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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 40, Issue 12 - Dec 2012
Volume 40, Issue 11 - Nov 2012
Volume 40, Issue 10 - Oct 2012
Volume 40, Issue 9 - Sep 2012
Volume 40, Issue 8 - Aug 2012
Volume 40, Issue 7 - Jul 2012
Volume 40, Issue 6 - Jun 2012
Volume 40, Issue 5 - May 2012
Volume 40, Issue 4 - Apr 2012
Volume 40, Issue 3 - Mar 2012
Volume 40, Issue 2 - Feb 2012
Volume 40, Issue 1 - Jan 2012
Selecting the target year
Reduced Order Modeling of Backward-Facing-Step Flow Field
Lee, Jin-Ik ; Lee, Eun-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 833~839
DOI : 10.5139/JKSAS.2012.40.10.833
In this paper, we analyze the reconstruction error in the modeling of flow field on BFS(Backward Facing Step). In order for the mathematical modelling of a density on the field, the spatial and temporal modes are extracted by POD(Proper Orthogonal Decomposition) method. After formulating the modeling error, we summarize the relationship between the energy strength and the reconstruction errors. Moreover the allowable modeling error limits in the flow control point of view are confined by analysing in the frequency domain as well as time domain of the reconstructed data.
ARX Design Technique for Low Order Modeling of Backward-Facing-Step Flow Field
Lee, Jin-Ik ; Lee, Eun-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 840~845
DOI : 10.5139/JKSAS.2012.40.10.840
An ARX(Auto-Regressive eXogenous) modeling technique for vortex dynamics in the BFS(Backward Facing Step) flow field is proposed in this paper. In order for the modeling of the dynamics, the spatial and temporal modes are extracted through POD(Proper Orthogonal Decomposition) analysis. Determining the orders of the inputs and outputs for an ARX structure is carried out by the spectrum analysis and temporal mode analysis, respectively. The order of input delay terms is also determined by the flow velocity. Finally the coefficients of the ARX model are designed by using an artificial neural network.
Experimental Study on Aerodynamic Characteristics of Morphing Airfoil Configuration
Ko, Seung-Hee ; Bae, Jae-Sung ; Kim, Hark-Bong ; Roh, Jin-Ho ; Ahn, Seok-Min ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 846~852
DOI : 10.5139/JKSAS.2012.40.10.846
The present paper is the preliminary study of the development of a morphing aircraft wing and investigates experimently the aerodynamic characteristics of a base airfoil and a morphing airfoil. The wind tunnel tests are conducted for a base Clark-Y airfoil, an airfoil with a mechanical flap, and a morphing airfoil. Lifts, drags, and pitching moments are measured by using a three-axis load cell and they are calibrated by considering solid blockage and wake blockage. The wind tunnel tests are conducted for various air speeds, Reynolds` numbers, and angles of attack. The experimental results show that the aerodynamic characteristics of the morphing airfoil in lift-drag and lift-pitching moment are better than those of the airfoil with a mechanical flap.
Performance Analysis of a Precise Explicit Guidance Algorithm for Space Launch Vehicles
Song, Eun-Jung ; Cho, Sang-Bum ; Park, Chang-Su ; Roh, Woong-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 853~861
DOI : 10.5139/JKSAS.2012.40.10.853
This paper considers one of the explicit guidance algorithms, which has been proposed by Jaggers, to determine the closed-loop guidance algorithm for upper stages of a 3-staged space launch vehicle. Its commanded thrust vector is closer to the optimal solution when compared with that obtained by using the well-known Powered Explicit Guidance (PEG), which has been developed through the Space Shuttle program. Its performance is evaluated here by applying for guidance of the launcher during the second and third stages. Furthermore, to generate more precise guidance commands, it is attempted not to use the approximate formulas for the derivation of the original guidance law, and it is shown that performance is improved in comparison with the original.
Numerical Simulations on Combustion Considering Propellant Droplet Atomization and Evaporation of 500 N Class Hydrogen Peroxide / Kerosene Rocket Engine
Ha, Seong-Up ; Lee, Seon-Mi ; Moon, In-Sang ; Lee, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 862~871
DOI : 10.5139/JKSAS.2012.40.10.862
The numerical simulations on 500-N class rocket engine using 96% hydrogen peroxide and kerosene have been conducted, considering atomization, evaporation, mixing and combustion of its propellants. The grid containing 1/6 part of combustion chamber has been generated and it is assumed that 3 kinds of liquid-phase propellants (kerosene, hydrogen peroxide and water) were injected as hollow cone spray pattern, using Rosin-Rammler function for distribution of droplet diameter. For the calculation of combustion the eddy-dissipation model was applied. Owing to small size of combustion chamber and large specific heat / latent heat of hydrogen peroxide and water the propulsion characteristics were highly influenced by the size of droplet particles, and in this analysis the engine with droplet particles of 30 micron in average has shown the best propulsion performance.
