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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 41, Issue 12 - Dec 2013
Volume 41, Issue 11 - Nov 2013
Volume 41, Issue 10 - Oct 2013
Volume 41, Issue 9 - Sep 2013
Volume 41, Issue 8 - Aug 2013
Volume 41, Issue 7 - Jul 2013
Volume 41, Issue 6 - Jun 2013
Volume 41, Issue 5 - May 2013
Volume 41, Issue 4 - Apr 2013
Volume 41, Issue 3 - Mar 2013
Volume 41, Issue 2 - Feb 2013
Volume 41, Issue 1 - Jan 2013
Selecting the target year
Investigation of the Performance of Anti-Icing System of a Rotorcraft Engine Air Intake
Ahn, Gook-Bin ; Jung, Ki-Young ; Jung, Sung-Ki ; Shin, Hun-Bum ; Myong, Rho-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 253~260
DOI : 10.5139/JKSAS.2013.41.4.253
Ice accretions on the surface around a rotorcraft air intake can deteriorate the safety of rotorcraft due to the engine performance degradation. The computational simulation based on modern CFD methods can be considered extremely valuable in analyzing icing effects before exact but very expensive icing wind tunnel or in-flight tests are conducted. In this study the range and amount of ice on the surface of anti-icing equipment are investigated for heat-on and heat-off modes. It is demonstrated through the computational prediction and the icing wind tunnel test that the maximum mass and height of ice of heat-on mode are reduced about 80% in comparison with those of heat-off mode.
An Experimental Study on Flapping Motion of Forward Flight Condition used to Articulated Hub Rotor
Ryi, Jae-Ha ; Back, Dong-Min ; Rhee, Wook ; Choi, Jong-Soo ; Song, Keun Woong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 261~267
DOI : 10.5139/JKSAS.2013.41.4.261
In this paper, wind tunnel test and analytical prediction are compared for result of flapping motion in helicopter forward flight condition. Tests were performed at low speed wind tunnel at Chungnam National University, test section of wind tunnel has 1.8 by 1.8 meter open-jet test section area. According to the results of measured data for aerodynamic performance of model rotor in forward flight. It has to observed the difference of analytical and measured results of power coefficient for fixed thrust coefficient. And calculated and measured data of helicopter rotor flapping angles in forward flight are compared for a model rotor in a wind tunnel. A test was conducted to verify the measured data of coning and lateral/longitudinal flapping angle with predicted values.
Optimization of Radar Absorbing Structures for Aircraft Wing Leading Edge
Jang, Byung-Wook ; Park, Sun-Hwa ; Lee, Won-Jun ; Joo, Young-Sik ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 268~274
DOI : 10.5139/JKSAS.2013.41.4.268
In this paper, objective functions are defined for optimization of radar absorbing structures (RAS) on the aircraft wing leading edge. RAS is regarded as a single layer structure made of dielectrics. Design variables are the real and imaginary parts of complex permittivity. Reflection coefficient(RC) and radar cross section(RCS) are used in the objective function respectively. Transmission line theory is employed to calculate the RC. The RCS is evaluated by using physical optics(PO) for a leading edge part model. Genetic algorithm(GA) is used to perform optimization procedures. The radar absorbing performance of designed RAS is assessed by the RCS of a wing which has RAS on the leading edge.
A Study on the Structural Optimum Design Method of Composite Rotor Blade Cross-Section using Genetic Algorithm
Won, You-Jin ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 275~283
DOI : 10.5139/JKSAS.2013.41.4.275
In this paper, the structural optimum design method of composite rotor blade cross-section was investigated with the genetic algorithm. An auto-mesh generation program was developed for iterative calculations of optimum design, and stresses in the blade cross-section were analyzed by VABS (variational asymptotic beam sectional analysis) program. Minimum mass of rotor blade was defined as an object function, and stress failure index, center mass and blade minimum mass per unit length were chosen as constraints. Finally, design parameters such as the thickness and layup angles of a skin, and the thickness, position and width of a torsion box were determined through the structural optimum design method of composite rotor blade cross-section presented in this paper.
Design of Nonlinear Unknown Input Observer by SDRE Method and Fault Detection of Reaction Wheels
Yoon, Hyungjoo ; Jin, Jaehyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 284~290
DOI : 10.5139/JKSAS.2013.41.4.284
The authors propose a nonlinear unknown input observer to estimate the angular speed of a satellite and to detect faults of reaction wheels. Input values are necessary to estimate the angular speed. Therefore, estimation errors are inevitable if faults occur in actuators or reaction wheels. Unknown input observers are useful to estimate the states of a system without being affected by unknown faults. The authors have designed a nonlinear unknown input observer by using the SDRE method and verified the proposed observer via numerical simulations. In spite of various and simultaneous faults, we have estimated the states and detected faults exactly by the proposed nonlinear unknown input observer.
