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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 37, Issue 12 - Dec 2009
Volume 37, Issue 11 - Nov 2009
Volume 37, Issue 10 - Oct 2009
Volume 37, Issue 9 - Sep 2009
Volume 37, Issue 8 - Aug 2009
Volume 37, Issue 7 - Jul 2009
Volume 37, Issue 6 - Jun 2009
Volume 37, Issue 5 - May 2009
Volume 37, Issue 4 - Apr 2009
Volume 37, Issue 3 - Mar 2009
Volume 37, Issue 2 - Feb 2009
Volume 37, Issue 1 - Jan 2009
Selecting the target year
An Analysis of BVI Unsteady Rotor Aerodynamics using Unsteady Panel and Time-Marching Free Wake
Wie, Seong-Yong ; Lee, Duck-Joo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 329~335
DOI : 10.5139/JKSAS.2009.37.4.329
The unsteady panel and time-marching free wake are applied to the rotor aerodynamics and wake behaviour. Numerical results of panel and free wake are compared and validated with experimental data. Using these methods, unsteady rotor aerodynamics in BVI condition is analyzed and discussed in detail.
Controlling the Horseshoe Vortex by the Leading-Edge Fence at a Generic Wing-Body Junction
Cho, Jong-Jae ; Kim, Kui-Soon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 336~343
DOI : 10.5139/JKSAS.2009.37.4.336
Secondary flow losses can be as high as 30~50% of the total aerodynamic losses generated in the cascade of a turbine. Therefore, these are important part for improving a turbine efficiency. As well, many studies have been performed to decrease the secondary flow losses. The present study deals with the leading edge fences on a wing-body to decrease a horseshoe vortex, one of the factors to generate the secondary flow losses, and investigates the characteristics of the generated horseshoe vortex as the shape factors, such as the installed height, and length of the fence. The study was investigated using
. Total pressure loss coefficient was improved about 4.0 % at the best case than the baseline.
Force Control of Main Landing Gear using Magneto-Rheological Damper
Hyun, Young-O ; Hwang, Jae-Up ; Hwang, Jae-Hyuk ; Bae, Jae-Sung ; Lim, Kyoung-Ho ; Kim, Doo-Man ; Kim, Tae-Wook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 344~349
DOI : 10.5139/JKSAS.2009.37.4.344
To improve performance of the main landing gear for helicopters, a semi-active control landing gear is introduced in this paper. An MR damper based on commercial finite element electromagnetic field analysis of an electromagnet has been adapted the shock absorber. Force control algorithm (which maintains constantly the sum of air spring force and damping force as internal forces) which keep the sum of air spring force and damping force constant during landing, has been used for the controller, applied to control the semi-active landing gear. A series of drop simulations using ADAMS has been done with the passive, sky-hook control type, and force control type landing gears. The result of each simulation has been compared to evaluate the landing performance of the proposed force control type landing gear.
Trajectory Optimization and the Control of a Re-entry Vehicle during TAEM Phase using Artificial Neural Network
Kim, Jong-Hun ; Lee, Dae-Woo ; Cho, Kyeum-Rae ; Min, Chan-Oh ; Cho, Sung-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 350~358
DOI : 10.5139/JKSAS.2009.37.4.350
This paper describes a result of the guidance and control for re-entry vehicle during TAEM phase. TAEM phase (Terminal Aerial Energy Management phase) has many conditions, such as density, velocity, and so on. Under these conditions, we have optimized trajectory and other states for guidance in TAEM phase. The optimized states consist of 7 variables, down-range, cross range, altitude, velocity, flight path angle, vehicle`s azimuth and flight range. We obtained the optimized reference trajectory by DIDO tool, and used feedback linearization with neural network for control re-entry vehicle. By back propagation algorithm, vehicle dynamics is approximated to real one. New command can be decided using the approximated dynamics, delayed command input and plant output, NARMA-L2. The result by this control law shows a good performance of tracking onto the reference trajectory.
A Study on Validation of OFP for UAV using Auto Code Generation
Cho, Sang-Ook ; Choi, Kee-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 359~366
DOI : 10.5139/JKSAS.2009.37.4.359
MATLAB Autocode generation is a feature that converts a block diagram model in Simulink to a c program. Utilizing this function makes MATLAB/Simulink an integrated developing environment, from controller design to implementation. It can reduce development cost and time significantly. However, this automated process requires high reliability on the software, especially the original Simulink block diagram model. And thus, the verification of the codes becomes important. In this study, a UAV flight program which is generated with Simulink is validated and modified according to DO-178B. As a result of applying the procedures, the final program not only satisfied the functional requirement but is also verified with structural point of view with Decision Coverage 93%, Condition Coverage 95% and MC/DC 90%.
Analysis on Optimality of Proportional Navigation Based on Nonlinear Formulation
Jeon, In-Soo ; Lee, Jin-Ik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 367~371
DOI : 10.5139/JKSAS.2009.37.4.367
Analysis on optimality of the proportional navigation guidance(PNG) law is presented in this paper. While most of previous studies on optimality of PNG were relied on the linear formulation, this paper is based on the nonlinear formulation. The analysis shows that PNG is an optimal solution minimizing a range-weighted control energy, where the weighting function is an inverse of
power of the distance-to-target. We show that the navigation constant N is related to
directly. And also the conditions required to ensure the analysis result are investigated.
