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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 38, Issue 12 - Dec 2010
Volume 38, Issue 11 - Nov 2010
Volume 38, Issue 10 - Oct 2010
Volume 38, Issue 9 - Sep 2010
Volume 38, Issue 8 - Aug 2010
Volume 38, Issue 7 - Jul 2010
Volume 38, Issue 6 - Jun 2010
Volume 38, Issue 5 - May 2010
Volume 38, Issue 4 - Apr 2010
Volume 38, Issue 3 - Mar 2010
Volume 38, Issue 2 - Feb 2010
Volume 38, Issue 1 - Jan 2010
Selecting the target year
Prediction of Glaze Ice Accretion on 2D Airfoil
Son, Chan-Kyu ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 747~757
DOI : 10.5139/JKSAS.2010.38.8.747
The ice accreted on the airfoil is one of the critical drivers that causes the degradation of aerodynamic performance as well as aircraft accidents. Hence, an efficient numerical code to predict the accreted ice shape is crucial for the successful design of de-icing and anti-icing devices. To this end, a numerical code has been developed for the prediction of glaze ice accretion shape on 2D airfoil. Constant Source-Doublet method is used for the purpose of computational efficiency and heat transfer in the icing process is accounted for by Messinger model. The computational results are thoroughly compared against available experiments and other computation codes such as LEWICE and TRAJICE. The direction and thickness of ice horn are shown to yield similar results compared to the experiments and other codes. In addition, the effects of various parameters - temperature, free-stream velocity, liquid water contents, and droplet diameter - on the ice shape are systematically analyzed through parametric studies.
A Sizing Method for Solar Power Long Endurance UAVs
Lee, Ju-Ho ; Lee, Chang-Gwan ; Lim, Se-Sil ; Kim, Keum-Seong ; Han, Jae-Hung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 758~766
DOI : 10.5139/JKSAS.2010.38.8.758
The design procedure of Solar Power UAVs is complicated because the configuration and required power for flight must be considered simultaneously as the supplied power is influenced by the wing area. In order to minimize trial and error for the Solar Power UAVs design, a systematic sizing method is proposed which can be used to determine whether a Solar Power UAV is feasible for a given mission, and to derive preliminary dimensional specification of it. The sizing procedure begins with initially assumed wing area because the power, lift, and drag of the wing are directly proportional to it. The assumed wing area and mission requirements are then used to determine step by step the airfoil specifications including lift coefficient and drag coefficient, weight, required power, and wing area. This procedure is iterated for each newly assumed wing area until the error between the assumed wing area and calculated wing area becomes significantly small enough. This sizing methodology was applied to previously developed Solar Power UAVs for validation purposes, resulting in good agreement. The methodology was also applied to determine the dimensions and specifications of the Solar Power High-Altitude Long-Endurance UAV.
Release Mechanism for small satellite using micro DC motor
Tak, Won-Jun ; Jo, Jae-Uk ; Lee, Min-Soo ; Kim, Byung-Kyu ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 767~773
DOI : 10.5139/JKSAS.2010.38.8.767
This paper describes development of a non-explosive separation device which can be equipped on small satellites. The spur geared micro DC motor, which has high reliability and advantage of price, is adopted as an actuator. The proposed separation device has resettability and it does not need extra jig to reload. In addition, the simple structure makes it easy to fabricate and assemble. To verify the performance of the proposed device, the response time tests, maximum preload tests and maximum shock level tests were performed. Also, through the vibration tests and thermal vacuum tests, feasibility of the proposed separation device was shown in launching and space environments. Therefore, we expect that the proposed separation device can replace the imported separation devices in near future.
Study of Time-to-go Polynomial Guidance Law with Considering Acceleration Limit
Lee, Chang-Hun ; Kim, Tae-Hun ; Tahk, Min-Jea ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 774~780
DOI : 10.5139/JKSAS.2010.38.8.774
This paper deals with the choice of guidance gain for the time-to-go polynomial (POLY) guidance law when the acceleration limit is existed. POLY is derived based on the assumption that guidance commands are formed by a time-to-go polynomial function. The main characteristic of POLY is that any positive values can be used for its guidance gain. For this reason, it is ambiguous to choose a proper guidance gain. To relieve this difficulty, we firstly derive the closed-form solution of acceleration command and figure out the relationship between the maximum acceleration and guidance gain. From this analysis, we provide a guideline for choosing a guidance gain which satisfies the desired acceleration limit. Finally, the proposed method is demonstrated by simulation study.
A Realization of Applicable GPS/INS Fault Detection Algorithm for UAV using Low Grade Processor
Yoo, Jang-Sik ; Ahn, Jong-Sun ; Sung, Sang-Kyung ; Lee, Young-Jae ; Chun, Se-Bum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 781~789
DOI : 10.5139/JKSAS.2010.38.8.781
In the GPS/INS integrated system fault detection, algorithm based on a chi-square distribution is commonly used. In this paper, it has been proposed simplified GPS/INS fault detection algorithm that is combined conventional RAIM (Receiver Autonomous Integrity Monitor) and algorithm based on chi-square distribution for UAV using row-grade processor. It use a fault model to verify the proposed algorithm and produced the result.