Hybrid control of the swash plate-type variable displacement hydraulic piston pump for an EHA
Kwon, Yong-Cheol ; Hong, Yeh-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 291~298
DOI : 10.5139/JKSAS.2013.41.4.291
In this paper a new hybrid-type control system is proposed which reduces the pump speed of an electro-hydraulic actuator consisting of a pressure-compensated variable displacement piston pump and a valve-controlled hydraulic cylinder, whenever the flow rate demand is low. In order to avoid interfering with the pressure regulator which also has an effect on swash plate angle, the pump speed is changed in proportion to the mean value of the speed component of position commands. Additionally a pressure switch is employed to prevent the system pressure from getting lower than a reference value. Based on computer simulation & experimental results, it is shown that the hybrid control can save the idling power up to 44% at a stand-by mode by reducing the pump speed from 1,800 rpm to 600 rpm without affecting the dynamic response of the electro-hydraulic actuator.
Performance Evaluation of 1 N Class HAN/Methanol Propellant Thruster
Lee, Jeongsub ; Huh, Jeongmoo ; Cho, Sungjune ; Kim, Suhyun ; Park, Sungjun ; Kim, Sukyum ; Kwon, Sejin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 299~304
DOI : 10.5139/JKSAS.2013.41.4.299
The HAN which is an ionic liquid is a non-toxic monopropellant with high storability, and its specific impulse can be increased by blending methanol, thereby it can substitute the hydrazine. The HAN was synthesized by acid-base reaction of hydroxylamine and nitric acid, and the blending ratio of HAN and methanol is 8.2:1. The iridium catalyst was used to decompose the HAN, and 1 N class thruster with shower head type injector having one orifice was used to evaluate the HAN/Methanol propellant. The thermal stability of distributor was increased by using ceramic material to endure the high temperature of product gas. The preheating temperature of catalyst should be
at least for the complete decomposition. The feeding pressure should be increased to increase the
efficiency, thereby the decomposition performance was decreased upstream catalyst, and the performance of thruster was decreased. The fine metal mesh was inserted after the injector to improve the atomization of propellant, thereby it can settle the performance decrease problem. The phenomenon of performance decrease was remarkably improved owing to the insertion of fine metal mesh.
Development of Aircraft and Radar Simulation for Air Traffic Control Training System
Oh, Hye-Ju ; Cho, Sang-Ook ; Choi, Keeyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 305~313
DOI : 10.5139/JKSAS.2013.41.4.305
This paper presents a simulation system for air traffic control (ATC) training. The structure of the ATC is analyzed to define simulation components to be developed. Requirements that must be satisfied by a training simulator are also identified. The results were reflected in the design of the simulator. The training simulator is composed of three modules same as in real life : air traffic controller, aircraft, radar. Each developed module performs the strict unit tests and combine test based on the scalability, ease, real-time, the operating range of the algorithm derived from the requirements. The simulation system can be connected to an actual ATC, and used to validate the ATC system. At peak load, 1200 aircraft and 30 radars can be operated simultaneously.
Tests of a Guidance Kit for Air-to-Surface Bomb
Lee, Inwon ; Lee, Kidu ; Park, Youngkuen ; Lim, Sangsoo ; Baek, Seungwoock ; Lee, Daeyearl ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 314~318
DOI : 10.5139/JKSAS.2013.41.4.314
Tests and evaluations following the U.S. MIL-HDBK/STANDARD were successfully conducted to assure the performance of the air-to-surface guidance kit which was developed first in Korea. Various ground tests confirmed the operation capability and reliability of the guidance kit, and flight tests proved very good mid-range gliding performance and accuracy of the gliding bomb which was a general purpose bomb with the guidance kit.
Analysis on Orbital Dynamics Operation Results of KOMPSAT-3 during Early Phase after Launch
Jung, Ok-Chul ; Yim, Hyeonjeong ; Chung, Dae-Won ; Kim, Eun-Kyou ; Kim, Hak-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 319~326
DOI : 10.5139/JKSAS.2013.41.4.319
This paper describes the orbital dynamics operation results for the launch and early operations phase (LEOP) of KOMPSAT-3, which was successfully launched on May 18, 2012. At the initial phase, operational orbit determination was carried out using ground tracking data and GPS navigation solution. And, both in-plane and out-of plane maneuvers were executed in order to change the orbit from the injection orbit to the mission orbit. In addition, the accuracy of precise orbit determination was indirectly evaluated by overlapping method using GPS raw data of KOMPSAT-3 and international GNSS service data from worldwide-distributed ground stations. Currently, KOMPSAT-3 is operated in pre-defined mission orbit, and its various kinds of orbit data are generated and distributed to support the normal mission operations.
Design of Solar Tracking CanSat
Jung, In-Jee ; Moon, Ji-Hwan ; Kim, Min-Soo ; Lim, Byoung-Duk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 4, 2013, Pages 327~334
DOI : 10.5139/JKSAS.2013.41.4.327
In August 2012 the first CanSat competition was hosted by the Satellite Research Center of KAIST under auspice of the Ministry of Education, Science and Technology. The present authors team won the first prize in the university session. In this paper the overall procedure of the CanSat project presented from the conceptual design stage to the final launch test. As the compulsory mission CanSat should send GPS data and attitude information to the ground station which in practice was performed via Bluetooth channel. In addition our CanSat is designed to trace the sun for the solar panels supplying electric power of satellite. IMU and servo motors are used for the attitude control in order that the solar sensor of the CanSat is always direct towards the sun. Launching of CanSat was simulated by dropping from a balloon at the height of around 150m via parachute. Launching test results showed that the attitude control of the CanSat and its solar sensing function were successful.