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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
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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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Transition Prediction of Boundary Layers over Airfoils based on Boundary Layer Stability Theory
Park, Dong-Hun ; Park, Seung-O ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 403~413
DOI : 10.5139/JKSAS.2010.38.5.403
Transition location of boundary layers over airfoils is predicted by using PSE(Parabolized Stability Equations) and
-method. Growth rates of disturbances are obtained from the PSE analysis and the N-factor curves are calculated by integrating the growth rates. The computational code developed in the present study is validated by comparing the computed results with the well known data for the cases of flat plate boundary layers and airfoils. Predictions of transition location are made for the boundary layers over NACA0012, NLF(1)-0414F, and NLF(1)-0416 airfoil. Predicted transition locations are found to be in good agreement with the experimental data.
Design Optimization of Transonic Wing/Fuselage System Using Proper Orthogona1 Decomposition
Park, Kyung-Hyun ; Jun, Sang-Ook ; Cho, Maeng-Hyo ; Lee, Dong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 414~420
DOI : 10.5139/JKSAS.2010.38.5.414
This paper presents a validation of the accuracy of a reduced order model(ROM) and the efficiency of the design optimization using a Proper Orthogonal Decomposition(POD) to transonic wing/fuselage system. Three dimensional Euler equations are solved to extrude snapshot data of the full order aerodynamic analysis, and then a set of POD basis vectors reproducing the behavior of flow around the wing/fuselage system is calculated from these snapshots. In this study, reduced order model constructed through this procedure is applied to several validation cases, and then it is confirmed that the ROM has the capability of the prediction of flow field in the space of interest. Additionally, after the design optimization of the wing/fuselage system with the ROM is performed, results of the ROM are compared with results of the design optimization using response surface model(RSM). From these, it can be confirmed that the design optimization with the ROM is more efficient than RSM.
Thickness Effect on Wrinkle-Crease Interaction for Thin Membrane
Woo, Kyeong-Sik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 421~426
DOI : 10.5139/JKSAS.2010.38.5.421
In this paper, the thickness effect on the wrinkle-crease interaction behavior of corner-loaded creased square membranes was studied using geometrically nonlinear post-buckling analysis. The membranes were modeled using shell elements, and the meshes were seeded with semi-random geometrical imperfection to instigate the buckling deformation. Results indicated that the wrinkle-crease interaction behavior was significantly dependent on the membrane thickness. Both the global and local wrinkles developed earlier as the thickness decreased. It was also found that the wrinkling behavior depended on the initial deployment angle in which the local wrinkle initiation occurred earlier, while the global wrinkle formation was delayed as the angle increased.
Task Assignment of Multiple UAVs using MILP and GA
Choi, Hyun-Jin ; Seo, Joong-Bo ; Kim, You-Dan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 427~436
DOI : 10.5139/JKSAS.2010.38.5.427
This paper deals with a task assignment problem of multiple UAVs performing multiple tasks on multiple targets. The task assignment problem of multiple UAVs is a kind of combinatorial optimization problems such as traveling salesman problem or vehicle routing problem, and it has NP-hard computational complexity. Therefore, computation time increases as the size of considered problem increases. To solve the problem efficiently, approximation methods or heuristic methods are widely used. In this study, the problem is formulated as a mixed integer linear program, and is solved by a mixed integer linear programming and a genetic algorithm, respectively. Numerical simulations for the environment of the multiple targets, multiple tasks, and obstacles were performed to analyze the optimality and efficiency of each method.
Analysis of Attitude Control Characteristics for an Underactuated Spacecraft Using a Single-Gimbal Variable-Speed CMG
Jin, Jae-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 437~444
DOI : 10.5139/JKSAS.2010.38.5.437
This paper deals with the attitude control of an underactuated spacecraft that has one single-gimbal variable-speed CMG. An underactuated spacecraft may not converge to arbitrary attitudes if its total angular momentum is not zero. To stabilize a spacecraft, the CMG has to align with the angular momentum in the inertial frame. Four different install configurations for the CMG have been considered and controllable angular momentums have been analyzed. Also, based on the backstepping method, stabilizing control laws have been presented and their properties have been compared.
Development of Helmholtz Solver for Thermo-Acoustic Instability within Combustion Devices
Kim, Seong-Ku ; Choi, Hwan-Seok ; Cha, Dong-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 445~455
DOI : 10.5139/JKSAS.2010.38.5.445
In order to effectively predict thermo-acoustic instability within real combustors of rocket engines and gas turbines, in the present study, the Helmholtz equation in conjunction with the time lag hypothesis is discretized by the finite element method on three-dimensional hybrid unstructured mesh. Numerical nonlinearity caused by the combustion response term is linearized by an iterative method, and the large-scale eigenvalue problem is solved by the Arnoldi method available in the ARPACK. As a consequence, the final solution of complex valued eigenfrequency and acoustic pressure field can be interpreted as resonant frequency, growth rate, and modal shape for acoustic modes of interest. The predictive capabilities of the present method have been validated against two academic problems with complex impedance boundary and premixed flame, as well as an ambient acoustic test for liquid rocket combustion chamber with/without baffle.
The Characteristics of DC-shift in Hybrid Rocket
Kang, Dong-Hoon ; Lee, Chang-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 456~466
DOI : 10.5139/JKSAS.2010.38.5.456
Typical combustion instability such as DC-Shift found in the hybrid rocket motor is characterized by non-linearity. DC-Shift can occur in two different realizations. One is so-called a positive shift of measured DC voltage where the pressure increase suddenly. The other is a negative shift where the pressure drops abruptly. In the present work, specifically the negative DC-Shift was investigated to analyze the effect of oxidizer flow condition and the resonance between fundamental frequency and other ones, such as Helmholtz frequency, and acoustic frequency. Results show a peak frequency of several hundreds HZ shifts as combustion proceeds. A negative DC-shift was found as the result of phase cancellation between two dominant frequency, combustion frequency and flow related frequency. Still is it required to study further to identify the change of dominance of frequency during the combustion.
