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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 42, Issue 12 - Dec 2014
Volume 42, Issue 11 - Nov 2014
Volume 42, Issue 10 - Oct 2014
Volume 42, Issue 9 - Sep 2014
Volume 42, Issue 8 - Aug 2014
Volume 42, Issue 7 - Jul 2014
Volume 42, Issue 6 - Jun 2014
Volume 42, Issue 5 - May 2014
Volume 42, Issue 4 - Apr 2014
Volume 42, Issue 3 - Mar 2014
Volume 42, Issue 2 - Feb 2014
Volume 42, Issue 1 - Jan 2014
Selecting the target year
A Study on Radiation Shielding for Grid-stiffened Multi-Functional Composite Structures
Jang, Tae Seong ; Rhee, Juhun ; Seo, Hyun-Suk ; Hyun, Bum-Seok ; Kim, Taig Young ; Seo, Jung Ki ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 629~639
DOI : 10.5139/JKSAS.2014.42.8.629
This paper deals with an alternative multi-functional structures by using grid-stiffened composite structure with excellent bending stiffness and lightweight characteristics which is capable of easy embedding of electrical/electronic circuitry into structure. The enhancement of thermal conduction capability is made by the application of pitch-based carbon fiber. The lightweight radiation spot shielding technique is also proposed for multi-functional structures without conventional housing and the effectiveness of selective radiation shielding is validated through the proton irradiation test.
Spectral Infrared Signature Analysis of the Aircraft Exhaust Plume
Gu, Bonchan ; Baek, Seung Wook ; Yi, Kyung Joo ; Kim, Man Young ; Kim, Won Cheol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 640~647
DOI : 10.5139/JKSAS.2014.42.8.640
Infrared signature of aircraft exhaust plume is the critical factor for aircraft survivability. To improve the military aircraft survivability, the accurate prediction of infrared signature for the propulsion system is needed. The numerical analysis of thermal fluid field for nozzle inflow, free stream flow, and plume region is conducted by using the in-house code. Weighted Sum of Gray Gases Model based on Narrow Band with regrouping is adopted to calculate the spectral infrared signature emitted from aircraft exhaust plume. The accuracy and reliability of the developed code are validated in the one-dimensional band model. It is found that the infrared radiant intensity is relatively more strong in the plume through the analysis, the results show the different characteristic of the spectral infrared signature along the temperature, the partial pressure, and the species distribution. The continuous spectral radiant intensity is shown near the nozzle exit due to the emission from the nozzle wall.
Numerical Investigation of Complex System for Electrical Energy Harvesting and Vibration Isolation
Kwon, Sung-Cheol ; Jo, Mun-Shin ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 648~653
DOI : 10.5139/JKSAS.2014.42.8.648
Fly-wheel, gimbal antenna, mechanical gyro and cryocooler with moving parts generate a micro-vibration during their on-orbit operation. For the acquisition of high quality image of observation satellite, additional technical efforts are required to reduce the micro-vibration level from the vibration sources. In this study, we proposed a passive isolation system combined with a tuned mass damper-type energy harvester to generate electrical energy from the micro-vibration which has always been subjected to useless isolation objectives. The feasibility of the system has been investigated through the numerical simulation.
Conceptual Design of a Launch Vehicle for Lunar Exploration by Combining Naro-1 and KSLV-II
Yang, Won-Seok ; Kim, So-Yeon ; Choi, Jeong-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 654~660
DOI : 10.5139/JKSAS.2014.42.8.654
In this paper, a conceptual design of a launch vehicles is proposed by combining Naro-1 and KSLV-II. For trans-lunar injection (TLI) to lunar orbit at 300 km LEO, the target performance is defined same as that of KSLV-II, which delivers an object of 2.6 tons into 300 km LEO. The proposal launch vehicle concept of this study is combination of 1st stage of KSLV-I and 2-3rd stage of KSLV-II. Thus, it is possible to reduce the development time and also could expand the options for national launch vehicle capabilities with proven technologies.
Analysis of Precise Orbit Determination of the KARISMA Using Optical Tracking Data of a Geostationary Satellite
Cho, Dong-Hyun ; Kim, Hae-Dong ; Lee, Sang-Cherl ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 661~673
DOI : 10.5139/JKSAS.2014.42.8.661
In this paper, a precise orbit determination process was carried out based on KARISMA(KARI Collision Risk Management System) developed by KARI(Korea Aerospace Research Institute), in which optical tracking data of a geostationary satellite was used. The real optical tracking data provided by ESA(European Space Agency) for the ARTEMIS geostationary satellite was used. And orbit determination error was approximately 420 m compared to that of the ESA`s orbit determination result from the same optical tracking data. In addition, orbit prediction was conducted based on the orbit determination result with optical tracking data for 4 days, and the position error for the orbit prediction during 3 days was approximately 500~600 m compared to that of ESA`s result. These results imply that the performance of the KARISMA`s orbit determination function is suitable to apply to the collision risk assessment for the space debris.
