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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 38, Issue 12 - Dec 2010
Volume 38, Issue 11 - Nov 2010
Volume 38, Issue 10 - Oct 2010
Volume 38, Issue 9 - Sep 2010
Volume 38, Issue 8 - Aug 2010
Volume 38, Issue 7 - Jul 2010
Volume 38, Issue 6 - Jun 2010
Volume 38, Issue 5 - May 2010
Volume 38, Issue 4 - Apr 2010
Volume 38, Issue 3 - Mar 2010
Volume 38, Issue 2 - Feb 2010
Volume 38, Issue 1 - Jan 2010
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Dynamic Correction of DES Model Constant for the Advanced Prediction of Supersonic Base Flow
Shin, Jae-Ryul ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 99~110
DOI : 10.5139/JKSAS.2010.38.2.099
The DES analysis of strong compressibility flow, LES mode is intentionally performed in boundary layer with the conventional empirical constant
value of 0.65. In this study, an expression is suggested to determine the
value dynamically by using a distribution function of the ratio of turbulence length scale and wall distance which is used in S-A DDES model for RANS mode protection. The application of the dynamic
presents better prediction than previous results those used constant but different
A Study on Failure Strength of Single Lap Adhesive Joint with Thick Adherend
Park, Jae-Hyun ; Choi, Jin-Ho ; Kweon, Jin-Hwe ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 111~118
DOI : 10.5139/JKSAS.2010.38.2.111
The joints are often the weakest areas in composite structures. In this paper, the thick aluminum-aluminum joint specimens and thick composite-aluminum single lap adhesive joint specimens were manufactured and the tensile tests were performed. The fracture mode of each specimen was investigated and the modified damage zone theory based on the yield strain was proposed and compared with experimental failure load of each mode. The failure loads of the thick aluminum-aluminum joint and composite-aluminum joint were predicted by the same failure criterion and they could be predicted to within 19.3% using the damage zone ratio method for all 14 cases investigated.
Hygrothermal Effect on the Strength of Carbon/Epoxy Composite Single-Lap Bonded Joints
Song, Min-Gyu ; Kweon, Jin-Hwe ; Choi, Jin-Ho ; Kim, Hyo-Jin ; Song, Min-Hwan ; Shin, Sang-Joon ; Byun, Jai-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 119~128
DOI : 10.5139/JKSAS.2010.38.2.119
The hygrothermal effect on the strength of composite single-lap bonded joints were investigated. The specimens were manufactured in four different manufacturing methods and tested in three different environmental conditions. An interesting result is that the strengths of the joints in the elevated temperature and wet (ETW) conditions were found to be 11 ~ 23% higher than those in the room temperature and dry (RTD) environment. In contrast, the strengths of the joints in the cold temperature and dry (CTD) condition decrease by 8 ~ 21% compared to those in the RTD environment except for cobonded joint. The difference in the strength by testing environments is mainly attributed to the change of the material properties of adhesive by temperature and moisture.
Thermomechanical Characteristics of SMAs with Strain-rate Dependence
Roh, Jin-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 129~134
DOI : 10.5139/JKSAS.2010.38.2.129
The influence of the strain-rate on the thermomechanical characteristics of shape memory alloys (SMAs) is numerically investigated. The three-dimensional SMA constitutive equations of strain-rate effect is developed. The strain-rate effect is taken into account by introducing a coupling equation between the production rate of martensite and the temperature change. For the numerical results, the SMA algorithm is implemented into the ABAQUS finite element program. Numerical simulation shows that the pseudoelasticity of SMA may significantly be changed by considering the strain-rate due to the temperature change.
Handling Deflection Limit in Open-Loop-Onset-Point PIO Analysis
Park, Sang-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 135~140
DOI : 10.5139/JKSAS.2010.38.2.135
A new treatment is proposed to handle a deflection limit in the open-loop-onset-point (OLOP), which is commonly used in the prediction of pilot in-the-loop oscillation (PIO) due to a rate saturation. The new approach is motivated by the frequency response of a stand-alone actuator in that, unlike the suggestion by the original OLOP procedure, the rate limit onset is not delayed to a higher frequency by a deflection limit. Indeed, if a feedback control loop is closed, the rate limit onset can be shifted to a lower frequency since the controller tends to react with larger commands when deflection limited. The amplitude of the command at this onset frequency is combined with the deflection limit to estimate the associated gain reduction in the open-loop-onset-point in the final step of the OLOP process. The comparison of the new approach with the previous method reveals that an inaccurate optimism which can occur in the previous method is corrected by the proposed treatment.
Optimal Impulsive Maneuver for Satellite FormationKeeping with Fuel Balancing
Mok, Sung-Hoon ; Choi, Yoon-Huck ; Cho, Dong-Hyun ; Bang, Hyo-Choong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 141~149
DOI : 10.5139/JKSAS.2010.38.2.141
This paper contains impulsive maneuver which considers fuel consumption balance of chief satellite and deputy satellite in satellite formation flying. Thrust input is obtained by Lagrange` Multiplier method which is constructed by cost function with weight parameter of each satellite. Energy matching constraint is applied for boundedness of relative orbit, and theoretical solutions are verified by simulation results. Simulations are divided into two scenarios, with or without air-drag effect. This paper`s results are expected to be used in real satellite formation flying, when fuel-balancing impulsive maneuver for relative orbit boundedness is needed.
