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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
Editor in Chief :
Volume & Issues
Volume 40, Issue 12 - Dec 2012
Volume 40, Issue 11 - Nov 2012
Volume 40, Issue 10 - Oct 2012
Volume 40, Issue 9 - Sep 2012
Volume 40, Issue 8 - Aug 2012
Volume 40, Issue 7 - Jul 2012
Volume 40, Issue 6 - Jun 2012
Volume 40, Issue 5 - May 2012
Volume 40, Issue 4 - Apr 2012
Volume 40, Issue 3 - Mar 2012
Volume 40, Issue 2 - Feb 2012
Volume 40, Issue 1 - Jan 2012
Selecting the target year
Performance Analysis of Autorotation(1) : Analysis Method and the Effect of Aerodynamic table
Kim, Hak-Yoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 1~11
DOI : 10.5139/JKSAS.2012.40.1.1
Performance analysis was performed for an autorotating rotor. For a given airspeed, shaft angle, and collective pitch, the steady state of autorotation was judged by using the transient simulation method(TSM), then the thrust, lift, and drag coefficient for that state were computed. Average thrust was calculated from the instantaneous thrusts, in which the TSM was used in blade thrust integration. The analysis method was applied to the model rotor that had been tested by wind tunnel. Some comparison between analysis and test was provided. Two types of two-dimensional airfoil aerodynamic data were utilized in analysis, and they were made by Navier-Stokes Solver in terms of Reynolds and Reynolds-Mach number. The quantitative difference of results using two data set was examined and compared.
Performance Analysis of Autorotation(2) : Performance of High Speed Autorotaion
Kim, Hak-Yoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 12~22
DOI : 10.5139/JKSAS.2012.40.1.12
Performance variation of autorotating rotor was investigated. The shaft angle of the rotor is reduced while the flight velocity is increased. The BO-105 helicopter rotor blade was replaced by untwisted NACA 0012 airfoil and the rotor was simulated by using Transient Simulation Method(TSM) to judge the autorotation region for the variables. To simulate the compressibility effect at high speed flight, two-dimensional aerodynamic data was analyzed by compressible Navier-Stokes solver and Pitt/Peters inflow theory was adopted to simulate the induced velocity field. Thrust and lift coefficients, lift to drag ratio variations were investigated, also the lift and power were compared to those of BO-105 helicopter. Sharing lift and power between the autorotating rotor and wing was considered when the compound aircraft concept is introduced.
A Study on Impact Point Prediction of a Reentry Vehicle using Integrated Track Splitting Filters in a Cluttered Environment
Moon, Kyung-Rok ; Kim, Tae-Han ; Song, Taek-Lyul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 23~34
DOI : 10.5139/JKSAS.2012.40.1.23
Space launch vehicles are designed to fly according to the elaborate pre-determined path. However, if a vehicle went out of the planned trajectory or its thrust terminated abnormally, or if a free-fall atmospheric reentry vehicle tracked by a tracking sensor became impossible to be measured, it is required to attempt to track by a another track equipment or estimate its impact point rapidly. In this paper a new algorithm is proposed, named the ITS-EKF combined with the Integrated Track Splitting (ITS) algorithm and the Extended Kalman Filter (EKF) to obtain the location information of a ballistic projectile without thrust, create its track and maintain it in an environment with clutter. For the reentry vehicle, the track performance is to be verified and the impact point is estimated by applying the simulation through ITS-EKF algorithm. To ensure the proposed algorithm`s adequacy, by comparing the track performance and impact point distribution by the ITS-EKF with those of ITS-PF combined with ITS and Particle Filter (PF), it is confirmed that the ITS-EKF algorithm can be used an effective real-time On-line impact point prediction.
Particle Filter Based Feature Points Tracking for Vision Based Navigation System
Won, Dae-Hee ; Sung, Sang-Kyung ; Lee, Young-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 35~42
DOI : 10.5139/JKSAS.2012.40.1.35
In this study, a feature-points-tracking algorithm is suggested using a particle filter for vision based navigation system. By applying a dynamic model of the feature point, the tracking performance is increased in high dynamic condition, whereas a conventional KLT (Kanade-Lucas-Tomasi) cannot give a solution. Futhermore, the particle filter is introduced to cope with irregular characteristics of vision data. Post-processing of recorded vision data shows that the tracking performance of suggested algorithm is more robust than that of KLT in high dynamic condition.
Inertial Sensor Aided Motion Deblurring for Strapdown Image Seekers
Kim, Ki-Seung ; Ra, Sung-Woong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 43~48
DOI : 10.5139/JKSAS.2012.40.1.43
This paper proposes a practical linear recursive robust motion deblurring filter using the inertial sensor measurements for strapdown image seekers. The angular rate information obtained from the gyro mounted on the missile is used to define the PSF(point spread function). Since the gyro output contains a unknown but bounded bias error. the motion blur image model can be expressed as the linear uncertain system. In consequence, the motion deblurring problem can be cast into the robust Kalman filtering which provides reliable state estimates even in the presence of the parametric uncertainty due to the gyro bias. Through the computer simulations using the actual IR scenes, it is verified that the proposed algorithm guarantees the robust motion deblurring performance.
