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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 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
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Aerodynamic Optimization of Helicopter Blade Planform (I): Design Optimization Techniques
Kim, Chang-Joo ; Park, Soo-Hyung ; O, Seon-Gu ; Kim, Seung-Ho ; Jeong, Gi-Hun ; Kim, Seung-Beom ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1049~1059
DOI : 10.5139/JKSAS.2010.38.11.1049
This paper treats the aerodynamic optimization of the blade planform for helicopters. The blade shapes, which should be determined during the threedimensional aerodynamic configuration design step, are defined and are parameterized using the B
zier curves. This research focuses on the design approaches generally adopted by industries and or research institutes using their own experiences and know-hows for the parameterization and for the definition of design constraints. The hover figure of merit and the equivalent lift-to-drag ratio for the forward flight are used to define the objective function. The resultant nonlinear programming (NLP) problem is solved using the sequential quadratic programming (SQP) method. The applications show the present method can design the important planform shapes such as the airfoil distribution, twist and chord variations in the efficient manner.
Aerodynamic Optimization of Helicopter Blade Planform (II): Applications to Design Optimization
Kim, Chang-Joo ; Park, Soo-Hyung ; Shin, Ki-Cheol ; Kim, Seung-Ho ; Chung, Ki-Hoon ; Kim, Seung-Bum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1060~1066
DOI : 10.5139/JKSAS.2010.38.11.1060
This paper focuses on the application of the proposed aerodynamic optimization techniques to design the blade planform of helicopter rotors. The design problems are formulated to maximize the hover figure of merit and the equivalent lift-to-drag ratio for high forward speed by optimally distributing airfoils, twist, and chord along the blade span. The numerical characters are investigated by solving various design problems. The advantages and limitations with the present design approach and the present modeling features for performance prediction are discussed. The recommendations for the required model refinements to get more accurate optimal configurations are addressed as future research areas.
Reliability Based Design Optimization for the Pressure Recovery of Supersonic Double-Wedge Inlet
Lee, Chang-Hyuck ; Ahn, Joong-Ki ; Bae, Hyo-Gil ; Kwon, Jang-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1067~1074
DOI : 10.5139/JKSAS.2010.38.11.1067
In this study, RBDO(Reliability Based Design Optimization) was performed for a supersonic double-wedge inlet. By considering uncertainty of design with given design space, the pressure recovery was transformed into the probabilistic constraint while the inlet drag was considered as a deterministic objective function. To save computational analysis cost and to search good design space, Latin-Hypercube design of experiment and the Kriging model were incorporated and then RBDO was performed. Monte-Carlo simulation was performed to verify the accuracy of AFORM(Advanced First Order Reliability Method). It was found that AFORM result agreed very well with the Monte-Carlo simulation result. The system reliability was guaranteed by considering uncertainty of the design variables. In case of considering diverse uncertainty of system design, RBDO was found to be useful.
Transonic Aeroelastic Analysis of a Airfoil with Friction Damping
Yoo, Jae-Han ; Lee, In ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1075~1080
DOI : 10.5139/JKSAS.2010.38.11.1075
For the aeroelastic analysis of a wing with friction damping, coupled time integration method was used to obtain time responses in the subsonic and transonic regions. To take into account aerodynamic nonlinearity induced by shock wave on the lifting surface, transonic small disturbance equation with in-phase periodic boundary condition was used for unsteady aerodynamic calculation. For 2-DOF airfoil system with displace-dependent friction dampers, the effects of normal load slope and Mach number on flutter boundary were investigated.
Study on Composite Solid Propellants for Rocket Assisted Projectile
Kim, Kyung-Moo ; Cho, Joon-Hyun ; Jeong, Deok-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1081~1086
DOI : 10.5139/JKSAS.2010.38.11.1081
The technical procedure of an enhancement of a 120 mm rocket assisted projectile has here addressed by analyzing the ballistic performance with several the solid rocket propellants and shell designs. The performance was evaluated by aero-ballistic analyses and static ground tests of the rocket motor. Consequently, firing tests showed that one of tested models gave about 70% of extended range compared with conventional projectiles.