Trajectory Planning and Fuzzy Controller Design of a Re-entry vehicle on Approach and Landing phase
Min, Chan-Oh ; Jo, Sung-Jin ; Lee, Dae-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 150~159
DOI : 10.5139/JKSAS.2010.38.2.150
The approach and landing phase of a re-entry vehicle is composed of Steep Glideslope phase, Circular Flare phase, Flare Maneuver phase. The trajectory planning algorithm with geometric parameters is studied in this paper for on-board trajectory planning. This algorithm generate reference trajectory rapidly considering safe landing of re-entry vehicle. In this paper, the Mamdani Fuzzy PD type controller for longitudinal and lateral control is designed which has robustness of nonlinear system. In addition, the simulation is performed including initial downrange and crossrange errors, and the results shows that the proposed fuzzy logic controller has good performance.
A Study of Flow Characteristics by Acoustic Excitation on the Laminar Non-premixed Jet Flame
Oh, Kwang-Chul ; Lee, Kee-Man ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 160~168
DOI : 10.5139/JKSAS.2010.38.2.160
An experimental study has been conducted to investigate the effects of forcing amplitude on the tone-excited non-premixed jet flame of the resonance frequency. Visualization techniques are employed using the laser optic systems, which are RMS tomography, PLIF and PIV system. There are three lift-off histories according to the fuel flow rates and forcing amplitudes; the regime I always has the flame base feature like turbulent flame when the flame lift-off, while the flame easily lift-off in the regime II even if a slight forcing amplitude applied. The other is a transient regime and occurs between the regime I and regime II, which has the flame base like the bunsen flame of partial premixed flame. In the regime I and II, the characteristics of the mixing and velocity profile according to the forcing phase were investigated by the acetone PLIF, PIV system. Particular understanding is focused on the distinction of lift-off history in the regime I and II.
Redundancy Management Design for Triplex Flight Control System
Park, Sung-Han ; Kim, Jae-Yong ; Cho, In-Je ; Hwang, Byung-Moon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 169~179
DOI : 10.5139/JKSAS.2010.38.2.169
Satisfying the same probability of loss of control and essentially two fail operative performance with a triplex computer architecture requires a lot of modification of the conventional redundancy management design techniques, previously employed in quadruplex digital flight control computer. T-50 FCS for triplex redundancy management design applied an advanced digital flight control architecture with an I/O controller which is functionally independent of the digital computer to achieve the same reliability and special failure analysis and isolation schemes for fail operational goals with a triplex configuration. The analysis results indicated that the triplex flight control system is to satisfy the safety requirement utilizing the advanced flight control techniques and the system performance of the implemented flight control system was verified by failure mode effect test.
Steering Performance Test of Autonomous Guided Vehicle(AGV) Based on Global Navigation Satellite System(GNSS)
Kang, Woo-Yong ; Lee, Eun-Sung ; Kim, Jeong-Won ; Heo, Moon-Beom ; Nam, Gi-Wook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 180~187
DOI : 10.5139/JKSAS.2010.38.2.180
In this paper, a GNSS-based AGV system was designed, and steering tested on a golf cart using electric wires in order to confirm the control efficiency of the low speed vehicle which used only position information of GNSS. After analyzed the existing AGVs system, we developed controller and steering algorithm using GNSS based position information. To analyze the performance of the developed controller and steering algorithm, straight-type and circle-type trajectory test are executed. The results show that steering performance of GNSS-based AGV system is
for a reference trajectory.
Development of SAR Image Quality Performance Analysis Tool for High Resolution Spaceborne Synthetic Aperture Radar
Oh, Tae-Bong ; Jung, Chul-Ho ; Song, Sun-Ho ; Shin, Jae-Min ; Kwag, Young-Kil ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 188~194
DOI : 10.5139/JKSAS.2010.38.2.188
In this paper, the typical Synthetic Aperture Radar (SAR) image quality parameters and analysis method are defined, and the SAR image analysis tool is presented for SAR image evaluation. The structure of the developed SAR image analysis tool consists of four key modules; point target analysis (PTA) module, distributed target analysis (DTA) module, ambiguity analysis (AMA) module, and NESZ analysis (NESZA) module. The developed tool is able to extract the various SAR system parameters from standard SAR product format files. Based on these extracted system parameters, typical SAR image quality parameters are derived from SAR image data.
The design and performance analysis of RS(255,223) code for X-band downlink of STSAT-3
Seo, In-Ho ; Kim, Byung-Jun ; Lee, Jong-Ju ; Kwak, Seong-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 195~199
DOI : 10.5139/JKSAS.2010.38.2.195
(255,223) RS(Reed-Solomon) code which is the CCSDS(Consultative Committee for Space Data Systems) standard was used in the STSAT-3 to correct errors during the downlink of payload data. The RS encoder developed by VHDL was implemented in MMU(Mass Memory Unit). Moreover, the RS decoder developed by C-language was implemented in the DRS(Data Receiving System) of ground station. In this paper, we reported the design and analysis results of RS(255,223) for STSAT-3. The BER(Bit Error Rate) performance from MMU to DRS was confirmed through the downlink test at 16 Mbps. Also, the error correction performance and capability of RS(255,223) was tested by the manual attenuation of the RF(Radio Frequency) signal in the X-band transmitter resulting in putting some errors in the communication line.
Thermal Performance Evaluations of Tungsten/Yttria as Nozzle Throat Insert Material for Long Duration Firing
Kang, Yoon-Goo ; Park, Jong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 2, 2010, Pages 200~205
DOI : 10.5139/JKSAS.2010.38.2.200
Heat-resistance of W/
as throat insert material was evaluated to develop rocket motor keeping thrust uniformly under condition of high-temperature, high-pressure and long-burn time. Test was conducted with varying burn time, and test results were compared with CIT. Test showed that ablation rate was decreased according as burn time was increased, and that ablation rate of W/
was about 55 % of CIT. Macro/micro structures of throat insert did not show a peculiar phenomenon by increased burn time. In addition, the vacuum heat treatment is effective for the prevention of crack in throat insert.