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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 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
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Study of Neural Network Training Algorithm Comparison and Prediction of Unsteady Aerodynamic Forces of 2D Airfoil
Kang, Seung-On ; Jun, Sang-Ook ; Park, Kyung-Hyun ; Jeon, Yong-Hee ; Lee, Dong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 425~432
DOI : 10.5139/JKSAS.2009.37.5.425
In this study, the ability of neural network in modeling and predicting of the unsteady aerodynamic force coefficients of 2D airfoil with the data obtained from Euler CFD code has been confirmed. Neural network models are constructed based on supervised training process using Levenberg-Marquardt algorithm, combining this into genetic algorithm, hybrid genetic algorithm and the efficiency of the two cases are analyzed and compared. It is shown that hybrid-genetic algorithm is more efficient for neural network of complex system and the predicted properties of the unsteady aerodynamic force coefficients of 2D airfoil by the neural network models are confirmed to be similar to that of the numerical results and verified as suitable representing reduced models.
A Study on the Effective Interpolation Methods to the Fluid-Structure Interaction Analysis for Large-Scale Structure
Lee, Ki-Du ; Lee, Young-Shin ; Kim, Dong-Soo ; Lee, Dae-Yearl ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 433~441
DOI : 10.5139/JKSAS.2009.37.5.433
Generally, the events in nature have multi-disciplinary characteristics. To solve this problems, these days loosely coupled methods are widely applied because of advantage of solvers which are already developed and well proved. Those solvers use different mesh system, so transformation and mapping of data are vital in the field of fluid-structure interaction(FSI). In this paper, the interpolation of deformation which is used globally and compactly supported radial basis functions(RBF), and mapping of force which use principle of virtual work are examined for computing time and accuracy to compare ability with simple 3-D problem. As the results, interpolation scheme of compactly supported radial basis functions are useful to interpolation and mapping for large-scale airplane in FSI with a k-dimensional tree(kd-tree) which is a space-partitioning data structure for organizing points in a k-dimensional space.
A Study on Calculation of Cross-Section Properties for Composite Rotor Blades Using Finite Element Method
Park, Il-Ju ; Jung, Sung-Nam ; Cho, Jin-Yeon ; Kim, Do-Hyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 442~449
DOI : 10.5139/JKSAS.2009.37.5.442
A two-dimensional cross-section analysis program based on the finite element method has been developed for composite blades with solid, thin-walled and compound cross-sections. The weighted-modulus method is introduced to determine the laminated composite material properties. The shear center and the torsion constant for any given section are calculated according to the Trefftz` definition and the St. Venant torsion theory, respectively. The singular value problem of cross-section stiffness properties faced during the section analysis has been solved by performing an eigenvalue analysis to remove the rigid body mode. Numerical results showing the accuracy of the program obtained for stiffness, offset and inertia properties are compared in this analysis. The current analysis results are validated with those obtained by commercial software and published data available in the literature and a good correlation has generally been achieved through a series of validation study.
Performance Investigation of Semi-Active Damper Considering Mass Modeling of Functional Fluid
Oh, Hyun-Ung ; Choi, Young-Jun ; Lee, Kyong-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 450~456
DOI : 10.5139/JKSAS.2009.37.5.450
Semi-active vibration control is one of the attractive control methods for space application due to its robustness as passive damping system and much higher damping performance than passive system. In this paper, performance investigation of semi-active damper considering a mass modeling of functional fluid inside of the damper has been performed. Numerical investigation results confirmed that the damper model considering the fluid mass is effective for vibration suppression performance at a relatively low viscosity range of functional fluid. Based on the analysis results, design method to enhance the performance of semi-active damper has been proposed.
Non-explosive Low-shock Separation Device for small satellite
Park, Hyun-Jun ; Tak, Won-Jun ; Han, Bum-Ku ; Kwag, Dong-Gi ; Hwang, Jai-Hyuk ; Kim, Byung-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 457~463
DOI : 10.5139/JKSAS.2009.37.5.457
This paper describes the development of non-explosive separation(NES) device which can be equipped on a small satellite. It comprises mechanism itself and spring-type shape memory alloy(SMA) actuator. In order to design SMA actuator properly, the necessary actuation force is measured. Based on that result, SMA actuator is designed and fabricated. Finally, SMA actuator and the proposed mechanism are integrated. In order to evaluate performance of the developed NES, we carried out a response time test, preload test and shock level test. In near future, we expect to replace the imported NES device with the developed device.
Fault Tolerant Controller Design for Supersonic Advanced Trainer Using Model Following Adaptive Technique
Kim, Seung-Keun ; Lee, Ho-Jin ; Yoon, Seung-Ho ; Han, Young-Su ; Kim, You-Dan ; Kim, Chong-Shup ; Cho, In-Je ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 464~469
DOI : 10.5139/JKSAS.2009.37.5.464
In this study, a new fault tolerant controller based on a model following adaptive technique is applied to the reconfiguration mode of supersonic advanced trainer. The designed controller is applied to the flight control system of high performance aircraft. To verify the performance of the proposed controller, numerical simulations are executed using a non-realtime nonlinear verification tool.
