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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 43, Issue 12 - Dec 2015
Volume 43, Issue 11 - Nov 2015
Volume 43, Issue 10 - Oct 2015
Volume 43, Issue 9 - Sep 2015
Volume 43, Issue 8 - Aug 2015
Volume 43, Issue 7 - Jul 2015
Volume 43, Issue 6 - Jun 2015
Volume 43, Issue 5 - May 2015
Volume 43, Issue 4 - Apr 2015
Volume 43, Issue 3 - Mar 2015
Volume 43, Issue 2 - Feb 2015
Volume 43, Issue 1 - Jan 2015
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Numerical Study on the Side-Wind Aerodynamic Forces of Chambered 3-D Thin-Plate Rigid-Body Model
Shin, Jong-Hyeon ; Chang, Se-Myong ; Moon, Byung-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 97~108
DOI : 10.5139/JKSAS.2015.43.2.97
In the design of sailing yachts, para-glider, or high-sky wind power, etc., the analysis of side-wind aerodynamic forces exerted on a cambered 3-D model is very important to predict the performance of various machinery systems. To understand the essential flow physics around the three-dimensional shape, simplified rigid-body models are proposed in this study. Four parameters such as free stream velocity, angle of attack, aspect ratio, and camber are considered as the independent variables. Lift and drag coefficients are computed with CFD technique using ANSYS-CFX, and the results with the visualization of post-processed flow fields are analyzed in the viewpoint of fluid dynamics.
A Study on Flow Characteristics of the Inlet Shape for the S-Duct
Lee, Jihyeong ; Choi, Hyunmin ; Ryu, Minhyoung ; Cho, Jinsoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 109~117
DOI : 10.5139/JKSAS.2015.43.2.109
Aircraft needs an inlet duct to supply the airflow to engine face. A fighter aircraft that requires low radar observability has to hide the engine face in the fuselage to reduce the Radar Cross Section(RCS). Therefore, the flow path of the inlet duct is changed into S-shape. The performance of the aircraft engine is known to be influenced by the shape and the centerline curvature of the S-Duct. In this study, CFD analysis of the RAE M 2129 S-Duct has been performed to investigate the influence of aspect ratio of inlet geometry. The performance of the S-Duct is evaluated in terms of the distortion coefficient. To simulate the flow under adverse pressure gradient better,
turbulence model is employed. The computational results are validated with the ARA experimental data. The secondary flow and the flow separation are observed for all computational cases, while the semi-circular geometry has been found to produce the best results.
Design of Single Layer Radar Absorbing Structures(RAS) for Minimizing Radar Cross Section(RCS) Using Impedance Matching
Jang, Byung-Wook ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 118~124
DOI : 10.5139/JKSAS.2015.43.2.118
The design of radar absorbing structures(RAS) is a discrete optimization problem and is usually processed by stochastic optimization methods. The calculation of radar cross section(RCS) should be decreased to improve the efficiency of designing RAS. In this paper, an efficient method using impedance matching is studied to design RAS for minimizing RCS. Input impedance of the minimal RCS for the specified wave incident conditions is obtained by interlocking physical optics(PO) and optimizations. Complex permittivity and thickness of RAS are designed to satisfy the calculated input impedance by a discrete optimization. The results reveal that the studied method attains the same results as stochastic optimization which have to conduct numerous RCS analysis. The efficiency of designing RAS can be enhanced by reducing the calculation of RCS.
UDRE Monitoring Analysis of Korean Satellite Navigation System
Park, Jong-Geun ; Ahn, Jongsun ; Heo, Moon-Beom ; Joo, Jung Min ; Lee, Kihoon ; Sung, Sangkyung ; Lee, Young Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 125~132
DOI : 10.5139/JKSAS.2015.43.2.125
This paper is about analysis of UDRE monitoring method for Korean Satellite navigation system, which is the correction parameter of satellite measurements. New receiver clock bias and tropospheric delay error estimation method to make pseudo-range residual for UDRE monitoring is proposed. Saastamoinen model and Neill mapping function are used for estimate the tropospheric delay and EKF is used for estimgate the receiver clock bias. Through the satellite measurements and regional weather data received directly from the domestic is using for UDRE monitoring analysis, more suitable UDRE monitoring threshold can be deducted and it is expected to be utilized for fault detection technique of Korean Satellite Navigation System.
Roll Angle Estimation of a Rolling Airframe Using a GPS and a Roll Rate Gyro
Hong, Ju-Hyeon ; Kim, Dusik ; Ryoo, Chang-Kyung ; Lee, Chang-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 133~140
DOI : 10.5139/JKSAS.2015.43.2.133
In this paper, a roll angle estimation method of a rolling airframe using a low grade GPS and a roll rate gyro is proposed. The strength of the received signal of the GPS antenna attached on the rolling airframe is maximized when the GPS satellite is placed on the plane determined by the x-axis of the rolling airframe and the GPS antenna axis. Under the assumption that the x-axis of the rolling airframe is coincident with its velocity vector, the roll angle of the rolling airframe is calculated from the relative position vector of the satellite to the GPS when the GPS signal strength becomes maximum. The Kalman filter combined with a roll rate gyro is introduced to increase the determination accuracy of the roll angle. The performance of the proposed method is verified via 6-DOF simulations.
