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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 44, Issue 9 - Sep 2016
Volume 44, Issue 8 - Aug 2016
Volume 44, Issue 7 - Jul 2016
Volume 44, Issue 6 - Jun 2016
Volume 44, Issue 5 - May 2016
Volume 44, Issue 4 - Apr 2016
Volume 44, Issue 3 - Mar 2016
Volume 44, Issue 2 - Feb 2016
Volume 44, Issue 1 - Jan 2016
Selecting the target year
Test Research Using an IR Thermography Technique in a Supersonic Wind Tunnel
Kim, Ikhyun ; Lee, Jaeho ; Park, Gisu ; Byun, Yunghwan ; Lee, Jongkook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 99~107
DOI : 10.5139/JKSAS.2016.44.2.99
Test research on Infra-Red Thermography(IRT) technique in a supersonic wind tunnel has been conducted. Inadvertent technical difficulties and their solutions associated with the technique in running of the facility were examined. Two flow conditions at Mach number of 3 and 4 were considered. A double compression ramp model, that replicates realistic high-speed vehicle configuration, was used as test model. The present IR data were compared with shadowgraph visualization images and laminar computational fluid dynamics(CFD) results. It has been shown that the IRT technique can be used in quantifying various fluid dynamic features such as flow transition, separation and three-dimensional phenomena around the double compression ramp model.
Analysis of Fluid-Structure Interaction by High Velocity Impact for Liquid Filled Cylindrical Container
Bae, Hongsu ; Woo, Kyeongsik ; Kim, In-Gul ; Kim, Jong-Heon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 108~115
DOI : 10.5139/JKSAS.2016.44.2.108
In this paper, fluid-structure of interaction behavior of a fluid-filled cylindrical polymer container impacted by a high speed spherical projectile was studied using ALE(Arbitrary Lagrangian Eulerian) method. The hydrodynamic ram phenomenon occurred by the impact projectile penetrating through the container was investigated by examining time histories of projectile velocity and fluid pressure and density. The analysis results were agreed reasonably well compared to those by experiments.
Performance Characteristics of a TBCC Engine with Turbo-Ramjet Engine Transition Mode
Moon, Kyoo-Hwan ; Sung, Hong-Gye ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 116~122
DOI : 10.5139/JKSAS.2016.44.2.116
The performance characteristics of a TBCC engine considering the transition mode from a turbojet to a ramjet engine has been investigated. The performance of each engine was proposed and a transition mode of the TBCC engine has been evaluated by adjusting the operating rate of the ramjet engine and turbojet engine performance changes continuously. Based on the transition model, it was confirmed that the performance is continuously changed at various flight Mach numbers and altitudes. The performance characteristics including thrust and specific impulse considering various flight conditions and transition mode were analyzed, which testifies characteristics of the engine itself, as well as transition of the combined cycle.
Design and Implementation of Real-Time Helmet Pose Tracking System
Hwang, Sang-Hyun ; Chung, Chul-Ju ; Kim, Dong-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 123~130
DOI : 10.5139/JKSAS.2016.44.2.123
This paper describes the design and implementation scheme of HTS(Helmet Tracking System) providing coincident LOS(Line of Sight) between aircraft and HMD(Helmet Mounted Display) which displays flight and mission information on Pilot helmet. The functionality and performance of HMD system depends on the performance of helmet tracking system. The target of HTS system design is to meet real-time performance and reliability by predicting non-periodic latency and high accuracy performance. To prove an availability of a proposed approach, a robust hybrid scheme with a fusion optical and inertial tracking system are tested through a implemented test-bed. Experimental results show real-time and reliable tracking control in spite of external errors.
IRF performance prediction by analyzing of amplitude and phase errors for the wideband Chirp signal
Kim, Dong-Sik ; Kim, Jong-Pil ; Lee, Jong-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 131~138
DOI : 10.5139/JKSAS.2016.44.2.131
In this paper, we studied the IRF performances of the chirp signal used in the SAR system. The most important factors that degrade IRF performances are amplitude and phase errors. Each factor can be represented to linear, quadratic, random and ripple terms. That can be extracted by a quadratic polynomial curve fitting of chirp waveform. We analyzed the IRF performances by the error terms and supposed the minimum value of RF non-linearity to meet the specification of the PSLR and ISLR.
