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 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
The Strain Corrections for Accuracy Improvement to Predict Large Deformation of Wings
Lee, Hansol ; Kim, In-Gul ; Park, Sunghyun ; Kim, Min-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 1~11
DOI : 10.5139/JKSAS.2016.44.1.1
The information about the deformations of high-aspect-ratio wings is needed for the real-time monitoring of structural responses. Wing deformation in flight can be predicted by using relationship between the curvatures and the strains on the wing skin. It is also necessary to consider geometric nonlinearity when the large deformation of wing is occurred. The strain distribution on fixed-end is complex in the chordwise direction because of the geometric shape of fixed-wings on fuselages. Hence, the wing displacement can be diversely predicted by the location of the strain sensing lines in the chordwise direction. We conducted a study about prediction method of displacements regardless of the chordwise strain sensing locations. To correct spanwise strains, the ratio of spanwise strain to chordwise strain, Poisson's ratio, and the ratio of the plate strain to the beam strain were used. The predicted displacements using the strain correction were consistent with those calculated by the FEA and verified through the bending testing.
Performance Analysis of Landing Point Designation Technique Based on Relative Distance to Hazard for Lunar Lander
Lee, Choong-Min ; Park, Young-Bum ; Park, Chan-Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 12~22
DOI : 10.5139/JKSAS.2016.44.1.12
Lidar-based hazard avoidance landing system for lunar lander calculates hazard cost with respect to the desired local landing area in order to identify hazard and designate safe landing point where the cost is minimum basically using slope and roughness of the landing area. In this case, if the parameters are only considered, chosen landing target can be designated near hazard threatening the lander. In order to solve this problem and select optimal safe landing point, hazard cost based on relative distance to hazard should not be considered as well as cost based on terrain parameters. In this paper, the effect of hazard cost based on relative distance to hazard on safe landing performance was analyzed and it was confirmed that landing site designation with two relative distances to hazard results in the best safe landing performance by an experiment using three-dimensional depth camera.
Key Parameters and Research Review on Counterflow Jet Study in USA for Drag Reduction of a High-speed Vehicle
Kim, Jihong ; Kang, Seungwon ; Lee, Jaecheong ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 23~32
DOI : 10.5139/JKSAS.2016.44.1.23
Various studies have been conducted for drag reduction of a high-speed vehicle by injecting counterflow jet from its nose cone. In this study, in order to obtain baseline data and key parameters for drag reduction method, the counterflow jet study of the USA is reviewed and summarized. The nose cone shapes of each study are hemisphere cylinder, truncated cone, and reentry capsule, and their test conditions are summarized accordingly. Key parameters for drag reduction are jet mach number, mass flow rate, and pressure ratio. Even though drag reduction effects show various results according to given test conditions, it is found that the drag reduction effect reaches up to 40~50%.
Analysis and dehazing of near-infrared images
Yu, Jae Taeg ; Ra, Sung Woong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 33~39
DOI : 10.5139/JKSAS.2016.44.1.33
Color image dehazing techniques have been extensively studied, and especially the dark channel prior (DCP)-based method has been widely used. Near infrared (NIR) image based applications are also widespread; however, NIR image-specific dehazing techniques have not attracted great interest. In this paper, the characteristics of NIR images are analyzed and compared with the color images' characteristics. The conventional color image dehazing method is also applied to NIR images to understand its effectiveness on different frequency-band signals. Furthermore, we modify the DCP method considering the characteristics of NIR images and show that our proposed method results in improved dehazed NIR images.
Experimental Investigation of Complex System for Electrical Energy Harvesting and Vibration Isolation
Kwon, Seong-Cheol ; Jeon, Su-Hyeon ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 40~48
DOI : 10.5139/JKSAS.2016.44.1.40
Micro-vibration induced by on-board appendages that have mechanical moving parts has always been treated as an useless objective that has to be isolated, in order to comply with a high-resolution mission requirement of the observation satellite. In this study, we proposed a tuned mass damper energy harvester combined with a conventional passive vibration isolator for exhibiting dual functions of both electrical energy harvesting and micro-vibration isolation. The feasibility of the proposed dual-function complex system has been demonstrated through the comparison with numerical simulations, based on the results of basic characteristic tests, and experiments of the harvested power and micro-vibration.