Analysis of MSAS Correction Information and Performance in Korea
Jeong, Myeong-Sook ; Kim, Jeong-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 372~382
DOI : 10.5139/JKSAS.2009.37.4.372
A GNSS software for processing the SBAS correction data is developed, and Japan MSAS correction data is analyzed. MSAS orbit correction data is analyzed and compared with WAAS data. MSAS ionosphere correction data is analyzed and the effect of the equatorial anomaly on the correction accuracy is discussed. Degradation due to receive delay of correction information and effect of the degradation on protection level analyzed using partial remove of MSAS correction information. Integrity and availability for precision approch using the MSAS system analyzed.
Detonation Wave Simulation of Thermally Cracked JP-7 Fuel/Oxygen Mixture using Induction Parameter Modeling
Cho, Deok-Rae ; Shin, Jae-Ryul ; Choi, Jeong-Yeol ; Yang, Vigor ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 383~391
DOI : 10.5139/JKSAS.2009.37.4.383
The detonation wave characteristics of JP-7 and oxygen mixture is investigated by one-step induction parameter model (IPM) obtained from a detailed chemistry mechanism. A general procedure of obtaining reliable one-step kinetics IPM for hydrocarbon mixture from the fully detailed chemistry is described in this study. The IPM is obtained by the reconstruction of the induction time database obtained from a detailed kinetics library. The IPM was confirmed by the comparison of the induction time calculations with that from detailed kinetics. The IPM is later implemented to a fluid dynamics code and applied for the numerical simulation of detonation wave propagation. The numerical results show the detailed characteristics of the detonation wave propagation in JP-7 and oxygen mixture at affordable computing time, which is not be possible by the direct application of the detailed chemical kinetics mechanism of hydrocarbon fuel combustion.
Thrust modulation performance analysis of pintle-nozzle motor
Kim, Joung-Keun ; Park, Jong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 392~398
DOI : 10.5139/JKSAS.2009.37.4.392
Theoretical thrust equations for the diverse nozzle expansion condition were derived. By using the obtained thrust equations, parametric studies were carried out to estimate the effect of pressure exponent, minimum operation pressure, ambient pressure and extinguishment pressure on thrust modulation performance in pintle-nozzle solid rocket motors. Analysis results showed that thrust turndown ratio can be easily attained by small nozzle-throat area variation at high pressure exponent, low minimum operation pressure, high ambient pressure and high extinguishment pressure condition. At those conditions, the highest chamber pressure to obtain the intended thrust turndown ratio can be minimized.
Dynamic Characteristics of a Piezoelectric Driven Stick-Slip Actuator for Focal Plane Image Stabilization
Kwag, Dong-Gi ; Bae, Jae-Sung ; Hwang, Jai-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 399~405
DOI : 10.5139/JKSAS.2009.37.4.399
The focal plane image stabilization for a satellite camera is one of the an effective method which can increase the satellite camera`s image quality by removing the motion disturbance of a focal plane. The objectives of this article are to introduce the concept of the focal plane image stabilization and determine the best driving conditions of the actuator for the response and thrust. Under various driving condition the experiments have been performed to investigate the response and thrust characteristics of the piezoelectric driven stick-slip actuator of the focal plane image stabilizing device. From experiments, the best driving frequency and duty ratio for the magnesium slider are 70 kHz and 27%, respectively.
Development of FAA AC120-63 Level C Flight Simulation Model for KA-32T
Jeon, Dae-Keun ; Jun, Hyang-Sig ; Choi, Hyoung-Sik ; Choi, Young-Kiu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 406~412
DOI : 10.5139/JKSAS.2009.37.4.406
Flight simulation model for helicopter simulator is one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the helicopter designers/manufacturers. The approaches in this study were to develop the basic model based on the available resources regarding helicopter operation/maintenance and to tune and validate it based on the flight test results. The basic model was developed with maintenance manuals, flight manuals, analyses, measurements, papers and so on considering that KA-32T data could not be obtained from the manufacturer. The flight test for KA-32T was performed and the reference data for the simulation validation tests were acquired. The flight simulation model was validated to have the fidelity compatible with level C of FAA AC120-63 after comparison and tuning with flight test results.
Design and Implementation of S-Band Transponder for Telemetry and Command of Small Satellite
Oh, Seung-Han ; Shin, Young-Sup ; Yi, Hui-Min ; Hong, Sung-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 413~418
DOI : 10.5139/JKSAS.2009.37.4.413
The S-band Transponder for telemetry and command of small satellite is designed and fabricated as prototype model using COTS(Commercial Off-The-Shelf) components. QPSK modulator and demodulator of transponder is implemented by using FPGA for system extension. The transponder consists of RF Front End, RF Modulator, RF Demodulator, and MODEM. The measured results of fabricated transponder show BER of less than
at -105 dBm input power.
Development of Xenon feed system for a 300 W Hall-effect Thruster
Kim, Youn-Ho ; Seon, Jong-Ho ; Kang, Seong-Min ; Wee, Jung-Hyun ; Yoon, Ho-Sung ; Choe, Won-Ho ; Lee, Jong-Sub ; Seo, Mi-Hui ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 4, 2009, Pages 419~424
DOI : 10.5139/JKSAS.2009.37.4.419
A Xenon feed system has been developed for a 300 W Hall-effect thruster intended for orbit maintenance of small satellite. The system can store about 2 kg of xenon gas at 150 bar and is capable of controlling the mass flow rate of the gas at 0.5 SCCM resolution. The performance of the system is verified with a laboratory experiment. It is confirmed that the operation of the feed system is successful at a pressure level of
torr in the vacuum chamber.