Aircraft configuration selection method using the airworthiness certification and the decision making process
Yoon, Jung-Won ; Bae, Bo-Young ; Lee, Jae-Woo ; Byun, Yung-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 467~476
DOI : 10.5139/JKSAS.2010.38.5.467
For the very light jet aircraft design, the design baseline configuration has been selected using the logical decision making process, and the design optimization problem is formulated by considering the airworthiness regulations as design constraints. Airworthiness regulations are the minimum requirements for the safe aircraft flight and must be considered from the conceptual design stage. After carefully selecting the airworthiness constraints and the user specified requirements, a series of design making models including the affinity diagram, nested column diagram, quality function deployment (QFD), Pugh concept selection matrix, are used to find and evaluate alternative configuration baselines. From the feasible design space searching process, the best altenative design, which satisfies the airworthiness constraints while excluding the user subjective decisions as much as possible, has been successfully derived.
Assessment of Self-sealing Performance of the Fuel Tank of the Rotorcraft against Gunfire Projectiles
Kim, Hyun-Gi ; Kim, Sung-Chan ; Lee, Jong-Won ; Hwang, In-Hee ; Hue, Jang-Wook ; Shin, Dong-Woo ; Jung, Tae-Kyung ; Ha, Byoung-Geun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 477~481
DOI : 10.5139/JKSAS.2010.38.5.477
Some rotorcraft fuel tanks are required to be self-sealing and crashworthy for enhancing the survivability of crews. Self-sealing capability prevents the fuel leakage through contacting fuel with self-sealing material when the tank wall is penetrated by projectiles such as bullets. US army established MIL-DTL-27422D which specifies the detail requirements related to gunfire resistant fuel tank especially for military rotorcraft. The Fuel tanks for Korea Helicopter Program have been developed in accordance with MIL-DTL-27422D. The Self-sealing capability of the fuel tanks has been confirmed by the gunfire resistance test which specified on the MIL-DTL-27422D.
Ground Vibration Tests of SmartUAV Airframe Structure
Jeon, Byoung-Hee ; Kang, Hui-Won ; Lee, Jung-Jin ; Lee, Young-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 482~489
DOI : 10.5139/JKSAS.2010.38.5.482
This paper describes the test procedure, instrumentation, verification methodology and the results of the ground vibration test(GVT) and force vibration test(FVT) of the SmartUAV aircraft to estimate experimentally dynamic characteristics of the aircraft. Bungee cords are used to emulate free-free boundary conditions of the test aircraft. The SmartUAV is excited by three shakers and one-hundred frequency response functions(FRF`s) is measured. The FRF`s are reduced and analyzed to identify the dynamics parameters of the SmartUAV. To extract modal parameters of the SmartUAV such as, natural frequencies and damping ratios, the poly-reference least square complex exponential method is used in the time domain. The mode shape coefficients are estimated with the least squares frequency domain method to identify the vibration modes. The FVT was performed by fixed sine frequency with three shakers on the x, y and z direction and vibration characteristics of structures and detail equipments are measured.
Tracking of ground objects using image information for autonomous rotary unmanned aerial vehicles
Kang, Tae-Hwa ; Baek, Kwang-Yul ; Mok, Sung-Hoon ; Lee, Won-Suk ; Lee, Dong-Jin ; Lim, Seung-Han ; Bang, Hyo-Choong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 490~498
DOI : 10.5139/JKSAS.2010.38.5.490
This paper presents an autonomous target tracking approach and technique for transmitting ground control station image periodically for an unmanned aerial vehicle using onboard gimbaled(pan-tilt) camera system. The miniature rotary UAV which was used in this study has a small, high-performance camera, improved target acquisition technique, and autonomous target tracking algorithm. Also in order to stabilize real-time image sequences, image stabilization algorithm was adopted. Finally the target tracking performance was verified through a real flight test.
Ground Stations of Korean Deep Space Network for Lunar Explorations
Kim, Sang-Goo ; Yoon, Dong-Weon ; Hyun, Kwang-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 499~506
DOI : 10.5139/JKSAS.2010.38.5.499
Many countries of the world have been launched the competition of space development and Korea also has a plan for the launch of Lunar orbiter in 2020 and Lunar lander in 2025 for Lunar explorations. For the success of the planned Lunar exploration, we need to enhance the required deep space communication technologies. To achieve our goals, we should develop space communications system and Korean DSN (deep space network) based on experiences and technologies through cooperation with the advanced countries in the field of deep space exploration. In this paper, we investigate overseas DSNs and deep space communication systems, and present the link margin and other technical requirements for successful DSN deployment. In addition, we propose a best strategy to secure domestic ground stations for the Korean Lunar exploration missions.
Study on Power Analysis and Test Verification for STSAT-2 Solar Array
Park, Je-Hong ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 5, 2010, Pages 507~517
DOI : 10.5139/JKSAS.2010.38.5.507
The KOREAN AIR - R&D Center has developed a solar array for STSAT-2 Flight Model, SaTReC-KAIST, using a fully localized technology and has verified the performance through a launch vibration test, orbit environment test and electrical performance test. The solar array will be launched at NARO Space Center by KSLV-I which is the first Korean launch vehicle, in May 2010. In this paper, a current-voltage curve that shows the power characteristics of solar arrays was derived by applying elements that affects the power performance of STSAT-2`s solar arrays to the solar cell equivalent models. The result was compared to LAPSS test results, and accuracy of the solar cell equivalent model and the power performance simulation has been analyzed.