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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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Simulation of Unsteady Rotor-Fuselage Interaction Using an Improved Free-Wake Method
Lee, Joon-Bae ; Seo, Jin-Woo ; Lee, Jae-Won ; Yee, Kwan-Jung ; Oh, Se-Jong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 629~636
DOI : 10.5139/JKSAS.2010.38.7.629
This study is to investigate the aerodynamic effects of the Rotor-Fuselage Interactions in forward flight, and is conducted by using an improved time-marching free-wake panel method. To resolve the instability caused by the close proximity of the wake to the blade surface, the field velocity approach is added to the prior unsteady panel code. This modified method is applied to the ROBIN(ROtor Body Interaction) problem, which had been conducted experimentally in NASA. The calculated results, pressure distribution on fuselage surface and induced inflow ratio without and with the rotor, are compared with the experimental results. The developed code shows not only very accurate prediction of the aerodynamic characteristics for the rotor-fuselage interaction problem but also the rotor wake development.
Aerodynamic Analysis of the Blended Wing Body Type MAV using the Time-Domain Panel Method
Park, Jin-Han ; Cho, Lee-Sang ; Cho, Jin-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 637~646
DOI : 10.5139/JKSAS.2010.38.7.637
A time-domain panel method based on the potential flow theory and the time-stepping method is developed to predict the steady/unsteady aerodynamic characteristics of FM07, which is the BWB (Blended-wing body) type MAV. In the aerodynamic analyses, we used two types of the initial model(Case I) and the improved model(Case II), which is moved the gravity center toward the rear and has larger aspect ratio. In the steady aerodynamic analyses, it is revealed that improved model has higher lift to drag ratio(L/D) and more stable pitch characteristic than those of the initial model. In the unsteady aerodynamic analyses for sudden acceleration motion similar to the launch phase of MAV, it seemed that there is a rapid increase of the lift coefficient after the launch and unsteady results are good agreed compare with steady results in just a few times. In the analysis for pitch oscillation motion, which is occurred at the cruise condition of the FM07, it shows that unsteady aerodynamic coefficients looped around steady results and the improved model has more sensitive aerodynamic characteristics.
Experimental Validation of Ornithopter Aerodynamic Model in Low Reynolds Number Regime
Lee, Jun-Seong ; Kim, Dae-Kwan ; Han, Jae-Hung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 647~654
DOI : 10.5139/JKSAS.2010.38.7.647
In this study, an efficient ornithopter aerodynamic model, which is applicable to ornithopter wing design considering fluid-structure interaction or ornithopter flight dynamics and control simulation, was proposed and experimentally validated through the wind tunnel experiments. Due to the ornithopter aerodynamics governed by unsteady low Reynolds number flow, an experimental device was specially designed and developed. A part of the experimental device, 2-axis loadcell, was situated in the non-inertial frame; the dynamic calibration method was established to compensate the inertial load for pure aerodynamic load measurements. The characteristics of proposed aerodynamic model were compared with the experimental data in terms of mean and root-mean-square values of lift and drag coefficients with respect to the flow speed, flapping frequency, and fixed angle of attack.
Aerodynamic Characteristics of WIG Effect Vehicle with Direct Underside Pressurization
Lee, Ju-Hee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 655~663
DOI : 10.5139/JKSAS.2010.38.7.655
DUP (direct underside pressurization) is a device that can considerably increase lift, reduce take-off speed and minimize hump drag when a WIG effect vehicle takes off on the water surface. A 3-dimensional numerical investigation of a WIG effect vehicle with DUP is performed to analyze aerodynamic characteristics and the static height stability. The model vehicle, named Aircat, consists of a propeller in the middle of a fuselage, an air chamber under the fuselage, Lippisch-type wings and a large horizontal T-tail. The lift is mainly increased by the stagnation of the accelerated air coming into the air chamber through the channel in the middle of the fuselage. However, the accelerated air increases drag as well as reduces static height stability.
