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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
Selecting the target year
Real Gas Speeds of Sound and Approximate Riemann Solver
Moon, Seong-Young ; Han, Sang-Hoon ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 1~11
DOI : 10.5139/JKSAS.2010.38.1.001
The definition of the speed of sound is reexamined since it is crucial in the numerical analysis of compressible real gas flows. The thermodynamic speed of sound (TSS),
, and the characteristic speed of sound (CSS),
, are derived using generalized equation of state (EOS). It is found that the real gas EOS, for which pressure is not linearly dependent on density and temperature, results in slightly different TSS and CSS. in this formalism, Roe`s approximate Riemann solver was derived again with corrections for real gases. The results show a little difference when the speeds of sound are applied to the Roe`s scheme and Advection Upstream Splitting Method (AUSM) scheme, but a numerical instability is observed for a special case using AUSM scheme. It is considered reasonable to use of CSS for the mathematical consistency of the numerical schemes. The approach is applicable to multi-dimensional problems consistently.
Experimental Study on the Small-Scale Rotor Hover Performance in Partial Ground Conditions
Seo, Jin-Woo ; Lee, Byoung-Eon ; Kang, Beom-Soo ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 12~21
DOI : 10.5139/JKSAS.2010.38.1.012
This paper focuses on the hover performance experiment of a small-scale single rotor in partial ground conditions. In this study, small-scale rotor blade rotating device and floor panel are used to include partial ground effect. Thrust and torque were measured with varying collective pitch angles at fixed rotor rotating speed. The overlap distance between rotor and ground is d, the rotor diameter is D. It was shown that the ground effects have little effect on the rotor performance until d/D is 0.25. Four blade rotor has more increased thrust and more reduced power than those of two blade rotor because of stronger ground effect. In addition, it was also found that the thrust increases as a collective pitch angle become smaller. Based on these experiment results, we deduced new empirical equation considered blade number and partial ground effect.
Impact Behavior Analysis on Composite Laminate with Damages
Kim, Sung-Joon ; Hong, Chang-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 22~28
DOI : 10.5139/JKSAS.2010.38.1.022
To detect the damage in composite structure, nondestructive evaluation techniques are widely used. Tapping test is perhaps the most common technique used for the detection of damage in composite laminates. The method is accomplished by tapping the inspection area with light hammer-like device. The tapping test has the ability that indicates damages in a structure due to a localized change of stiffness. The change in vibration signature may be detected by measurement of the dynamic contact force during impact. In this study, it has been shown that the characteristics of impact force histories from a structure during tapping are changed by the presence of damage such as surface crack and delamination. And impact response analysis has been performed on composite rotor blade with crack to investigate the effect of damage.
Strength Improvement of Insert Joint for Composite Sandwich Structure
Kim, Kwang-Soo ; An, Jae-Mo ; Jang, Young-Soon ; Yi, Yeong-Moo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 29~34
DOI : 10.5139/JKSAS.2010.38.1.029
In this study, joint strength and failure characteristics were experimentally examined with pull-out and shear specimens in which new designed "high strength insert" was applied. The performance of the new insert was compared with typical insert design. The experimental results showed that the "high strength insert" had the joint strengths of 2.1 times in the pull-out specimens and 2.04 times in the shear specimen compared with typical insert joints. Therefore, the new developed "high strength insert" will be usefully used in the aerospace structure.
Reconfiguration Control Using LMI-based Constrained MPC
Oh, Hyon-Dong ; Min, Byoung-Mun ; Kim, Tae-Hun ; Tahk, Min-Jea ; Lee, Jang-Ho ; Kim, Eung-Tai ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 35~41
DOI : 10.5139/JKSAS.2010.38.1.035
In developing modern aircraft, the reconfiguration control that can improve the safety and the survivability against the unexpected failure by partitioning control surfaces into several parts has been actively studied. This paper deals with the reconfiguration control using model predictive control method considering the saturation of control surfaces under the control surface failure. Linearized aircraft model at trim condition is used as the internal model of model predictive control. We propose the controller that performs optimization using LMI (linear matrix inequalities) based semi-definite programming in case that control surface saturation occurs, otherwise, uses analytic solution of the model predictive control. The performance of the proposed control method is evaluated by nonlinear simulation under the flight scenario of control surface failure.
Fault Tolerant Attitude Control of a Spacecraft Using Two Wheels
Jin, Jae-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 42~47
DOI : 10.5139/JKSAS.2010.38.1.042
This paper considers a fault tolerant control problem for a spacecraft using wheels which are momentum exchanging devices. The control of a satellite with only two healthy wheels has been studied and its result has been presented. Two different configurations have been considered. When the yaw rate cannot be controlled directly by any control input, the desired yaw rate can be obtained by using the roll rate as a pseudo control. As a result, all three angular speeds have been stabilized, and two attitude angles including pitch and yaw have been controlled to converge to the desired values.
A Comparison of Scheduling Optimization Algorithm for the Efficient Satellite Mission Scheduling Operation
Baek, Seung-Woo ; Cho, Kyeum-Rae ; Lee, Dae-Woo ; Kim, Hae-Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 48~57
DOI : 10.5139/JKSAS.2010.38.1.048
A comparison of two kinds of scheduling optimization algorithms is presented in this paper. As satellite control and operation techniques have been developed, satellite missions became more complicated and overall quantity of missions also increased. These changes require more specific consideration and a huge amount of computation for the satellite mission scheduling. Therefore, it is a good strategy to make a scheduling optimization algorithm for the efficient satellite mission scheduling operation. In this paper, two kinds of scheduling optimization algorithms are designed with tabu-search algorithm and genetic algorithm respectively. These algorithms are applied for the same mission scenario and the results of each algorithm are compared and analyzed.
