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REFERENCE LINKING PLATFORM OF KOREA S&T JOURNALS
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International Journal of Aeronautical and Space Sciences
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Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 11, Issue 4 - Dec 2010
Volume 11, Issue 3 - Sep 2010
Volume 11, Issue 2 - Jun 2010
Volume 11, Issue 1 - Mar 2010
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Self-Sensing Composites and Optimization of Composite Structures in Japan
Todoroki, Akira ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 155~166
DOI : 10.5139/IJASS.2010.11.3.155
I review research on self-sensing and structural optimizations of laminated carbon/epoxy composites in Japan. Self-sensing is one of the multiple functions of composites; i.e., carbon fiber is used as a sensor as well as reinforcement. I present a controversial issue in self-sensing and detail research results. Structural optimization of laminated CFRP composites is indispensable in reducing the weights of modern aerospace structural components. I present a modified efficient global search method using the multi-objective genetic algorithm and fractal branch and bound method. My group has focused its research on these subjects and our research results are presented here.
Dynamic Modeling and Stabilization Techniques for Tri-Rotor Unmanned Aerial Vehicles
Yoo, Dong-Wan ; Oh, Hyon-Dong ; Won, Dae-Yeon ; Tahk, Min-Jea ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 167~174
DOI : 10.5139/IJASS.2010.11.3.167
The design, dynamics, and control allocation of tri-rotor unmanned aerial vehicles (UAVs) are introduced in this paper. A trirotor UAV has three rotor axes that are equidistant from its center of gravity. Two designs of tri-rotor UAV are introduced in this paper. The single tri-rotor UAV has a servo-motor that is installed on one of the three rotors, which enables rapid control of its motion and its various attitude changes-unlike a quad-rotor UAV that depends only on the angular velocities of four rotors for control. The other design is called 'coaxial tri-rotor UAV,' which has two rotors installed on each rotor axis. Since the tri-rotor type of UAV has the yawing problem induced from an unpaired rotor's reaction torque, it is necessary to derive accurate dynamic and design control logic for both single and coaxial tri-rotors. For that reason, a control strategy is proposed for each type of tri-rotor, and nonlinear simulations of the altitude, Euler angle, and angular velocity responses are conducted by using a classical proportional-integral-derivative controller. Simulation results show that the proposed control strategies are appropriate for the control of single and coaxial tri-rotor UAVs.
Development of a Simulator of a Magnetic Suspension and Balance System
Lee, Dong-Kyu ; Lee, Jun-Seong ; Han, Jae-Hung ; Kawamura, Yoshiyuki ; Chung, Sang-Joon ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 175~183
DOI : 10.5139/IJASS.2010.11.3.175
The increased demand for a higher performing magnetic suspension and balance system (MSBS) resulted in an increase in costs for the efforts necessary for achieving an improved MSBS. Therefore, MSBS performance should be predicted during the design in order to reduce risk. This paper presents the modeling and simulation of an MSBS that controls 6-degree of freedom (DOF) of an aerodynamic body within the MSBS. Permanent magnets and electromagnets were modeled as coils, and this assumption was verified by experimental results. Finally, an MSBS simulator was developed, predicting that the MSBS is able to contain the model within a bounded region as well as measure external forces acting on the body during wind tunnel tests.
Design of an Initial Fine Alignment Algorithm for Satellite Launch Vehicles
Song, Eun-Jung ; Roh, Woong-Rae ; Kim, Jeong-Yong ; Oh, Jun-Seok ; Park, Jung-Ju ; Cho, Gwang-Rae ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 184~192
DOI : 10.5139/IJASS.2010.11.3.184
In this paper, an initial fine alignment algorithm, which is developed for the strap-down inertial navigation systems of satellite launch vehicles, is considered. For fast and accurate alignment, a simple closed-loop estimation algorithm using a proportional-integral controller is introduced. Through computer simulation for the sway condition in the launch pad, it is shown that a simple filter structure can guarantee fast computational speed that is adequate for real-time implementation as well as the required alignment accuracy and robustness. In addition, its implementation results are presented for the Naro-1 flight test.
