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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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Numerical Flow Simulation of a UH-60A Full Rotorcraft Configuration in Forward Flight
Lee, Hee-Dong ; Kwon, Oh-Joon ; Kang, Hee-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 519~529
DOI : 10.5139/JKSAS.2010.38.6.519
In the present study, unsteady calculations have been performed to simulate flows around a UH-60A full configuration including main rotor, fuselage, and tail rotor. A flow solver developed for helicopter aerodynamic analysis was used for the simulation of the complete helicopter in high-speed and low-speed forward flight. Unsteady vibratory loads on the main rotor blades were compared with flight test and other calculated data for the assessment of the present flow solver. Aerodynamic interaction of the three components of the helicopter was investigated by comparing with the results of main-rotor-alone, main rotor and fuselage, and tail-rotor-alone configurations. It was found that the existence of the fuselage has an effect on the normal force distribution of the main rotor by varying downwash distribution on the rotor disc, and tip vortices trailed from the main rotor strongly interact with the tail-rotor.
An Investigation of Icing Effects on the Aerodynamic Characteristics of KC-100 Aircraft
Jung, Sung-Ki ; Lee, Chang-Hoon ; Shin, Sung-Min ; Myong, Rho-Shin ; Cho, Tae-Hwan ; Jeong, Hoon-Hwa ; Jung, Jae-Hong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 530~536
DOI : 10.5139/JKSAS.2010.38.6.530
In-flight icing is a critical technical issue for aircraft safety and, in particular, ice accretions on aircraft surfaces can drastically impair aerodynamic performances and control authority. In order to investigate icing effects on the aerodynamic characteristics of KC-100 aircraft, a state-of-the-art CFD code, FENSAP-ICE, was used. A main wing section and full configuration of KC-100 aircraft were considered for the icing analysis. Also, shapes of iced area were calculated for the design of anti-/de-icing devices. The iced areas around leading edge of main wing and horizontal tail wing were observed maximum 7.07% and 11.2% of the chord length of wing section, respectively. In case of wind shield, 16.7% of its area turned out to be covered by ice. The lift of KC-100 aircraft were decreased to 64.3%, while the drag was increased to 55.2%.
A Study on Assessment of Fatigue Durability for Composite Torque Link of Landing Gear
Kwon, Jung-Ho ; Kang, Dae-Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 537~546
DOI : 10.5139/JKSAS.2010.38.6.537
This research work contributed to a study for the procedure and methodology to assess the fatigue durability for a composite torque link of helicopter landing gear, which was newly developed and fabricated by the resin transfer moulding technique to interchange with metal component. The simulated load spectrum anticipated to be applied to the torque link during its operation life was generated using an advanced method of probabilistic random process, and the fatigue durability was evaluated by the strength degradation approach on the basis of material test data. The full scale fatigue test was also performed and compared with the analysis results.
Fluid-Structure Interaction Analysis of High Aspect Ratio Wing for the Prediction of Aero-elasticity
Lee, Ki-Du ; Lee, Young-Shin ; Lee, Dae-Yearl ; Lee, In-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 547~556
DOI : 10.5139/JKSAS.2010.38.6.547
For the safety of aircraft and accuracy of bombs, many companies have researched the new concept of adaptive kit to flying-bombs. For the long distance flying, it's normally used deployed high-aspect ratio wing because of limited volume. The probabilities of large elastic deformation and flutter are increased due to decreased stiffness of high-aspect ratio wing. In this paper, computational fluid dynamics and computational structure dynamics interaction methodology are applied for prediction of aerodynamic characteristics. FLUENT and ABAQUS are used to calculate fluid and structural dynamics. Code-bridge was made base on the compactly supported radial basis function to execute interpolation and mapping. There are some differences between rigid body and fluid-structure interaction analysis which are results of aerodynamics characteristics due to structural deformation. Small successive vibration was observed by interaction.