Study on the Satellite Thermal Control Hardware Composed of Two Parallel Channels Working for Heat Pipe and Phase Change Material
Kim, Taig-Young ; Hyun, Bum-Seok ; Lee, Jang-Joon ; Rhee, Ju-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1087~1093
DOI : 10.5139/JKSAS.2010.38.11.1087
The satellite thermal control H/W composed of two parallel channels working for heat pipe (HP) and phase change material (PCM) is suggested for the high heat dissipating component which works intermittently with short duty. In a limited point of view, the HP-PCM device is a kind of off-the-shelf component that requires no dedicated configuration and thermal designs to PCM. Therefore, it can be used with less impact on the program cost and schedule different from most of the PCM applications. In present study the typical honeycomb structure radiator applying the HP-PCM device is designed and the detail thermal math model is developed for numerical analyses. The result comparison between without and with PCM shows that the HP-PCM device redistributes the peak heat around the whole mission period through the alternate melting and freezing of PCM, and, as a result, the maximum and minimum temperatures are effectively alleviated. The drawback of PCM application due to low thermal conductivity can be successfully resolved by means of parallel arrangement of HP channel.
Part1 : Numerical Code Validation and Quantitative Analyses of Ice Accretion around Airfoils
Son, Chan-Kyu ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1094~1104
DOI : 10.5139/JKSAS.2010.38.11.1094
In the previous studies, the validation of numerical codes has been conducted based on the qualitative comparison of predicted ice shapes with experiments, which poses a significant limit on the systematic analysis of ice shapes due to the variation of meteorological conditions. In response to this, the numerical code has been quantitatively validated against available experiment for the ice accretion on cylinders and airfoils in the present study. Ice shapes accumulated on the bodies are systematically investigated with respect to various icing parameters. To this end, maximum thickness, heading direction and ice thickness are quantified and expressed in the polar coordinate system for the comparison with other numerical results. By applying the quantitative analysis, similar shapes are intuitively distinguished. The developed numerical code underestimates the ice accretion area and the ice thickness of lower surface. In order to improve the accuracy, further accurate aerodynamic solver is required for the water droplet trajectories.
Part2 : Quantitative Analyses of Accumulated Ice Shapes with Various Icing Conditions
Son, Chan-Kyu ; Oh, Se-Jong ; Yee, Kwan-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1105~1114
DOI : 10.5139/JKSAS.2010.38.11.1105
Ice shapes accumulated on the aircraft surfaces are categorized into rime and glaze ice, which are highly dependent on various parameters such as ambient temperature, liquid water contents (LWC), mean volumetric droplet diameter and freestream velocity. In this study, quantitative analyses on the ice accretion have been attempted in a systematical manner and the key findings are as follows. First, the increase of freestream velocity can cause tremendous change in the ice accumulation such as the growth of ice accretion area, ice heading direction and maximum thickness of ice horn. Second, LWC is found to be linearly proportional to the ice accretion area. Third, the effects of ambient temperature on incoming water mass seem to be relatively small in comparison with LWC and freestream velocity. Finally, it was shown that MVD has only a little influence on ice shapes. However, it may increase the ice accretion area by increasing the droplet impacting range.
Strength of sandwich-to-laminate single-lap bonded joints in elevated temperature and wet condition
Choi, Bae-Hyun ; Kweon, Jin-Hwe ; Choi, Jin-Ho ; Shin, Sang-Jun ; Song, Min-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1115~1122
DOI : 10.5139/JKSAS.2010.38.11.1115
The main objective of this study is to experimentally investigate the effect of adhesive thickness and environmental conditions on the failure and strength of sandwich-to-laminate bonded joints. Three different adhesive thicknesses (t=0.2, 2 and 4 mm) and two different environmental conditions were considered. Environmental conditions include the RTD(room temperature and dry condition) and ETW(elevated temperature and wet condition). Test results show as the adhesive thickness increases from 0.2 mm to 2 and 4 mm, the joint strength decreases 16 and 30%, respectively. Regarding the effect of environmental conditions, except for one case, the joint strength in the ETW conditions turned out to be 12% higher than those in the RTD conditions. In the joints with adhesive thickness of 0.2 mm, remarkable difference from RTD condition was not found.