Design of Radio Frequency Test Set for TC&R RF Subsystem Verification of LEO and GEO Satellites
Cho, Seung-Won ; Lee, Sang-Jeong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 674~682
DOI : 10.5139/JKSAS.2014.42.8.674
Radio Frequency Test Set (RFTS) is essential to verify Telemetry, Command & Ranging (TC&R) RF subsystem of both Low Earth Orbit (LEO) and Geostationary Earth Orbit (GEO) satellite during Assembly Integration & Test (AI&T). The existing RFTS was specialized for each project and needed to be modified for each new satellite. The new design enables RFTS to be used in various projects. The hardware and software was designed considering this and therefore it could be directly used in other projects within a similar test period without modification or inconvenience. It will be also easily controlled, modified, and managed through the extension in modularization according to each function and the use of COTS (commercial on-the-self) and this will improve system reliability. A more reliable RF test measurement is also provided in this new RFTS by using an accurate reference clock signal.
Configuration design of a deployable SAR antenna for space application and tool-kit development
Jeong, Suk-Yong ; Lee, Seung-Yup ; Bae, Min-Ji ; Cho, Ki-Dae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 683~691
DOI : 10.5139/JKSAS.2014.42.8.683
Significance of SAR(Synthetic Aperture Radar) satellite regadless of weather have grown for Earth observation. According to the cost-effective trend in satellite development, SAR antenna is actively studied. It`s a competitive candidate to use deployable SAR antenna out of CFRP. In this study, variables for an antenna configuration model was researched and evaluated. The design of the antenna was structurally analyzed by FEM(Finite Element Model). Tool-kit was developed for modifying the SAR antenna model easily in accordance with system requirement change. In the tool-kit, antenna configuration design and error analysis of the antenna surface could be achieved. And compatibility of tool-kit results to CST, a RF analysis program, was confirmed.
Satellite finite element model updating for the prediction of the effect of micro-vibration
Lim, Jae Hyuk ; Eun, Hee-Kwang ; Kim, Dae-Kwan ; Kim, Hong-Bae ; Kim, Sung-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 692~700
DOI : 10.5139/JKSAS.2014.42.8.692
In this work, satellite FE (finite element) model updating for the prediction of the effect of micro-vibration is described. In the case of satellites launched in low earth orbit, high agility and more mission accomplishments are required by the customer in order to procure many images from satellites. To achieve the goal, many mechanisms, including high capacity wheels and antennas with multi-axis gimbals have been widely adopted, but they become a source of micro-vibration which could significantly deteriorate the quality of images. To investigate the effect due to the micro-vibration in orbit on the ground, a prediction is conducted through an integrated model coupling the measured jitter sources with FE (finite element) model. Before prediction, the FE model is updated to match simulation results with the modal survey test. Subsequently, the quality of FE model is evaluated in terms of frequency deviation error, the resemblance of mode shapes and FRFs (frequency response functions) between test and analysis.
The establishment of requirement and kinematic analysis of mechanism for deployable optical structure
Jeong, Seongmoon ; Choi, Junwoo ; Lee, Dongkyu ; Hwang, Kukha ; Kim, Sangwoo ; Kim, Jangho ; Kim, Byungkyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 701~706
DOI : 10.5139/JKSAS.2014.42.8.701
In these days, there have been numerous researches on nano and micro satellites under the slogan of "Faster, Smaller, Better, Cheaper". Since optical structure occupies large portion of satellite volume, research on deployable optical structure gains great attention to reduce total volume of the satellite. In this paper, we establish the requirement of deployable optical structure based on specification of conventional optical structure and propose two candidate mechanisms which can satisfy the degree of deployment precision. Then, in order to evaluate the degree of deployment precision, we carry out kinematic analysis on de-space among tilt, de-space and de-center which influences optical characteristic of a satellite.
Design Improvement for Abnormal Display of Fuel Indicator Mounted on the Korean Utility Helicopter
Kim, Joung-Hun ; Kim, Chang-Young ; Chang, Joong-Jin ; Chang, In-Ki ; Jun, Byung-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 707~712
DOI : 10.5139/JKSAS.2014.42.8.707
Aircraft fuel indicator is a device to indicate the amount of fuel remained during flight, where accurate and consistent operation of the indicator should be maintained. Previously the Korean Utility Helicopter fuel indicator sporadically displayed abnormal sign by "8888" during flight, jeopardizing flight safety. Inappropriate EMI/EMC performance was detected during trouble shooting process. The cause of the abnormal display was found to be resulted from unstable power induced by electro-magnetic disturbance and CAN communication error. The aircraft fuel indicator design was improved and the design compatibility was verified to avoid abnormal display.
Next Generation Rotorcraft Technologies in USA and Europe
Oh, Sejong ; Kim, Sung Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 8, 2014, Pages 713~721
DOI : 10.5139/JKSAS.2014.42.8.713
In Europe and USA, new programs called GRC(Green Rotorcraft) and SRW (Subsonic Rotary Wing program) respectively, have been currently underway for developing the next generation rotorcraft. The final goal is to develope fuel-efficient/environmental-friendly tilt-rotor civilian rotorcraft, which can partly replace short-range regional aircrafts. Also for safe operation, the new rotorcraft technology is cooperated with the new air transport management(ATM) system, called SESAR(Single European Sky ATM Research) and NextGen(Next Generation Air Transport System) in Europe and USA. In addition to achieve the final goal, the tilt-rotor aircraft, they are trying to improve the performance of conventional helicopters by adopting more efficient propulsion system, active rotor system, and reducing internal and external noise. Especially in GRC program of Europe, the environmental factors such as noise, fuel efficiency, reduction of emission gas(CO2, NOx), are focused for the new technologies.