Target Observability Analysis of Time-to-go Polynomial Guidance Law
Lee, Chang-Hun ; Kim, Tae-Hun ; Tahk, Min-Jea ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 664~672
DOI : 10.5139/JKSAS.2010.38.7.664
This paper provides the target observability analysis of time-to-go polynomial guidance law with bearing-only measurement. In this study, a direct approach is used to analyze the target observability. Since the observability condition of a constant-velocity target is given by the function of LOS angle only, the target observability characteristic is determined by substituting the closed form solution of LOS angle to the observability condition directly. The analysis results show that the target observability is depended on the choice of guidance gain, initial intercept condition and guidance command shape. After that this mathematical analysis result is evaluated and demonstrated by number of simulation.
Terrain Aided Inertial Navigation for Precise Planetary Landing
Jeong, Bo-Young ; Choi, Yoon-Hyuk ; Jo, Su-Jang ; Bang, Hyo-Choong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 673~683
DOI : 10.5139/JKSAS.2010.38.7.673
This study investigates Terrain Aided Inertial Navigation(TAIN) which consists of Inertial Navigation System (INS) with the optical sensor for precise planetary landing. Image processing is conducted to extract the feature points between measured terrain data and on-board implemented terrain information. The navigation algorithm with Iterated Extended Kalman Filter(IEKF) can compensate for the navigation error, and provide precise navigation information compared to single INS. Simulation results are used to demonstrate the feasibility of integration to accomplish precise planetary landing. The proposed navigation approach can be implemented to the whole system coupled with guidance and control laws.
A Study on Optimal Earth-Moon Transfer Orbit Design Using Mixed Impulsive and Continuous Thrust
No, Tae-Soo ; Jeon, Gyeong-Eon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 684~692
DOI : 10.5139/JKSAS.2010.38.7.684
Based on the planar restricted three body problem formulation, optimized trajectories for the Earth-Moon transfer are obtained. Mixed impulsive and continuous thrust are assumed to be used, respectively, during the Earth departure and Earth-Moon transfer/Moon capture phases. The continuous, dynamic trajectory optimization problem is reformulated in the form of discrete optimization problem by using the method of direct transcription and collocation, and then is solved using the nonlinear programming software. Representative results show that the shape of optimized trajectory near the Earth departure and the Moon capture phases is dependent upon the relative weight between the impulsive and the continuous thrust.
Attitude and Position Estimation of a Helmet Using Stereo Vision
Shin, Ok-Shik ; Heo, Se-Jong ; Park, Chan-Gook ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 693~701
DOI : 10.5139/JKSAS.2010.38.7.693
In this paper, it is proposed that an attitude and position estimation algorithm based on a stereo camera system for a helmet tracker. Stereo camera system consists of two CCD camera, a helmet, infrared LEDs and a frame grabber. Fifteen infrared LEDs are feature points which are used to determine the attitude and position of the helmet. These features are arranged in triangle pattern with different distance on the helmet. Vision-based the attitude and position algorithm consists of feature segmentation, projective reconstruction, model indexing and attitude estimation. In this paper, the attitude estimation algorithm using UQ (Unit Quaternion) is proposed. The UQ guarantee that the rotation matrix is a unitary matrix. The performance of presented algorithm is verified by simulation and experiment.
Numerical Study on a Reaction Wheel and Wheel-Disturbance Modeling
Kim, Dae-Kwan ; Oh, Shi-Hwan ; Yong, Ki-Lyuk ; Yang, Koon-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 702~708
DOI : 10.5139/JKSAS.2010.38.7.702
Reaction wheel assemblies(RWA) are expected to be one of the largest high frequency disturbance sources to the optical payload of satellites. To ensure the tight pointing-stability budget and high image quality of satellites, a vibration isolation device should be applied to the main disturbances. For developing the isolating system, the disturbances need to be identified and modeled accurately. In the present study, a modeling technique of RWA and its disturbance was described. The micro-vibration disturbances were generated numerically by using an analytical wheel and disturbance model. The parameter estimation scheme of the model was suggested, and the RWA and disturbance modeling technique was verified through the numerical example analysis. The analytical results show that the wheel and disturbance model can be accurately established by using the modeling technique proposed in the present study. The wheel and disturbance model is expected to be useful for development of the RWA isolator system.