Optimization of Sun-synchronous Spacecraft Constellation Orbits
Kim, Hwayeong ; No, Tae Soo ; Jung, Okchul ; Chung, Daewon ; Choi, Jin-Heng ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 141~148
DOI : 10.5139/JKSAS.2015.43.2.141
This paper presents a sun-synchronous orbit design which effectuvely includes the requirements derived from spacecraft to ground station contact and spacecraft to target image accessibility. For this purpose, operation parameters of multiple spacecraft are defined as Contact Overlap, Contact Overlap Gap, Access Overlap, Access Overlap Gap. These parameters are used to form a Figure of Merit that reflects the operational requirements. The Figure of Merit is optimized to increase the efficiency of operating multiple spacecraft in constellation and is used to determine the operational orbit of each spacecraft that constitutes the constellation.
Optimization of Thermo-optical Property for Electrostatic Actuating MEMS-based Variable Emissivity Radiator
Ha, Heon-Woo ; Kang, Soo-Jin ; Han, Sung-Hyeon ; Kim, Tae-Gyu ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 149~155
DOI : 10.5139/JKSAS.2015.43.2.149
MEMS-based louver and shutter type conventional variable emissivity radiators change their emissivity properties in accordance with a temperature condition to achieve efficient thermal control performance. However, there are some drawbacks such as a structural safety of the mechanical moving parts under sever launch environment and constant power consumption to maintain the intended emissivity. In this study, to overcome above drawbacks, we proposed a MEMS-based variable emissivity radiator, which can change the emissivity property according to the polarity change of electrodes by using electric charge of the bead. The effectiveness of the optimized radiator design has been demonstrated through the comparison of efficiency with the fixed emissivity radiator.
Development of Survivability Analysis Program for Atmospheric Reentry
Sim, Hyung-Seok ; Choi, Kyu-Sung ; Ko, Jeong-Hwan ; Chung, Eui-Seung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 156~165
DOI : 10.5139/JKSAS.2015.43.2.156
A survivability-analysis program has been developed to analyze the ground collision risk of atmospheric reentry objects, such the upper stages of a launch vehicle or satellites, which move at or near the orbital velocity. The aero-thermodynamic load during the free fall, the temperature variation due to thermal load, and the phase shift after reaching the melting point are integrated into the 3 degree-of-freedom trajectory simulation of the reentry objects to analyze the size and weight of its debris impacting the ground. The analysis results of the present method for simple-shaped objects are compared with the data predicted by similar codes developed by NASA and ESA. Also, the analysis for actual reentry orbital objects has been performed, of which results are compared with the measurement data.
A Study on Verify of UAV Flight Control Software Simulated Flight using Model-Based Development and X-Plane simulator
Han, Dong-In ; Kim, Young-Sik ; Lee, Chang-Yong ; Lee, Dae-Woo ; Cho, Kyeum-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 166~171
DOI : 10.5139/JKSAS.2015.43.2.166
This paper shows the design of operational flight program(OFP) using model-based design(MBD) method which is used in various engineering fields to reduce time and flight risks for development. The verification of OFP for DO-178C guidelines carry out by a model advisor function of simulink. The flight control logic on simulink is converted into C-language by auto code generation tool from, then it is implemented on 32bit digital signal processor(DSP). The verifications of flight control algorithm on various weather conditions are performed by the HILS system with Flight simulator program, X-plane.
Development of 100Nm-class Control Moment Gyroscopes for Industrial Applications
Lee, Seon-Ho ; Kim, Dae-Kwan ; Kim, Yong-Bok ; Yong, Ki-Lyuk ; Choi, Dong-Soo ; Park, Do-Hwan ; Kim, Il-Jong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 172~178
DOI : 10.5139/JKSAS.2015.43.2.172
The control moment gyroscope(CMG) which is well known as an effective high-torque-generating device is applicable to space vehicles, airplanes, ships, automobiles, robotics, etc. for attitude stabilization and maneuver. This paper deals with the overall details of 100Nm-class CMG development for various industrial applications, and provides the activities and results associated with the CMG system-level requirement analysis, the motor subsystem design/manufacturing/integration, the construction of ground support equipment, and the performance test and evaluation. The performance test reveals that the CMG generates the torque output more than 120Nm in as-designed operation of spin motor and gimbal motor.
Study on Methodology of Trade-Off for Space-borne FPA Thermal Design by Simplified Thermal Node Analysis
Chang, Jin-Soo ; Yang, Seung-Uk ; Kim, Jong-Un ; Kim, Ee-Eul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 2, 2015, Pages 179~185
DOI : 10.5139/JKSAS.2015.43.2.179
The main objective of thermal design for a space-borne FPA(Focal Plane Assembly) is to provide stable thermal environment during imaging operation and thus maintain the image quality. An FPA must be maintained within its operating temperature range and cooled down to its initial temperature soon enough for the next imaging operation. This paper describes the study result on performing trade-off studies for FPA thermal design by using simplified thermal node analysis about FPA preliminary design. It also describes the verification results of the study by comparing thermal analysis results and trade-off study results. According to results, we can conclude that this approach is useful for simple and quick trade-off studies without thermal analysis based on thermal math models.