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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
Aerodynamic Interference Effect of Aircraft Wing Tip Vortex in Formation Flight
Cho, Hwan-Kee ; Lee, Sang-Hyun ; Lee, Soontae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 849~854
DOI : 10.5139/JKSAS.2013.41.11.849
Experimental study was conducted to investigate aerodynamic interference effect of wing tip vortex in formation flight of high speed aircraft. In formation flight, wing tip vortex produced by leading aircraft can affect on the aerodynamic characteristics of trailing aircraft. The interference effect of flow is varied with distances between wing tips of leading and trailing aircraft. It is confirmed, in this study, that the interference of wing tip vortex generated from the leading aircraft makes the aerodynamic forces and moments of the trailing aircraft with the vertical or horizontal positions of the trailing aircraft. Especially, the lift coefficients of trailing aircraft were highly increased at y/b
Modeling of a Rotor System Incorporating Active Tab and Analysis of BVI Noise Reduction Characteristics
Kim, Do-Hyung ; Kang, Hee Jung ; Wie, Seong-Yong ; Kim, Seung-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 855~864
DOI : 10.5139/JKSAS.2013.41.11.855
Active tab is one of the promising technology for the BVI (blade-vortex interaction) noise reduction, and analysis of noise reduction performance is very important phase of the technology development. For the purpose of analysing the performance of noise reduction using active tab, CAMRAD II model for a model-scale rotor system was constructed utilizing structural design result and airfoil aerodynamic data generated by CFD (computational fluid dynamics) calculation. HHC strategy was applied to descent flight condition and air-load was calculated by CAMRAD II then variations of BVI noise was calculated by in-house program. Calculation result with respect to tab length and control phase changes showed BVI noise could be reduced by -3.3dB.
Analysis Methods of Wrinkle Prediction for Thin Membrane
Bae, Hongsu ; Woo, Kyeongsik ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 865~873
DOI : 10.5139/JKSAS.2013.41.11.865
In this paper, numerical methods for wrinkle prediction of thin membrane were studied by finite element analysis. Techniques using membrane and shell elements were applied for triangular membrane. In case of membrane element method, the wrinkling was accounted for by the wrinkle algorithm of property modification, which was implemented to ABAQUS as a user subroutine. In case of shell method, geometrically nonlinear post-buckling analysis was performed to obtain the wrinkle deformation explicitly. The wrinkling deformation was induced by seeding the mesh with a random geometric imperfection. The results were investigated focusing on the mesh convergence and the solution accuracy.
Estimation of Thermodynamic/Transport Properties of Kerosene using a 3-Species Surrogate Mixture
Joh, Miok ; Kim, Seong-Ku ; Choi, Hwan-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 874~882
DOI : 10.5139/JKSAS.2013.41.11.874
Kerosene(Jet A-1), one of the propellants for each stage`s engine of the Korea Space Launch Vehicle-II(KSLV-II), functions as coolant at the same time as it flows inside the cooling jacket of the combustion chambers and is injected through the film cooling holes. A physical surrogate mixture model to reproduce the thermophysical characteristics of Jet A-1 has been selected and the thermodynamic/transport properties of the model fuel under high pressure including supercritical conditions have been estimated using SUPERTRAPP(NIST SRD4). Comparisons with the measured properties suggest that proposed database can be used to extract properties of Jet A-1 for conjugate heat transfer analysis of liquid propellant rocket engine thrust chambers. Predicted combustion/cooling performance of regeneratively cooled thrust chambers shall be validated through comparisons with upcoming firing test results.
Aircraft Combat Survivability Analysis based on the Random Variable Weighted Score Algorithm
Yang, Ju-Suk ; Lee, Kyung-Tae ; Jee, Cheol-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 883~890
DOI : 10.5139/JKSAS.2013.41.11.883
Aircraft combat survivability analysis is essential process for the development of combat aircraft. M&S methodology is the typical procedure for the aircraft combat survivability analysis, and the last step is the expensive Live Fire Test if it is necessary. This study introduced cost and time effective survivability analysis methodology based on the random variable weighted score algorithm in conceptual design phase. For this study, essential element and event analysis (E3A) is used to define the random variables and Monte-Carlo simulation is implemented to estimate weighted score and the final value of survivability.
