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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 37, Issue 12 - Dec 2009
Volume 37, Issue 11 - Nov 2009
Volume 37, Issue 10 - Oct 2009
Volume 37, Issue 9 - Sep 2009
Volume 37, Issue 8 - Aug 2009
Volume 37, Issue 7 - Jul 2009
Volume 37, Issue 6 - Jun 2009
Volume 37, Issue 5 - May 2009
Volume 37, Issue 4 - Apr 2009
Volume 37, Issue 3 - Mar 2009
Volume 37, Issue 2 - Feb 2009
Volume 37, Issue 1 - Jan 2009
Selecting the target year
An External Shape Optimization Study to Maximize the Range of a Guided Missile in Atmospheric Flight
Yang, Young-Rok ; Hu, Sang-Bum ; Je, So-Yeong ; Park, Chan-Woo ; Myong, Rho-Shin ; Cho, Tae-Hwan ; Hwang, Ui-Chang ; Je, Sang-Eon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 519~526
DOI : 10.5139/JKSAS.2009.37.6.519
This paper describes a research result of a external shape optimization study to maximize the range of the guided missile with canards and tailfins in atmospheric flight. For this purpose, the external shape optimization program which can enhance the range of a missile was developed, incorporated with the trajectory analysis and the optimization technique. In the trajectory analysis part, Missile DATCOM which utilizes the semi-empirical method was directly connected to the trajectory code to supply the aerodynamic coefficients efficiently at every time step. In the gliding flight trajectory after apogee, a maximum
trim condition calculation module was attached under the assumption of the missile continuously flying at maximum
condition. In the optimization part, a Response Surface Method(RSM) was adopted to reduce the computing time.
A Study of Design of Sidewalls for Cascade Model with Single Blade Within a 160% Pitch Passage
Cho, Chong-Hyun ; Kim, Young-Cheol ; Ahn, Kook-Young ; Cho, Soo-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 527~536
DOI : 10.5139/JKSAS.2009.37.6.527
A cascade apparatus was designed with only one blade. Its passage is a 160% width of the cascade pitch. This kind of apparatus can give more accurate experimental result than those applying multi-blades even though the apparatus is small. However, this causes difficulties to make the periodic condition along the pitchwise direction. In this study, sidewalls were designed to satisfy the periodic condition based on the flow structure using a gradient based optimization and a genetic algorism. The objective function was adopted the surface Mach number obtained on the cascade and fourteen design variables were selected for controlling sidewall shapes. The designed sidewalls using the genetic algorism shows better result.
A Study of Attitude Control and Stability Analysis Using D-Decomposition Stability Area Technique for Launch Vehicle
Park, Yong-Kyu ; Sun, Byung-Chan ; Roh, Woong-Rae ; Oh, Choong-Seok ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 537~544
DOI : 10.5139/JKSAS.2009.37.6.537
This paper concerns analysis technique on determining of attitude control gain in the low frequency region using stability area. The stability area is defined by the D-Decomposition method, which was designed by Neimark. In this paper, it is introduced D-Decomposition method from reference paper and design attitude control gain of generic launch vehicle during first stage flight phase. For selecting PD control gain, it is considered the system parameter uncertainty about whole first-stage flight phase, represented the stability area boundary on each case. After deciding the PD control gain using stability area method, it is applied to launch vehicle linear model, and checking the stability margin requirement, frequency response characteristics.
A Study on INS`s initial attitude error reducing methods at navigation mode entry in vibration environment
Lee, Youn-Seon ; Lee, Sang-Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 545~550
DOI : 10.5139/JKSAS.2009.37.6.545
Generally, the smoothing pre-filter of sensor`s raw measurement(accelerometer and gyroscope) is used for INS`s fast alignment. When the pre-filter is abruptly removed at Navigation-mode entry in vibration environment, INS`s initial attitude error can be largely generated. So that we propose initial attitude error reducing methods(monotone increasing of cutoff-frequency, real-time attitude estimation), these are proved by simulation.