Development and Design Verification of Thermal Control Subsystem for EOS-C Ver.3.0 Flight Model
Chang, Jin-Soo ; Yang, Seung-Uk ; Kim, Ee-Eul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 872~881
DOI : 10.5139/JKSAS.2012.40.10.872
The Flight Model (FM) of a high-resolution electro-optical camera (EOS-C Ver.3.0), the mission payload of an Earth observation satellite, was successfully developed by Satrec Initiative. We designed it to give improved thermal representatives compared with the Structural-Thermal Model (STM) by optimizing the thermal characteristics based on the STM thermal vacuum test results. We developed the FM and verified the workmanship by performing the acceptance level thermal vacuum test. We also conducted the verification of its Thermal Mathematical Model (TMM) by the thermal balance test. As the result, it was confirmed that TMM faithfully represents the thermal characteristics of the EOS-C Ver.3.0 FM.
Analysis of the Aerodynamic Characteristics of `Buhwal` Airplane
Noh, Kuk-Hyeon ; Cho, Hwan-Kee ; Cheong, Seong-Gee ; Cho, Tae-Hwan ; Kim, Byung-Soo ; Park, Chan-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 882~887
DOI : 10.5139/JKSAS.2012.40.10.882
This paper describes on the aerodynamic characteristics of the first domestically manufactured aircraft, Buhwalho, in Korea. The computational fluid dynamics(CFD) calculations and wind tunnel test were utilized to investigate the basic aerodynamic characteristics of aircraft with control surface deflections and attitude changes. Variations of lift, drag and pitching moment due to angles of attack and control surface deflections were analyzed and also flight stability due to side force, yawing and rolling moments caused by the change of sideslip angles, rudder and aileron deflections were discussed. Through this study, the meaningful aerodynamic data by CFD calculations and wind tunnel tests were obtained and the flight characteristics based on these data were confirmed accordingly by the flight tests.
Application of Wind Tunnel Testing on the Dynamic Stability Derivatives of a Rocket Model
Cho, Hwan-Kee ; Sung, Hong-Gye ; Kim, Jin-Kon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 888~893
DOI : 10.5139/JKSAS.2012.40.10.888
This paper described the wind tunnel testing apparatus and technique to acquire the dynamic stability derivatives of large slenderness ratio air vehicle such as the guided missiles or rockets. There have been few difficulties in conducting wind tunnel testing for slender long rocket due to the size limitation of the test section size and the installation of oscillation equipments. In this study, the dynamic stability balance was used as the wind tunnel technique for obtaining the dynamic stability derivatives. Through the wind tunnel testing, the experimental apparatus for slender air vehicle`s oscillation is established. The measured data showed that it is possible to acquire the dynamic stability derivatives of large slenderness ratio rocket, properly.
An Experimental Study on Roll-Damping Characteristics of a Finned Spinning Projectile
Oh, Se-Yoon ; Lee, Do-Kwan ; Kim, Sung-Cheol ; Kim, Sang-Ho ; Ahn, Seung-Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 894~900
DOI : 10.5139/JKSAS.2012.40.10.894
The purpose of this research is to investigate the dynamic roll-damping characteristics of a spin-stabilized projectile in wind-tunnel testing. In the present work, the high-speed wind-tunnel tests for the roll-damping measurements were conducted on a finned spin-stabilized projectile model in the Agency for Defense Development`s Trisonic Wind Tunnel at spin rates about 8,000 rpm. The test Mach numbers ranged from 0.6 to 0.9, and the angles of attack ranged from 0 to +15 deg. The evaluation of the bearing friction parameter was also conducted to eliminate the tare damping moment from the aerodynamic damping moment.
The study on characteristics of solid-state NaBH
hydrogen generation and supply system for fuel cell UAV
Lee, Chung-Jun ; Kim, Tae-Gyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 901~909
DOI : 10.5139/JKSAS.2012.40.10.901
This paper describes characteristics of solid-state
hydrogen generation and supply system for fuel cell UAV. Flow rate and pressure of the generated hydrogen were dramatically changed during
decomposition using acid. Hydrogen supply was stabilized by a self-pressurized reactor, and hydrogen stabilization method was introduced. For hydrogen generation in below zero-temperature, hydrochloric acid was diluted by propylene glycol-water mixtures. Solid-state
hydrogen generation and supply system was designed. Basic operation experiments was performed to reveal the characteristics of this hydrogen generation system.
An Evaluating Analysis of Installing Type of EOTS for The Boramae Fighter
Kang, Chi-Hang ; Oh, Seung-Hyun ; Kang, Hee-Chang ; Cheon, Ho-Jeong ; Lee, Beom-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 10, 2012, Pages 910~915
DOI : 10.5139/JKSAS.2012.40.10.910
In this paper, the loading methods of EOTS for an exploratory developing fighter were analysed by the technical characteristics of it`s operation, maintenance, engineering technology and development cost. By the analysis of operational ability evaluation, the internal type had the merits of stealth function, but the external loading type was preferable to certificate the accessibility, install/detach, compatibility and interoperability with the existing fighter aircraft. From the results of 17 items of technology and development cost evaluation, we found out that the internal type had the advantage of small sizing lightweight, but the external type was highly estimated in the field of application of domestic technology, cost reduction and technical stability for achievement of performance.