, static load test and shock level measurement test.