Ground Test & Evaluation of Conformal Load-bearing Antenna Structure for Communication and Navigation
Kim, Min-Sung ; Park, Chan-Yik ; Cho, Chang-Min ; Jun, Seung-Moon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 891~899
DOI : 10.5139/JKSAS.2013.41.11.891
This paper suggests a test and evaluation procedure of conformal load-bearing antenna structure(CLAS) for high speed military jet application. A log periodic patch type antenna was designed for multi-band communication and navigation antenna. Carbon/Glass fiber reinforced polymer was used as a structure supporting aerodynamic loads and honeycomb layer was used to improve antenna performance. Multi-layers were stacked and cured in a hot temperature oven. Gain, VSWR and polarization pattern of CLAS were measured using anechoic chamber within 0.15~2.0 GHz frequency range. Tension, shear, fatigue and impact load test were performed to evaluate structural strength of CLAS. Antenna performance test after every structural strength test was conducted to check the effect of structural test to antenna performance. After the application of new test and evaluation procedure to validate a new CLAS, a design improvement was found.
Structural test of KSLV-I Payload fairing
Lee, Jong-Woong ; Kong, Cheol-Won ; Eun, Se-Won ; Nam, Gi-Won ; Jang, Young-Soon ; Shim, Jae-Yeul ; Lee, Young-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 900~907
DOI : 10.5139/JKSAS.2013.41.11.900
Payload fairing(PLF) protects satellites and related equipment from the external environment. They are separated before the satellite separation. Payload fairing made of composite sandwich materials due to their considerable bending stiffness and strength-to-weight ratio. Payload fairing have compression, shear and bending load during the flight. In this study, To check the strength of PLF and connected part, structural test of PLF accomplished using an actuator and a fixture. Purpose of structural test is to verify the strength of PLF in force of separation spring and combination structural load applied. Test result shows that the PLF have an acceptable margin of safety for the combination structural load and force of separation spring.
Development and Flight Test of a Small Solar Powered UAV
Ahn, Il-Young ; Bae, Jae-Sung ; Park, SangHyuk ; Yang, Yong-Man ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 908~914
DOI : 10.5139/JKSAS.2013.41.11.908
This study has developed a small solar powered UAV and performed its flight tests. In daylight, a solar powered UAV flies by using some of electricity generated from solar cells, and stores the remainder into battery. At night it flies by using electricity from battery. A solar powered UAV should have aerodynamically efficient configurations, light-weight, strong wing and fuselage. Its electric propulsion system and solar power system should also be very efficient. In the present study the solar powered UAV and its solar power system are developed for 12 hour continuous flight and the flight tests are performed to verify its performance. The flight tests performed in fall and winter to prove the present solar powered UAV is successful in four-season 12 hour flight.
Overview of Thermal Test and Practice in Developing Satellite
Seo, Joung-Ki ; Jang, Tae-Seong ; Cha, Won-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 915~920
DOI : 10.5139/JKSAS.2013.41.11.915
Units developed for a real satellite should pass space environmental tests and launch environment tests. Thermal Vacuum Test, one of the space environmental test, simulates extreme thermal environment encountered in on-orbit operation of satellite. Many payloads which adapt non-traditional, brand-new technology are developed by developers who is not familiar to space engineering field. There might be some possibility of mistakes which result in serious problem due to lack of experience, especially from planning to performing thermal vacuum test. In this paper, brief overview of thermal environmental test related to a satellite development is summarized in order to prepare and perform the thermal test.
Development and Verification of Thermal Control Subsystem for High Resolution Electro-Optical Camera System, EOS-D Ver.1.0
Chang, Jin-Soo ; Kim, Jong-Un ; Kang, Myung-Seok ; Yang, Seung-Uk ; Kim, Ee-Eul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 41, issue 11, 2013, Pages 921~930
DOI : 10.5139/JKSAS.2013.41.11.921
Satrec Initiative successfully developed and verified a high-resolution electro-optical camera system, EOS-D Ver.1.0. We designed this system to give improved spatial and radiometric resolution compared with EOS-C series systems. The thermal control subsystem (TCS) of the EOS-D Ver.1.0 uses heaters to meet the opto-mechanical requirements during in-orbit operation and uses different thermal coatings and multi-layer insulation (MLI) blankets to minimize the heater power consumption. Also, we designed and verified a refocusing mechanism to compensate the misalignment caused by moisture desorption from the metering structure. We verified the design margin and workmanship by conducting the qualification level thermal vacuum test. We also performed the verification of thermal math model (TMM) by comparing with thermal balance test results. As a result, we concluded that it faithfully represents the thermal characteristics of the EOS-D Ver.1.0.