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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 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
Selecting the target year
Experimental Investigations of Systematic Errors in Wind Tunnel Testing Using Design of Experiments
Oh, Se-Yoon ; Park, Seung-O ; Ahn, Seung-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 335~341
DOI : 10.5139/JKSAS.2013.41.5.335
The variation of systematic bias errors in the wind tunnel testing has been studied. A Design of Experiments(DOE) approach to an experimental study of fuselage drag and stability characteristics of a helicopter configuration was applied. When forces and moments measured in one time block differ significantly from measurements made in another time block under assumption that sample observations can be expected to yield same results within permissible measuring errors. The practical implication of this paper is that the systematic error can not be assumed not to exist. The those error reduction could be achieved through the process of randomization, blocking, and replication of the data points.
Neural Network Based Adaptive Control for a Flying-Wing Type UAV with Wing Damage
Kim, DaeHyuk ; Kim, Nakwan ; Suk, Jinyoung ; Kim, Byungsoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 342~349
DOI : 10.5139/JKSAS.2013.41.5.342
A damage imposed on an unmanned aerial vehicle changes the flight dynamic characteristics, and makes difficult for a conventional controller based on undamaged dynamics to stabilize the vehicle with damage. This paper presents a neural network based adaptive control method that guarantees stable control performance for an unmanned aerial vehicle even with damage on the main wing. Additionally, Pseudo Control Hedging (PCH) is combined to prevent control performance degradation by actuator characteristics. Asymmetric dynamic equations for an aircraft are chosen to describe motions of a vehicle with damage. Aerodynamic data from wind tunnel test for an undamaged model and a damaged model are used for numerical validation of the proposed control method. The numerical simulation has shown that the proposed control method has robust control performance in the presence of wing damage.
Error Quantification of Photogrammetric 6DOF Pose Estimation
Kim, Sang-Jin ; You, Heung-Cheol ; Reu, Taekyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 350~356
DOI : 10.5139/JKSAS.2013.41.5.350
Photogrammetry has been widely used for measuring the important physical quantities in aerospace areas because it is a remote and non-contact measurement method. In this study, we analyzed photogrammetric error which can be occur in six degrees of freedom(6DOF) analysis among coordinates systems with single camera. Error analysis program were developed, and validated using geometric problem converted from imaging process. We analogized that the statistic from estimated camera pose which is need to 6DOF analysis is normally distributed, and quantified the photogrammetric error using estimated population standard deviation.
An Experimental Study of Aerodynamic Characteristics on a Projectile with Counter-Rotating Head Installed Fins
Park, Young-Ha ; Je, Sang-Eon ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 357~365
DOI : 10.5139/JKSAS.2013.41.5.357
In this study, forces and moments were measured on a projectile which consisted of a missile configuration body(shell) and a head installed control fins. The shell and the head were separated each other and the shell was rotated by an electric motor. The head rotated reversely against the rotational direction of the shell. The rotational force on the head was obtained from a couple of fixed fins of which angular displacement were set to the rotational direction equally. The air velocity was 40m/s on the experiment and the Reynolds number based on the diameter of head was
. The other couple of fins were used to control the position and direction of the projectile by changing the angular displacement. From this experiment, the variation of force and moment were measured on the rotating projectile, and the effective amplitude and frequency were obtained through the FFT analysis.
Design of a Structural Model for Korean Lunar Explorer
Son, Taek-Joon ; Na, Kyung-Su ; Kim, Jong-Woo ; Lim, Jae Hyuk ; Kim, Kyung-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 366~372
DOI : 10.5139/JKSAS.2013.41.5.366
Korean lunar explorer will be launched by korean launcher KSLV-2 in the 2020s in accordance with national space development strategy. Korean lunar explorer is composed of two unmanned orbiter and lander and should be developed as small size and light weight within 550kg of launch mass due to launcher`s loading capability. A structure of lunar explorer is required to have sufficient stiffness and strength under launch and operational environment as well as to accommodate mission equipment. This paper describes the result of a preliminary study on structural model design for korean lunar explorer.
Development of Engagement Simulation Program between ASM with IIR Seeker and Defense System
Park, Sang-Sup ; Kim, Do-Wan ; Choi, Kee-Young ; Kim, Jung-Ho ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 373~382
DOI : 10.5139/JKSAS.2013.41.5.373
In this paper, in order to analyze the performance of a decoy system for ship defense against an anti-ship missile(ASM) with an infrared image(IIR) seeker, the modeling and engagement simulation program is introduced. The IIR seeker on the ASM detects the infrared signal of ship from a distance and approaches the ship based on proportional navigation guidance(PNG) or impact angle control guidance(IACG). Hence the guidance performance of the ASM is basically depend on the target tracking algorithm of the seeker as well as the infrared signal of the ship. Using the developed program, we can investigate the effect of the ship decoy system such as flares and surface cooling system of the ship with respect to various kinds of tracking algorithms of the IIR seeker of the ASM.