Concept Design of Angular Deviation and Development of Measurement System for Transparency in Aircraft
Moon, Tae-Sang ; Woo, Seong-Jo ; Kwon, Seong-Il ; Ryu, Kwang-Yeol ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1123~1129
DOI : 10.5139/JKSAS.2010.38.11.1123
Angular Deviation(AD) on transparency applied to TA-50 Aircraft deteriorates armament system's accuracy because it makes a difference in between actual and theoretical targets. In order to increase accuracy, therefore, TA-50 Aircraft measures AD on transparency and provide the measured values for the integrated mission display computer as a type of AD coefficients. This makes AD revised so that pilots can accurately see the actual target on their head-up display. In order to implement such mechanism into a real field, we develop a new device and system automatically measuring AD for the first time. We also deal with basic concept including AD induction formula as well as operating systems. As a consequence of testing the accuracy and precision for verifying reliability of the system, we got satisfactory results. In specific, the accuracy was within the resultant criterion of 1%. The precision was also satisfied with respect to the whole criteria. The system developed through this research is qualified as a military standard equipment for transparency of the canopy.
Drop Test of an Oleo-pneumatic Landing Gear
Kim, Tae-Uk ; Lee, Sang-Wook ; Shin, Jeong-Woo ; Lee, Seung-Kyu ; Kim, Sung-Chan ; Hwang, In-Hee ; Kang, Shin-Hyun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1130~1135
DOI : 10.5139/JKSAS.2010.38.11.1130
The main function of a landing gear is to absorb the impact energy during touchdown. Most landing gear use an oleo-pneumatic shock absorber which essentially consists of an oil damper and a gas spring. The performance of a shock absorber can be estimated by analysis but it should be verified by drop test, which is required by MIL Spec. and FAR. In the drop test, various data such as ground loads, shock absorber pressure, stroke and mass travel are analyzed to validate the shock absorbing efficiency and the mathematical model for analysis. This paper presents the introduction of drop test facility, the test procedure and data evaluation method with real drop test example.
Laser Ranging for Lunnar Reconnaissance Orbiter using NGSLR
Lim, Hyung-Chul ; McGarry, Jan ; Park, Jong-Uk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1136~1143
DOI : 10.5139/JKSAS.2010.38.11.1136
One-way laser ranging technology is applied for the precise orbit determination of LRO, which is the first trial for supporting the missions of lunar or planetary spacecraft. In this paper, LRO payload and ground system are discussed for LRO laser ranging, and some errors effecting on time of flight and tracking mount accuracy are analyzed. Additionally several technologies are also analyzed to make laser pulses shot from ground stations to arrive in the LRO earth window. Measurement data of LRO laser ranging verified that these technologies could be implemented for one-way laser ranging of lunar spacecraft.
Analysis of the Collision Probability and Mission Environment for Space debris
Seong, Jae-Dong ; Min, Chan-Oh ; Lee, Dae-Woo ; Cho, Kyeum-Rae ; Kim, Hae-Dong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 11, 2010, Pages 1144~1151
DOI : 10.5139/JKSAS.2010.38.11.1144
The increasing number of orbital debris objects is a risk for satellites because of past 50 years space activities. The LEO (low earth orbit) where KOMPSAT-2 and KOMPSAT-5 are operated is including about 84% of the total space debris. Thus, the space missions need to consider the space debris. In this paper, we analysis the orbit characteristics and spatial density of space debris about KOMPSAT-2 that is in activity and KOMPSAT-5 that will be launched in 2010. Analyzed probability damage and collision with space debris are also performed. ESA MASTER2005 and of NASA DAS2.0 are used to analysis KOMPSAT mission environment. As a result, it is noted that KOMPSAT-2's collision probability was far more than KOMPSAT-5 because KOMPSAT-2's orbit has high density composed space debris.