A Study on Winter Season Usability Performance Improvement of Flapper Valve for KUH-1
Choi, Jae Hyung ; Chang, In ki ; Shim, Dai Sung ; Ahn, Jeong Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 49~56
DOI : 10.5139/JKSAS.2016.44.1.49
Flapper Valve of Korean Utility Helicopter(KUH-1) is an essential equipment in Environmental Control System(ECS) for pilot to perform flight mission. It provides pilots and crews with heating, ventilating and air conditioning. It has function of maintaining room temperature to sustain operational capability for pilot and crew. This paper summarizes pilot comments in flight test which are classified by cause of occurrence and the troubleshooting process about each comment. It also describes design improvements which was derived from troubleshooting and suggests verification results of flight test at low temperature.
Comparison Study of H-infinity Controller Design Algorithms for Spacecraft Attitude Control
Rhee, Seung-Wu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 57~69
DOI : 10.5139/JKSAS.2016.44.1.57
There are three kinds of algorithms(2-ARE, mu-synthesis, LMI) for controller design using closed-loop shaping method. This paper provides the summary of background theory of three algorithms and
controller design results for spacecraft attitude control using the three controller design tools of Matlab
Toolbox for comparison. As a result, it reveals that LMI design method is more reliable as well as easier than others for spacecraft attitude control design. Comparison results are as follow: 2-ARE method and LMI method provide almost same results in robust stability, robust performance and control authority level. But 2-ARE method is more sensitive than LMI method with respect to proper design of weighting functions: 2-ARE method is more difficult than LMI method in weighting function design. The design result of mu-synthesis method shows worse performance and requires bigger control authority than others.
Performance Evaluation of Thermal Control Subsystem of EOS-D Ver.1.0 from In-orbit Telemetry Data
Chang, Jin-Soo ; Kim, Jong-Un ; Kang, Myung-Seok ; Kim, Ee-Eul ; Yang, Seung-Uk ; An, Su-Mi ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 70~79
DOI : 10.5139/JKSAS.2016.44.1.70
Satrec Initiative successfully developed a high-resolution electro-optical camera system, EOS-D Ver.1.0. EOS-D Ver.1.0 is the main payload of DubaiSat-2 and Deimos-2, which are developed based on the SI-300 platform of Satrec Initiative. After the launch and early operation (LEOP) of DubaiSat-2 and Deimos-2, we performed refocusing for the telescope of EOS-D Ver.1.0 to compensate for the dimensional change of its metering structure by moisture out-gassing. Before and after refocusing, we conducted the performance evaluation of thermal control system(TCS) for EOS-D Ver.1.0 using the in-orbit telemetry data. The evaluation showed EOS-D Ver.1.0 was under well-controlled thermal environment, which demonstrates TCS was designed and developed to meet all requirements.
Thermal pointing error analysis of the observation satellites with interpolated temperature based on PAT method
Lim, Jae Hyuk ; Kim, Sun-Won ; Kim, Jeong-Hoon ; Kim, Chang-Ho ; Jun, Hyoung-Yoll ; Oh, Hyeon Cheol ; Shin, Chang Min ; Lee, Byung Chai ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 80~87
DOI : 10.5139/JKSAS.2016.44.1.80
In this work, we conduct a thermal pointing error analysis of the observation satellites considering seasonal and daily temperature variation with interpolated temperature based on prescribed average temperature (PAT) method. Maximum 200 degree temperature excursion is applied to the observation satellites during on-orbit operation, which cause the line of sight (LOS) to deviate from the designated pointing direction due to thermo-elastic deformation. To predict and adjust such deviation, the thermo-elastic deformation analysis with a fine structural finite element model is accomplished with interpolated thermal maps calculated from the results of on-station thermal analysis with a coarse thermal model. After verifying the interpolated temperatures by PAT with two benchmark problems, we evaluate the thermal pointing error.
Design and Performance Test of a Closed Loop Thermal Control System for Thermal Vacuum Chamber
Seo, Heejun ; Cho, Hyokjin ; Park, Sungwook ; Moon, Gueewon ; Jung, Sanghun ; Huh, Hwanil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 1, 2016, Pages 88~97
DOI : 10.5139/JKSAS.2016.44.1.88
A closed loop thermal control system simulates space thermal environment to verify the satellites' functionality in extremely cold/hot temperature. It is composed of a cryogenic blower, thermal shroud, heater, cryogenic valves. This paper presents an overview of closed loop thermal control system's design parameter and test results for control parameter. A capacity of blower is calculated through energy balance equation and an advantage/disadvantage for a shroud material and a type was analysed. The thermal control system is controlled by a constant density of fluid in the system. A requested performance of closed loop thermal control system was verified by measuring a homogeneity and stability of shroud through control parameter such as density and RPM of blower.