Optical Head Tracker using Pattern Matching for Initial Attitude
Kim, Young-Il ; Park, Chan-Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 470~475
DOI : 10.5139/JKSAS.2009.37.5.470
This paper is the study which is head tracker using pattern matching. Proposal algorithm obtains initial attitude of head tracker using pattern matching. Optical head tracker consists of infrared LEDs(features) which are attached helmet as pattern, stereo infrared cameras. Proposal algorithm analyzes patterns by error rate of feature distance and estimates feature characteristic number. Initial attitude of head tracker is obtained to compare map data and feature characteristic number.
Numerical Study of the effect of pintle shape on the thrust level
Kim, Joung-Keun ; Park, Jong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 476~482
DOI : 10.5139/JKSAS.2009.37.5.476
The effect of pintle shape on the thrust level of pintle-nozzle Solid Rocket Motor(PNSRM) was studied numerically using the Spalart-Allmaras turbulent model of Fluent. Mass flow rate of PNSRM was always less than theoretical value and the extent of decrease in mass flow rate grew in the large pintle because of increase in the relative boundary layer thickness between pintle body and nozzle wall. The bigger pintle size was, the more thrust of pintle tip pressure was obtained. Meanwhile the more thrust of nozzle and chamber pressure decreased. Hence, total thrust of big pintle was less than a small pintle under same throat area condition. Specific impulse was relatively flat for all pintle shape.
Cavitation in Fuel Pump with 2D Cascade Modeling
Quangnha, Thai ; Lee, Chang-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 483~489
DOI : 10.5139/JKSAS.2009.37.5.483
A CFD code was developed to investigate the inception of cavitation around impeller blades of centrifugal fuel pump using two dimensional cascade modeling. With the verification test for numerical validity of the developed code, the prediction of the onset of cavitation was made for the configuration of a newly designed KHP fuel pump. The calculation results show impeller design was free of cavitation if the pump operates within the operational temperature and rotational speed range. However, the cavitation would be relatively easy to occur at off design region of fuel pump where the rotational speed is higher than design limit. Specially, the onset of cavitation is sensitively dependent on the increase in fuel temperature while the decrease in temperature will reduce the possibility of cavitation inception in the pump.
Development of Hall-effect Thruster for Orbit Correction and Transfer of Small Satellites
Seon, Jong-Ho ; Kang, Seong-Min ; Kim, Yon-Ho ; Chun, Eun-Yong ; Choe, Won-Ho ; Lee, Jong-Sub ; Seo, Mi-Hui ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 490~495
DOI : 10.5139/JKSAS.2009.37.5.490
A small Hall-effect thruster with a thrust range near 10 mN and a specific impulse of about 1500 s has been designed to control or maintain the orbits of small satellites. The thruster system consists of a hall-effect thruster head, a power processing unit and a Xenon (Xe) gas feed system. The total mass, the consumed electric power and the efficiency of the thruster are approximately 10 kg, 300W and 30%, respectively. Analyses results that support the selection of the thruster for small satellites are provided along with a brief description of the thruster system.
Development of the Head Unit of a 300 W Cylindrical Hall Thruster for Small Satellites
Kang, Seong-Min ; Kim, Youn-Ho ; Seon, Jong-Ho ; Lee, Jong-Sub ; Seo, Mi-Hui ; Choe, Won-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 496~501
DOI : 10.5139/JKSAS.2009.37.5.496
The thruster head unit of a 300 W cylindrical Hall thruster was developed for the propulsion system of small satellites. The magnetic topology in the thruster channel is a key parameter to achieve high performances. Two types of magnetic circuit structures were designed and manufactured to compare the thrust levels and efficiencies. Also the endurance test was conducted to measure the stable operation duration of the thruster head and to find degree of erosion after extended operation.
Fault Detection Method of Laser Inertial Navigation System Using FFT
Yoo, Hae-Seong ; Kim, Cheon-Joong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 502~510
DOI : 10.5139/JKSAS.2009.37.5.502
Laser Inertial Navigation System(LINS) consists of Ring Laser Gyroscopes(RLG) and accelerometers. RLG has a lock-in region in which there is zero output for input angular rates less than 0.1deg/sec. The lock-in region is generated by the imperfect mirrors in RLG. To avoid the lock-in region, sinusoidal motion which is called dither motion is applied on RLG. Therefore without the fault in LINS, the dither motion must be measured by RLG/accelerometer. In this paper, we propose the method to detect the fault of LINS through checking out whether or not the dither motion is always measured by RLG/accelerometer using the Fast Fourier Transformation(FFT) on the real time. The feasibility of the fault detection method proposed in this paper is verified through the stationary and van test.
Development of Servo Type Angle-of-Attack Sensor for UAV
Park, Mi-Hyun ; Kim, Sung-Su ; Ryoo, Chang-Kyung ; Choi, Kee-Young ; Park, Choon-Bae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 5, 2009, Pages 511~517
DOI : 10.5139/JKSAS.2009.37.5.511
A servo type angle of attack sensor using the null-seeking method is designed and its characteristics are analyzed in this study. Angle-of-attack in the null-seeking method is given by the probe rotation angle with respect to the body reference line when pressure difference measured in two holes on the probe becomes zero. This method provides highly accurate and uniform angle-of-attack measurements over all range. Hence, this kind of angle-of-attack sensor is adequate for unmanned aerial vehicles(UAVs). In this paper, we first analyze the requirements for developing angle-of-attack sensors. And the servo type angle-of-attack sensor is then designed and fabricated. The on-board angle-of-attack calculation algorithm is also developed. Finally, the characteristics of the developed angle-of-attack sensor are identified through MATLAB Simulink and wind tunnel tests.