New Technologies of Space Launch Vehicles including Electric-Pump Cycle Engine
Jeong, Seung-Min ; Kim, Kui Soon ; Oh, Sejong ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 139~155
DOI : 10.5139/JKSAS.2016.44.2.139
Present paper introduces the recent advances in space launch vehicle technologies. A brief survey is given for the space development programs in civil sector with their business model and key technologies. Advances in key technologies were reviewed in detail with more emphasis on the electric pump cycle engine for low cost high performance small launch vehicle, Electron, under development by Rocketlab Ltd., since their contributions would give good lessons for rocket scientists.
Thermal Vacuum Test and Thermal Analysis for a Qualification Model of Cube-satellite STEP Cube Lab.
Kang, Soo-Jin ; Ha, Heon-Woo ; Han, Sung-Hyun ; Seo, Joung-Ki ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 156~164
DOI : 10.5139/JKSAS.2016.44.2.156
Qualification model(QM) of main payloads including concentrating photovoltaic system using fresnel lens, heating wire cutting type shockless holding and release mechanism, and MEMS-based solid propellant thruster have been developed for the STEP Cube Lab.(Cube Laboratory for Space Technology Experimental Project), which is a pico-class satellite for verification of core space technologies. In this study, we have verified structural safety and functionality of the developed payloads under a qualification temperature range through the QM thermal vacuum test. Additionally, a reliability of thermal model of the payloads has been confirmed by performing a thermal correlation based on the thermal balance test results.
A Study on Plume Disturbance Calculation Method of GEO-KOMPSAT-2 Satellite
Kang, Wooyong ; Chae, Jongwon ; Park, Youngwoong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 165~171
DOI : 10.5139/JKSAS.2016.44.2.165
The attitude control, station keeping and wheel off-loading at GEO-KOMPSAT-2 are realized by thrusters firings. Thrusters 1, 2 and 3 are mounted on the same axis as the solar array, which generates the plume disturbance largely. Therefore the effect of plume disturbance should be analyzed from satellite design phase. In this paper, we described the calculation method of plume disturbance and analyzed the plume disturbance of thruster 1,2 and 3 using GEO-KOMPSAT-2 initial configuration.
Life Prediction of Failure Mechanisms of the CubeSat Mission Board using Sherlock of Reliability and Life Prediction Tools
Jeon, Su-Hyeon ; Kwon, Yae-Ha ; Kwon, Hyeong-Ahn ; Lee, Yong-Geun ; Lim, In-OK ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 172~180
DOI : 10.5139/JKSAS.2016.44.2.172
A cubesat classified as a pico-satellite typically uses commercial-grade components that satisfy the vibration and thermal environmental specifications and goes into mission orbit even after undergoing minimum environment tests due to their lower cost and short development period. However, its reliability exposed to the physical environment such as on-orbit thermal vacuum for long periods cannot be assured under minimum tests criterion. In this paper, we have analysed the reliability and life prediction of the failure mechanisms of the cubesat mission board during its service life under the launch and on-orbit environment by using the sherlock software which has been widely used in automobile fields to predict the reliability of electronic devices.
Reliability Prediction of Liquid Rocket Engines for Different Propellant and Engine Cycles
Kim, Kyungmee O. ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 181~188
DOI : 10.5139/JKSAS.2016.44.2.181
It is known that reliability of liquid rocket engines depends on the design thrust, propellant, engine cycle, and hot firing test time. Previously, a method was developed for estimating reliability of a new engine by adjusting the design thrust and hot firing test time of reference engines where reference engines have the same propellant and engine cycle with the new engine. In this paper, we provide a procedure to predict the engine reliability when the new engine and the reference engine have different propellant and engine cycles. The proposed method is illustrated to estimate the engine reliability of the first stage of Korea Space Launch Vehicle II.
Analysis of Economic Effects for Surion Research and Development Program
Lee, Ki Young ; Kim, Sung Geun ; Shim, Dai Sung ; Kim, Mi Joung ; Kwon, Ki Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 44, issue 2, 2016, Pages 189~194
DOI : 10.5139/JKSAS.2016.44.2.189
This paper deals with the economic effects for the Surion(KUH-1) research and development program. The economic effects was measured by Inter-industry analysis method for production-inducing effects, value-added inducement effects, and job-creation effects and by estimating actual domestic input cost. In addition, technical riffle effects was analyzed for aerospace industry, defense industry and commercial industry market through similarity and contribution of technology.