A study on the image formation system variable and performance analysis for optimum design of high resolution SAR
Kwak, Jun-Young ; Jeong, Dae-Gwon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 49~60
DOI : 10.5139/JKSAS.2012.40.1.49
Synthetic aperture radar (SAR) has been employed in various fields due to its capability to generate high resolution images regardless of weather and visibility. This paper presents a performance analysis on the image formation of high resolution SAR according to various slant range distance and synthetic aperture lengths using a range migration algorithm simulator. Although the visual performance on the SAR image is more accurate, a numeric analysis resulted in a comparable measurement. More specifically, raw data were generated for an ideal point target upon imaging geometries and design parameters such as slant range distance and synthetic aperture lengths. Finally, spatial resolution, peak to sidelobe ratio and integrated sidelobe ratio are drawn to provide SAR capabilities in the initial concept design, final in-flight calibration and validation stages.
The Study of analysis and test for crash survival about the Crash Protected Module in Black Box used at aircraft
Lee, Sock-Kyu ; Lee, Byoung-Ho ; Choi, Ji-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 61~68
DOI : 10.5139/JKSAS.2012.40.1.61
The purpose of Crash Protected Module in Black Box used at aircraft is to protect a stored information(Flight data & Cockpit Voice) safely even after extreme environment like a plane crash. This study shows the structure & thermal analyses and the comparisons of predictions and results of tests about CPM for Crash Survival through extreme environment such as Penetration Resistance, High Temperature Fire, Low Temperature Fire. Specially, the Effect of housing thickness change was studied through the Penetration Resistance analysis using LS-DYNA, and the influence of volume ratio change between phase change material and thermal insulation material was studied through the High Temperature & Low Temperature analysis using Icepak. Also, structural and thermal reliability of CPM was validated through the tests.
Analysis of Delta-V of Earth-Moon Transfer Trajectories for Minimization of Fuel Consumption
Kang, Sang-Wook ; Ju, Gwang-Hyeok ; Rew, Dong-Young ; Lee, Sang-Ryool ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 69~77
DOI : 10.5139/JKSAS.2011.40.1.69
After lunar explorations were restarted in 1990s, the world space advanced countries have been competing actively to preoccupy the Moon from the 2000s. Korea has been also conducting precedent study on lunar exploration to carry out that by ourselves in 2020. This study analyzed delta-V of various Earth-Moon transfer trajectories for minimization of fuel consumption. Through the simulation, the best Earth-Moon transfer trajectory for Korean lunar mission is suggested and it will be used as useful materials of Korean lunar mission.
Statistical Conjunction Analysis between KOMPSAT-2 and Space Debris
Jung, In-Sik ; Choi, Su-Jin ; Chung, Dae-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 78~85
DOI : 10.5139/JKSAS.2012.40.1.78
Space debris is the collection of objects in orbit around the Earth that were created by humans but no longer serve any useful purpose. Since the beginning of spacecraft launch in 1957, the number of space debris has been increasing. According to USSTRATCOM, the number of space debris which were bigger than 10 cm is more than 15,000. Recently there were two critical events: One is that China shot down their satellite using missile and the other is that two satellite, United States`s Iridium 33 and Russia`s Cosmos 2251, collided with each other. Thanks to these events, Space environment in which KOMPSAT-2 operates has become severer. This paper presents the analysis of the number of space debris which are close to KOMPSAT-2 and the maximum conjunction probability via minimum range. Especially, this paper makes it possible to continuously monitor the space debris that is possible to hit KOMPSAT-2 through the identification and analysis.
Technology of Control Moment Gyroscope and its Industrial Trend
Lee, Seon-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 86~92
DOI : 10.5139/JKSAS.2012.40.1.86
The well-used actuators for the attitude control of spacecrafts are thruster, reaction wheel, control moment gyroscope, and magnetic torquer. Among them, the control moment gyroscope(CMG) which generates the torque based on the gyroscopic principle in physics, has an advantage of the high torque output compared to the low power consumption. This paper introduces an outline of CMG hardware technology, its application history in spacecrafts, and their associated hardware characteristics. Moreover, its spin-off cases to the other industrial fields such as ship, robotics, and MEMS including their research trend are provided.
Development of an Airborne Telemetry Relay System Using Aircraft
Yeom, Hyeong-Seop ; Oh, Jong-Hoon ; Sung, Duck-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 1, 2012, Pages 93~100
DOI : 10.5139/JKSAS.2011.40.1.93
A telemetry signal occurs the line-of-sight problem by the effect of geography in flight test. A fixed relay system or a mobile relay system is used to solve that problem in general but we propose an airborne telemetry relay system using aircraft in this paper. An airborne telemetry relay system receives the telemetry signal of the test vehicle and then retransmits it to the ground system. The receiving antenna which is a phased array antenna can be tilted to
beam direction by beam-forming and track the rapidly moving test vehicle in effect. The relay pod which is mounted to an aircraft consists of the front antenna and the side antenna. It receives S-band signal and then down-converts the frequency to L-band signal. As a result, that can remove the frequency interference on an aircraft while retransmitting.