Design of Fiber Optic Gyroscope for Sensing High Rotation
Do, Jae-Chul ; Chong, Kyoung-Ho ; Jo, Min-Sik ; Song, Ki-Won ; Moon, Hong-Key ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 551~555
DOI : 10.5139/JKSAS.2009.37.6.551
We studied the design of fiber optic gyroscope that enables to sense high rotation by extending the limit of rotation sensibility of fiber optic interferometer. Based on the digital serrodyne modulation technique, the signal processing of fiber optic gyroscope was designed and the prototype fiber optic gyroscope showed the high rotation sensibility up to
and scale factor performance of about 150[ppm] by the experiments. Accordingly, we confirmed that the design of fiber optic gyroscope was valid for high rotation.
A Study on Multi-Fault Diagnosis for Turboshaft Engine of UAV Using Fuzzy and Neural Networks
Kong, Chang-Duk ; Ki, Ja-Young ; Kho, Seong-Hee ; Koo, Young-Ju ; Lee, Chang-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 556~561
DOI : 10.5139/JKSAS.2009.37.6.556
The UAV(Unmanned Aerial Vehicle) that is remotely operating in various and long flight environments must have a very reliable propulsion system. Precise fault diagnosis of the turbo shaft engine for the Smart UAV that has the vertical take-off, landing and forward flight behaviors can promote reliability and availability. This work proposes a new diagnostic method that can identify the faulted components from engine measuring parameter changes using Fuzzy Logic and quantify its faults from the identified fault pattern using Neural Network Algorithms. The proposed diagnostic method can detect not only single fault but also multiple faults.
Measurement of Aerodynamic Heating over a Protuberance in Hypersonic Flow of Mach 7
Lee, Hyoung-Jin ; Lee, Bok-Jik ; Jeung, In-Seuck ; Kim, Seong-Lyong ; Kim, In-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 562~570
DOI : 10.5139/JKSAS.2009.37.6.562
An Experimental study was conducted on the flow characteristics and interference heating caused by a two-dimensional object protruding from a flat plate using a blow-down type of hypersonic wind tunnel. Inflow condition was a free-stream Mach number of 7.0 and a unit Reynolds number of
. Experimental conditions were varied with three heights of protuberance for two flat plate models which have different lengths. Experimental data were obtained from Schlieren visualization images and heat flux measurements. Also, this paper suggests hypersonic experimental techniques such as boundary-layer detection method in detail. A Large separation region was observed in front of the protuberance and that region was very sensitive to the height of protuberance and the length of the flat plate. For only the highest protuberance, a severe jump of heat flux was observed at the top station among the measuring points. Measured heat flux is large when the height of protuberance is large and the length of flat plate is long.
Shock compression of condensed matter using multi-material Reactive Ghost Fluid method : development and application
Kim, Ki-Hong ; Yoh, Jai-Ick ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 571~579
DOI : 10.5139/JKSAS.2009.37.6.571
For the flow analysis of reactive compressible media involving energetic materials and metallic confinements, a Hydro-SCCM (Shock Compression of Condensed Matter) tool is developed for handling multi-physics shock analysis of energetics and inerts. The highly energetic flows give rise to the strong non-linear shock waves and the high strain rate deformation of compressible boundaries at high pressure and temperature. For handling the large gradients associated with these complex flows in the condensed phase as well as in the reactive gaseous phase, a new Eulerian multi-fluid method is formulated. Mathematical formulation of explosive dynamics involving condensed matter is explained with an emphasis on validating and application of hydro-SCCM to a series of problems of high speed multimaterial dynamics in nature.