Numerical Investigation on the Mechanism of Mode Transition in Axi-symmetric Supersonic Jet Screech
Bin, Jong-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 790~797
DOI : 10.5139/JKSAS.2010.38.8.790
Mode transition of the axi-symmetric screech tone in the low supersonic Mach number range from 1.0 to 1.20 is numerically analyzed. The axi-symmetric Navier-Stokes equations and the k-e turbulence model are solved in the cylindrical coordinate system. The dispersion-relation-preserving(DRP) scheme is applied for space discretization and the optimized four levels marching method are used for time integration. At low supersonic Mach numbers with an axi-symmetric A1 mode in the simulation, it is shown that acoustic propagation due to the nonlinear effects is seen in the lateral direction and the screech tone frequency is the same as the vortex passing frequency due to the generation of intense large-scale vortical motions.
Random Vibration Characteristics of a Whole Structure Composite Satellite Having Hybrid Composite Sandwich Panels
Cho, Hee-Keun ; Rhee, Ju-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 798~805
DOI : 10.5139/JKSAS.2010.38.8.798
Whole composite structure small class (150kg) satellite, STSAT-3, was initially developed in Korea. The structure does have aluminum frames that support the structure, and it is composed of only composite sandwich panels. A number of electronic boxes and mechanical apparatus will be shielded within the compartments built up by the composite panels. This study focused on the random vibration responses of the satellite. For this objective, vibration tests and analyses have been successfully performed with respect to STM (structure and thermal model) of the satellite. Additionally, through the experiment and theoretical analyses, the both results` accuracy was verified by comparison each other.
Assessment of Crashworthiness Performance for Fuel Tank of Rotorcraft
Kim, Hyun-Gi ; Kim, Sung-Chan ; Lee, Jong-Won ; Hwang, In-Hee ; Hue, Jang-Wook ; Shin, Dong-Woo ; Jun, Pil-Sun ; Jung, Tae-Kyung ; Ha, Byung-Kun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 806~812
DOI : 10.5139/JKSAS.2010.38.8.806
Fuel tanks for rotorcraft have a great influence on the survivability of crews. The philosophy of crashworthy rotorcraft design evolved from the long term effort of the US Army. US army established MIL-DTL-27422D for specifying detail requirements related to crash resistant fuel tank especially for military rotorcraft to prevent post crash fire which is the greatest threat to life in rotorcraft crash. Crashworthiness of the rotorcraft fuel tank could be guaranteed through the crash impact tests which are specified in the MIL-DTL-27422D. Fuel tanks for Korea Helicopter Program have been developed and tested according to MIL-DTL-27422D with minor modifications of flexible fittings. The present study shows some results of the mandatory crash impact tests of the fuel tanks to verify their performances.
Safety Design and Validation of Mission Equipment Package for Korean Utility Helicopter
Kim, Yoo-Kyung ; Kim, Myung-Chin ; Kim, Tae-Hyun ; Yim, Jong-Bong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 813~822
DOI : 10.5139/JKSAS.2010.38.8.813
Integrated data processing for display of flight critical data and mission critical data was conducted without additional display instruments using glass cockpit design. Based on a pre-designed flight critical system and a mission critical system, this paper shows an optimal design of subsystem integration. The design satisfies safety requirements of flight control systems(FCS) and requires minimized modification of pre-designed systems. By conducting integration test using System Integration laboratory(SIL), it is confirmed that the introduced design approach meets the safety requirements of the MEP system.
Investigation of Thermophysical Properties of the Kerosene Using the Surrogate Model Fuel at Supercritical Conditions
Kim, Kuk-Jin ; Heo, Jun-Young ; Sung, Hong-Gye ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 823~833
DOI : 10.5139/JKSAS.2010.38.8.823
For the study of thermophysical properties of kerosene for the liquid rocket and aviation fuels, the surrogate models are investigated. The density distributions based on the real gas equations of state(Soave modification of Redlich-Kwong and Peng-Robinson equation of state) and NIST SUPERTRAPP(extended corresponding state principle) are compared with the previous experimental results at supercritical conditions. The error range of thermophysical properties analyzed for the surrogate models as well. Peng-Robinson equation of state and extended corresponding state principle are especially accurate for the hydrocarbon fuels but the appropriate surrogate models need to be chosen to the operation conditions such as pressure and temperature.
STSAT-3 Hall Thruster Propulsion System Development
Cho, Hee-Keun ; Ryu, Kwang-Sun ; Cha, Won-Ho ; Lee, Jong-Sup ; Seo, Mi-Hee ; Choi, Won-Ho ; Myung, Noh-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 834~841
DOI : 10.5139/JKSAS.2010.38.8.834
The STSAT-3 (science and technology satellite) is the first satellite whose entire structure was made of composite materials in Korea and it will be launched later in 2011. As like other small satellites, it is also equipped with several advanced instruments whose major objectives focused on the scientific tests in space. The HPS (hall thruster propulsion system) using xenon gas as a propellant has been developed and its overall ground tests were conducted. This research emphasizes on the technologies and procedure applied to the development of the entire HPS and its function and environment tests.
Development and Verification of Thermal Analysis Model for Thermal Vacuum Test of Satellite Components
Kim, Sang-Ho ; Seo, Hyun-Suk ; You, Jae-Ho ; Han, Eun-Soo ; Kim, Tai-Kyung ; Kim, Hyeong-Dong ; Huh, Hwan-Il ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 8, 2010, Pages 842~847
DOI : 10.5139/JKSAS.2010.38.8.842
Thermal analysis for the simulation of satellite component level thermal vacuum test processes was carried out by considering thermal vacuum test environment condition, thermal vacuum chamber configuration, and satellite`s inner thermal environment. The transient analysis results can be obtained for the temperatures of component and thermal vacuum chamber assemblies. The thermal analysis model was verified with the component thermal environmental test results by using enhanced thermal vacuum chamber.