Research on the Ejection Gas Generator to Improve Ejecting Performance
Oh, Seok-Jin ; Jang, Seung-Gyo ; Cha, Hong-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 383~390
DOI : 10.5139/JKSAS.2013.41.5.383
The reduction of the maximum acceleration which causes shock for a missile is very important to prevent abnormal operation of a missile and decrease size and cost of missile components. Because the maximum acceleration created by operation of an ejection gas generator occurs in the initial ejection stage, the design parameters which affect initial ejection stage were examined. The igniter and the nozzle closure were selected as design parameters of a gas generator. The maximum acceleration created by the gas generator was examined experimentally by changing of the design parameters. Finally the reduction effect of the maximum acceleration was compared quantitatively by static fire test of a gas generator. The maximum acceleration of the best model which was applied to each optimal design parameter was about 68% reduced than that of the reference model.
Initial Sizing of General Aviation Aircraft Propelled by Electric Propulsion system
Han, Hye-Sun ; Shin, Kyo-Sic ; Park, Hong-Ju ; Hwang, Ho-Yon ; Nam, Taewoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 391~403
DOI : 10.5139/JKSAS.2013.41.5.391
Propeller aircraft propelled by an electric propulsion system is gaining a renewed interest because of ever-increasing environmental concern on harmful emissions emitted from conventional jet engines and national energy security. Traditional aircraft sizing methods are not readily applicable to electric propulsion aircraft that utilize a variety of alternative energy sources and power generation systems. This study showcases an electric propulsion aircraft sizing exercise based on a generalized, power based sizing method. A general aviation aircraft is propelled by an electric propulsion system that comprises of a propeller, a high temperature super conducting motor, a Proton Exchange Membrance(PEM) fuel cell system fuelled with hydrogen, and power conditioning equipment. In order to assess the impact of technology progression, aircraft sizing was conducted for two different sets of technology assumptions for electric components, and the results were compared with conventional baseline aircraft.
The Development of Performance Analysis Code for Conceptual Design of Jet Fighters
Kim, Taewoo ; Choi, Hyunmin ; Choi, Byungryul ; Lee, Sungjin ; Nam, Hwajin ; Choi, Donghoon ; Cho, Jinsoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 404~414
DOI : 10.5139/JKSAS.2013.41.5.404
In the conceptual design phase of jet fighters, the trade study is performed repeatedly for a selection of the baseline configuration. The automation of repeated trade study makes possible to select efficiently the baseline configuration. In this study, the performance analysis code was developed for the automation of trade study. The code was consists of the module of shape generation, the module of weight estimation, the module of mission performance analysis. 3D CAD Model can be generated by the module of shape generation and Weight can be estimated by using the empirical equation in the module of weight estimation. The module of mission performance analysis was able to calculate the mission performance about the arbitrary mission profile. In addition, the optimal mission performance can be calculated by using optimization method. By performing the validation, the code was confirmed to be able to apply to the conceptual design phase.
Improvement of Manufacturing Process for KUH by Applying new equipment
Kim, Young-Jin ; Park, Cha-Hwan ; Kim, Hong-Joo ; Shim, Han-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 415~421
DOI : 10.5139/JKSAS.2013.41.5.415
This paper contains a review of problems in the localized blade manufacturing process through KUH program and research for improvement of it. Contrary to development, mass production needs reliable process due to the long period of supply. The main process of blade manufacturing(Lay-Up, Curing) accepts new equipment(Robot, Heatmold) for improvement of it. And then, the evaluation is performed. Additionally, it is proven that blade which is made by the new process is suitable for mass production by conducting a performance test in the development phase.
A Distance Measurement System Using a Laser Pointer and a Monocular Vision Sensor
Jeon, Yeongsan ; Park, Jungkeun ; Kang, Taesam ; Lee, Jeong-Oog ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 5, 2013, Pages 422~428
DOI : 10.5139/JKSAS.2013.41.5.422
Recently, many unmanned aerial vehicle (UAV) studies have focused on small UAVs, because they are cost effective and suitable in dangerous indoor environments where human entry is limited. Map building through distance measurement is a key technology for the autonomous flight of small UAVs. In many researches for unmanned systems, distance could be measured by using laser range finders or stereo vision sensors. Even though a laser range finder provides accurate distance measurements, it has a disadvantage of high cost. Calculating the distance using a stereo vision sensor is straightforward. However, the sensor is large and heavy, which is not suitable for small UAVs with limited payload. This paper suggests a low-cost distance measurement system using a laser pointer and a monocular vision sensor. A method to measure distance using the suggested system is explained and some experiments on map building are conducted with these distance measurements. The experimental results are compared to the actual data and the reliability of the suggested system is verified.