Design and Thermal Analysis of Focal Plane Assembly Cooling Unit of Earth Observation Camera
Seo, Joung-Ki ; Cho, Hee-Ken ; Lee, Deog-Gyu ; Lee, Seung-Hoon ; Choi, Hae-Jin ; Kang, Seok-Bong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 580~585
DOI : 10.5139/JKSAS.2009.37.6.580
Thermal analysis and design of FPA(Focal Plane Assembly)-CU(Cooling Unit) for Earth observation camera is performed. FPA-CU is the first cooling device for a spacecraft which is designed and manufactured by its own technology in Korea. FPA-CU has a special feature, TBM(Thermal Buffer Mass) which is discriminated from typical cooling devices using heat pipes and radiator. TBM can be regarded as a thermal energy reservoir and it shows thermally transient characteristics, which make it difficult to design the size and shape of TBM. In current study, a method to determine the volume and the size of TBM is proposed and validated. The transient thermal analysis for FPA-CU for 5 operational scenarios is performed and validates the final design of FPA-CU (Radiator,TBM, Heat pipe I/F). In case of an abnormal operation of a heat pipe among three radiator heat pipes, the temperature of FPA can be increased
according to the numerical simulation.
Spectrum and Equivalent Transient Vibration Analysis of Small Composite Satellite Structure
Cho, Hee-Keun ; Seo, Jung-Ki ; Myung, Noh-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 586~594
DOI : 10.5139/JKSAS.2009.37.6.586
This paper is the study on random, sinusoidal and shock vibration responses for the STSAT-3(science and technology satellite-3) proto-model which is the first small size all-composite satellite in Korea. The structure system of the STSAT-3 forms box type structure by joining several hybrid sandwich panels comprised of honeycomb core and carbon fiber reinforced laminated composite skins on both side. Mode shape, stress, displacement and acceleration responses are obtained on both the frequency domain and time domain by means of a commercial FEA software MSC/NASTRAN. From these analysis results, failure, safety factor and design validity are assessed. These results can be successfully applicable as reference data when a new satellite is developed as well as giving out an excellent criteria in satellite vibration treatment design.
Development of Reliability Block Diagram Analysis Tool for H/W Redundancy Structure based on Unit Module
Kim, Sung-Su ; Park, Sang-Hyuk ; Kim, Sung-Hwan ; Choi, Kee-Young ; Ha, Cheol-Keun ; Park, Choon-Bae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 595~601
DOI : 10.5139/JKSAS.2009.37.6.595
A flight control system for high reliability consists of complicated redundant structures. This redundancy can improve fault tolerant characteristics of system. So, a system manager is able to choose a suitable structure using analyzed quantitative data of various redundant structures. In this paper, we analyzed redundant characteristics and reliability. We defined necessary mathematical model for analysis tool. Then we compose a reliability block diagram analysis tool applying such defined analysis model using Simulink blocks. Finally we verified the analysis tool using a commercial tool.
A Study on Flight Simulation Based on HLA-RTI
Hyun, Se-Woong ; Yoon, Sug-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 602~608
DOI : 10.5139/JKSAS.2009.37.6.602
The HLA system architecture, prescribed in IEEE-1516, is a core fundamental technology to build a complex simulation network system which is composed of a number of individual simulation developed for different purposes. The model structure of flight simulation with expansibility and compatability was suggested in this thesis by showing how to implement HLA to a commercial flight simulation software and how the system implemented with HLA to work. In addition, it was judged whether real-time can be guaranteed implementing to a simulation system with integrity through analysis of flight information data collected by comparing real-time simulation based on HLA with commercial flight simulation.
Engineering Qualification Model Development of S-band Receiver for STSAT-3
Lee, Jung-Su ; Oh, Seung-Han ; Seo, Gyu-Jae ; Oh, Chi-Wook ; Myung, Noh-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 37, issue 6, 2009, Pages 609~614
DOI : 10.5139/JKSAS.2009.37.6.609
The TT&C communication subsystem of STSAT-3 is consisted of communication link to send telemetry data of spacecraft to the ground station and receive command data from ground station. The S-band receiver is used to receive command data from ground station, Engineering Qualification Model of S-band receiver has been designed and manufactured. The Designed S-band Receiver uses a single conversion for a simple frequency conversion, including a DC-DC Converter and EMI Filter. Also, Digital demodulation part designed using FPGA and RS-422 data interface. The performance of S-band Receiver in functional and space environments test satisfies the requirements of STSAT-3.