Effect Analysis of Guard Band and Quantization Level on BER Performance in OBP Satellite Systems
Kang, Ki-Wan ; Yoon, Dong-Weon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 709~715
DOI : 10.5139/JKSAS.2010.38.7.709
MCDD performs demultiplexing and demodulation of multi-carrier signals for signal processing schemes such as switching, channel encoding and remodulation in an OBP satellite. During the demultiplexing procedure, several factors such as frequency offset and/or quantization error degrade BER performance. Hence, influences of those factors should be reduced. A influence of the frequency offset can be reduced by inserting guard band between channels, and that of quantization error can be decreased by quantization level control. In case that the data rate of system is not limited, the guard band and the quantization level do not affect each other. In the other case, however, mutual influence between them should be considered. In this paper, we observe the mutual influence when the data rate of the MCDD is limited, and analyze the BER performance.
Development of an Automated Aero-Structure Interaction System for Multidisciplinary Design Optimization for the Large AR Aircraft Wing
Jo, Dae-Sik ; Yoo, Jae-Hoon ; Joh, Chang-Yeol ; Park, Chan-Woo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 716~726
DOI : 10.5139/JKSAS.2010.38.7.716
In this research, design optimization of an aircraft wing has been performed using the fully automated Multidisciplinary Design Optimization (MDO) framework, which integrates aerodynamic and structural analysis considering nonlinear structural behavior. A computational fluid dynamics (CFD) mesh is generated automatically from parametric modeling using CATIA and Gambit, followed by an automatic flow analysis using FLUENT. A computational structure mechanics (CSM) mesh is generated automatically by the parametric method of the CATIA and visual basic script of NASTRAN-FX. The structure is analyzed by ABAQUS. Interaction between CFD and CSM is performed by a fully automated system. The Response Surface Method (RSM) is applied for optimization, helping to achieve the global optimum. The optimization design result demonstrates successful application of the fully automated MDO framework.
Development of a Composite Spacecraft Structure for STSAT-3 Satellite Program
Cho, Hee-Keun ; Seo, Jung-Ki ; Kim, Byoung-Jung ; Jang, Tae-Seung ; Cha, Won-Ho ; Lee, Dai-Gil ; Myung, Noh-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 727~736
DOI : 10.5139/JKSAS.2010.38.7.727
A satellite that has an all-composite structure, STSAT-3(science and technology satellite), was initially developed in Korea. Partially use of advanced composites in space applications such as solar panel is well developed, however the application of an all-composite satellite bus has never been achieved in Korea. This study emphasizes the application of composite technology to the design and fabrication of an all-composite spacecraft bus for small-class satellite STSAT-3. Moreover its structure design concept is totally different from the one that was used in the previous satellites developed in Korea.
Operation of the GPS Receiver System for KSLV-I on the Launch Site at Naro Space Center
Kwon, Byung-Moon ; Moon, Ji-Hyeon ; Shin, Yong-Sul ; Choi, Hyung-Don ; Cho, Gwang-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 7, 2010, Pages 737~745
DOI : 10.5139/JKSAS.2010.38.7.737
This paper describes the operation results of the GPS receiver system for KSLV (Korea Space Launch Vehicle)-I on the launch site at Naro Space Center that is the first spaceport of South Korea located at Goheung. All equipments of KSLV-I including the GPS receiver system should be monitored and controlled through hard-wired interface during KSLV-I is on standby at the launch pad. The GPS receiver for KSLV-I is connected to triple almost omni-directional patch antennas mounted on the cylindrical surface of KSLV-I that should be erected vertically on the launch pad until lift-off. Signal interference and multipath effects observed in the GPS receiver on the launch site are analyzed in this paper based on the GPS signals received from each GPS antenna.