Detection of GPS Clock Jump using Teager Energy
Heo, Youn-Jeong ; Cho, Jeong-Ho ; Heo, Moon-Beom ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 58~63
DOI : 10.5139/JKSAS.2010.38.1.058
In this paper, we propose a simple technique for the detection of a frequency jump in the GPS clock behavior. GPS satellite atomic clocks have characteristics of a second order polynomial in the long term and a non-periodic frequency drift in the short term, showing a sudden frequency jump occasionally. As satellite clock anomalies influence on GPS measurements, it requires to develop a real time technique for the detection of the clock anomaly on the real-time GPS precise point positioning. The proposed technique is based on Teager energy which is mainly used in the field of various signal processing for the detection of a specific signal or symptom. Therefore, we employed the Teager energy for the detection of the jump phenomenon of GPS satellite atomic clocks, and it showed that the proposed clock anomaly detection strategy outperforms a conventional detection methodology.
Frequency Response of Turbulent Flow to Momentum Forcing in a Channel with Wall Blowing
Na, Yang ; Lee, Chang-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 64~72
DOI : 10.5139/JKSAS.2010.38.1.064
Due to the interaction between main oxidizer flow and the wall injected flow resulting from the regression process, a specific time characteristics identified in the frequency spectrum of streamwise velocity is generated in the hybrid rocket motor. In order to understand the response of the turbulent flow to two different types of external momentum forcing, LES analysis was conducted without considering the combustion. It turns out that both concentrated and distributed forcings do not lead to the disastrous resonance phenomenon. Energy contents are enhanced due to the added momentum but the peak frequency was not modified in the turbulent flow near the end of the rocket motor. Natural frequency of the flow system should be taken into account to further pursue the instability issue by using external forcing.
Flow Visualization and Calculation at the Outlet of Propellant Tank Pressurizing Gas Injector
Kwon, Oh-Sung ; Han, Sang-Yeop ; Kwon, Ki-Jung ; Chung, Yong-Cahp ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 73~79
DOI : 10.5139/JKSAS.2010.38.1.073
Propellant tank pressurizing gas injector is used in the pressurization system of liquid propellant rocket to reduce incoming gas velocity and distribute the gas in the tank. Temperature distribution in the propellant tank ullage is varied according to the gas injector shape, and it has influence on the required pressurant gas and thermal phenomena in the tank. In this paper, diffuser type gas injector was studied to make the ullage have stratified temperature distribution. Injected gas flow at the outlet of prototype diffuser was visulized using particle image velocimetry method and it was compared with the results of calculation. Calculation was well agreed with measurement and was used as an inlet condition of propellant tank ullage calculation.
Design and Implementation of Engineering Qualification Model of S-Band Transmitter for STSAT-3
Oh, Seung-Han ; Seo, Gyu-Jae ; Oh, Dae-Soo ; Lee, Jung-Soo ; Oh, Chi-Wook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 80~86
DOI : 10.5139/JKSAS.2010.38.1.080
This paper describes the development result of S-band Transmitter of STSAT-3 by satellite research center(SaTReC), KAIST. STSAT-3 has two kinds of communication channels, S- band for Telemetry & Command and X-band for mission payload. S-band Transmiiter(STX) consist of modulator, frequency synthesizer, power amp and DC/DC converter. The modulation scheme of STX is FSK(Frequency Shift Keying). The interface between spacecraft OBC and STX is RS-422. The STX is based on modular design. The RF output power of STX is 1.5W(31.7dBm) and BER of STX is under 1E-5. The Test of STX is completed successfully such as functional Test and environmental(vibration, thermal vacuum) Test.
Error Correction Code and SEU Test Analysis of Mass Memory for STSAT-3
Seo, In-Ho ; Ryu, Kwang-Sun ; Oh, Dae-Soo ; Kim, Byung-Jun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 87~93
DOI : 10.5139/JKSAS.2010.38.1.087
RS(10,8) Code by 4-bit symbol was developed to protect the mass memory of STSAT-3 from SEU in orbit. Therefore, one symbol can be corrected for 32-bit data with 8-bit parity configuration. Moreover, scrubbing period and SEU occurrence rate was calculated based on the KITSAT-3 result. A prediction of SEU rates was performed based on the ground experiment results with a proton accelerator in the KIRAMS(Korea Institute of Radiological Medical Sciences).
High Reliability Proto-type Auxiliary Power Supply Development for Satellite
Choo, Won-Gyo ; Kim, Hyun-Gu ; Woo, Hyung-Je ; Koo, Ja-Chun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 1, 2010, Pages 94~98
DOI : 10.5139/JKSAS.2010.38.1.094
The auxiliary power supply for satellite should make the power safe and support it for subsystems during its operational lifetime. Several contstraints should be required to get high reliability. In this paper, the auxiliary power supply was satisifed and designed to be satisified with some contstraints. Control circuits for the auxiliary power supply used majority voter circuits to remove the single point failure. To verify majority voter circuits, proto-type auxiliary power supply was manufactured and tested.