Efficient Adaptive Global Optimization for Constrained Problems
Ahn, Joong-Ki ; Lee, Ho-Il ; Lee, Sung-Mhan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 557~563
DOI : 10.5139/JKSAS.2010.38.6.557
This paper addresses the issue of adaptive global optimization using Kriging metamodel known as EGO(Efficient Global Optimization). The algorithm adaptively chooses where to generate subsequent samples based on an explicit trade-off between reduction of global uncertainty and exploration of the region of the interest. A strategy that saves the computational cost by using expectations derived from probabilistic nature of approximate model is proposed. At every iteration, a candidate test point that seems to be feasible/inactive or has little possibility to improve for minimum is identified and excluded from updating approximate models. By doing that the computational cost is saved without loss of accuracy.
Implementation of the Aircraft Autopilot System Simulator based on VOR/DME System
Lee, Dong-Kyu ; Lee, Sang-Chul ; Oh, Hwa-Suk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 564~569
DOI : 10.5139/JKSAS.2010.38.6.564
VOR/DME is the short range radio navigation system for much of the world. The navigation with VOR/DME is used for a long time because of its reliability. It can be used for almost all civil aircraft. To simulate the small aircraft's autopilot system based on VOR/DME system, we developed a simulator by using SIMULINK. The output panel of the simulator was developed according to the cockpit instrument of an actual aircraft. To verify the performance of the simulator several scenarios were planned. And we showed that the simulator performed well.
The Abnormal Increasing Pseudorange Satellite Detection Method Using Comparison of Residual Horizontal Projection
Ahn, Yong-Woon ; Ahn, Jong-Sun ; Won, Dae-Hee ; Heo, Mun-Beom ; Jo, Jeong-Ho ; Sung, Sang-Kyung ; Lee, Young-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 570~576
DOI : 10.5139/JKSAS.2010.38.6.570
This paper can be used for GPS air navigation study on integrity monitoring algorithm as, the projected horizontal plane using GPS pseudorange residuals for fault detection satellites were suspected. Failure to remove the detected suspicious satellite, compare with threshold which is calculated using satellite deployment (PDOP) and determine whether the failure is presented. The theory that horizontal projection of the satellite failure residuals greater than residual of normal satellite is proved mathematically. Comparison with horizontal projection residuals are likely to malfunction in the satellite were presented. To evaluate the proposed algorithm, bias fault insert into GPS pseudorange, and compare with conventional parity space method about fault detection and isolation capability.
Infrared Signature Analysis on a Flat Plate by Using the Spectral BRDF Data
Choi, Jun-Hyuk ; Kim, Dong-Geon ; Kim, Jung-Ho ; Kim, Tae-Kuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 577~585
DOI : 10.5139/JKSAS.2010.38.6.577
This paper is a part of developing a software that predicts the infrared signal emitted from a ground object by considering solar irradiation. The radiance emitted from a surface can be calculated by using the temperature and optical characteristics of the surface object. The bidirectional reflectance distribution function (BRDF) is defined as the ratio of reflected radiance to incident irradiance. It is a very important surface reflection property that decides the reflected radiance from the object. In this paper, the spectral radiance received by a remote sensor over the mid-wave infrared(MWIR), and the long-wave infrared(LWIR) regions are computed and compared each other for several different materials. The results show that the optical surface properties such as the BRDF and the emissivity of the object surface can play a major role in generating the infrared signatures of various objects, and the largest infrared signal may reach up to 10 times the smallest one when the infrared signals obtained from a flat plate with different surface conditions under the sun light.
Performance Load Balancing and Sensitivity Analysis of Ramjet/Scramjet for Dual-Combustion/Dual-Mode Ramjet Engine Part I. Performance Load Balancing
Kim, Sun-Kyoung ; Jeon, Chang-Soo ; Sung, Hong-Gye ; Byen, Jong-Ryul ; Yoon, Hyun-Gull ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 586~595
DOI : 10.5139/JKSAS.2010.38.6.586
An analytical study based on physical understandings and aero-thermodynamic theories was conducted to observe the performance characteristics and to derive the essential design parameters of dual ramjet(dual-combustion/dual-mode) propulsion for wide Mach number. The performances and operating limitations of the engines with two types combustors, such as constant pressure- and constant area- combustor, over various flight Mach numbers was investigated. Finally, the transition Mach number from ramjet to scramjet was carried out to optimize performance load balancing of ramjet and scramjet.
Performance Load Balancing and Sensitivity Analysis of Ramjet/Scramjet for Dual-Combustion/Dual-Mode Ramjet Engine Part II. Performance Sensitivity
Kim, Sun-Kyoung ; Jeon, Chang-Soo ; Sung, Hong-Gye ; Byen, Jong-Ryul ; Yoon, Hyun-Gull ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 596~604
DOI : 10.5139/JKSAS.2010.38.6.596
In order to investigate the operating conditions and major design parameters of a dual ramjet propulsion system, an theoretical analysis of ramjet and scramjet propulsion systems was performed. The performance characteristics of each engine are delivered by thermo-dynamical cycle analysis, considering loss effects in a real engine. The performance sensitivity analysis is conducted by investigating various performance parameters, such as an intake efficiency, combustor inlet Mach number, configuration of the combustor, fuel flow rate, and exhaust nozzle efficiency. Based on these analysis results, the processes of application to dual ramjet cycle engines are specified.
Rupture Safety Assesment of Bipropellant Propulsion System at High Pressure Testing
Chang, Se-Myong ; Han, Cho-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 605~611
DOI : 10.5139/JKSAS.2010.38.6.605
The geostationary satellite COMS is going to be launched in 2010, and, in the series of test, there are some high-pressure tests concerning the vessel tank filled with helium gas of hundreds atmospheric pressure. In this paper, authors evaluates risk associated with accidental rupture of the test system. Two possible scenarios are considered: 1) the 310-bar helium tank ruptures at the center of the acoustic chamber, and 2) the 116-bar reduced-pressure helium tank ruptures in the test room shielded by bullet-proof glasses. Using the theory of blast wave propagation and computational simulation, the dynamics of wave reflected in a confined space is investigated for highly complex unsteady flow physics.
Design of an Elastomeric Bearing for a Helicopter Rotor Hub by Non-linear Finite Element Method
Kim, Hyun-Duk ; Yoo, Si-Yoong ; Park, Jung-Sun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 612~619
DOI : 10.5139/JKSAS.2010.38.6.612
In this paper, an elastomeric bearing for a helicopter rotor hub is designed using nonlinear finite element method. The elastomeric bearing is the main component of the helicopter rotor hub that acts as a hinge to three motions(flapping, lagging and pitching) of rotor blade. The elastomeric bearing consists of rubber and metal plates. The stiffness design of the elastomeric bearing is important because elastic deformation of rubber is served to hinge. Accordingly, the elastomeric bearing is designed to satisfy the stiffness requirements for rotor hub bearing. In this study, a FE model generation algorithm is developed and stiffness characteristic of a rubber plate is analyzed for an efficient design of the spherical elastomeric bearing. It is proven that the elastomeric bearing satisfies stiffness requirements of the spherical bearing for a helicopter rotor hub.
A Study on Standardization of Data Bus for Modular Small Satellite
Jang, Yun-Uk ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 6, 2010, Pages 620~628
DOI : 10.5139/JKSAS.2010.38.6.620
Small satellites can be used for various space research and scientific or educational purposes due to advantages in small size, low-cost, and rapid development. Small Satellites have many advantages of application to Responsive Space. Compared to traditional larger satellites, however, Small satellites have many constraints due to limitations in size. Therefore, it is difficult to expect high performance. To approach maximum capability with minimal size, weight, and cost, standard modular platform of Small satellites is necessary. Modularity supports plug-and-play architecture. The result is Small satellites that can be combined quickly and reliably using plug-and-play mechanisms. For communication between modules, standard bus interface is needed. Controller Area Network(CAN) protocol is considered optimum data bus for modular Small satellite. CAN can be applied to data communication with high reliability. Hence, design optimization and simplification can also be expected. For ease of assembly and integration, modular design can be considered. This paper proposes development method for standardized modular Small satellites, and describes design of data interface based on CAN and a method of testing for modularity.