Aerodynamic Heating Characteristics Over a Protuberance in Hypersonic Flows Using Fast Response Thermo Gauges
Lee, Hyoung-Jin ; Lee, Bok-Jin ; Jeung, In-Seuck ; Kim, Seoung-Lyoung ; Kim, In-Sun ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 193~200
DOI : 10.5139/IJASS.2010.11.3.193
Through experimental investigations utilizing hypersonic shock tunnel-coaxial thermocouples as well as blow down hypersonic wind tunnel-temperature sensitive paints, the heat flux and the temperature over a protuberance were measured and analyzed. The experimental data were subsequently compared to heat flux data that was obtained by using blow down hypersonic wind tunnel and heat flux gauges. According to the comparison, both sets of data illustrated correlation with one another. The measured heat flux was large when the height of the protuberance was large. Experimental results show that heat flux measurements taken at higher locations were greater than those taken at lower locations. For high protuberances, a severe jump in the heat flux was observed, ranging in values within 0.6-0.7 of the height of the protuberances. However, when the protuberance was sufficiently short, a rise in the heat flux was rarely observed as the protuberance was totally submerged under the separation region.
A Study on the Design of a Pulse-Width Modulation DC/DC Power Converter
Lho, Young-Hwan ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 201~205
DOI : 10.5139/IJASS.2010.11.3.201
DC/DC Switching power converters are commonly used to generate regulated DC output voltages with high-power efficiencies from different DC input sources. A switching converter utilizes one or more energy storage elements such as capacitors, or transformers to efficiently transfer energy from the input to the output at periodic intervals. The fundamental boost converter studied here consists of a power metal-oxide semiconductor field effect transistor switch, an inductor, a capacitor, a diode, and a pulse-width modulation circuit with oscillator, amplifier, and comparator. A buck converter containing a switched-mode power supply is also studied. In this paper, the electrical characteristics of DC/DC power converters are simulated by simulation program with integrated circuit emphasis (SPICE). Furthermore, power efficiency was analyzed based on the specifications of each component.
Optimal Control for Proximity Operations and Docking
Lee, Dae-Ro ; Pernicka, Henry ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 206~220
DOI : 10.5139/IJASS.2010.11.3.206
This paper proposes optimal control techniques for determining translational and rotational maneuvers that facilitate proximity operations and docking. Two candidate controllers that provide translational motion are compared. A state-dependent Riccati equation controller is formulated from nonlinear relative motion dynamics, and a linear quadratic tracking controller is formulated from linearized relative motion. A linear quadratic Gaussian controller using star trackers to provide quaternion measurements is designed for precision attitude maneuvering. The attitude maneuvers are evaluated for different final axis alignment geometries that depend on the approach distance. A six degrees-of-freedom simulation demonstrates that the controllers successfully perform proximity operations that meet the conditions for docking.
A Numerical Study of the High-Velocity Impact Response of a Composite Laminate Using LS-DYNA
Ahn, Jeoung-Hee ; Nguyen, Khanh-Hung ; Park, Yong-Bin ; Kweon, Jin-Hwe ; Choi, Jin-Ho ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 221~226
DOI : 10.5139/IJASS.2010.11.3.221
The failure of a Kevlar29/Phenolic composite plate under high-velocity impact from an fragment simulation projectile was investigated using the nonlinear explicit finite element code, LS-DYNA. The composite laminate and the impactor were idealized by solid elements, and the interface between the laminas was modeled as a tiebreak type in LS-DYNA. The interaction between the impactor and laminate was simulated using a surface-to-surface eroding contact algorithm. When the stress level meets the given failure criteria, the layer in the element is eroded. Numerical results were verified through existing test results and showed good agreement.
Optimization of Composite Laminates Subjected to High Velocity Impact Using a Genetic Algorithm
Nguyen, Khanh-Hung ; Ahn, Jeoung-Hee ; Kweon, Jin-Hwe ; Choi, Jin-Ho ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 227~233
DOI : 10.5139/IJASS.2010.11.3.227
In this study, a genetic algorithm was utilized to optimize the stacking sequence of a composite plate subjected to a high velocity impact. The aim is to minimize the maximum backplane displacement of the plate. In the finite element model, we idealized the impactor using solid elements and modeled the composite plate by shell elements to reduce the analysis time. Various tests were carried out to investigate the effect of parameters in the genetic algorithm such as the type of variables, population size, number of discrete variables, and mutation probability.
Calibration of Inertial Measurement Units Using Pendulum Motion
Choi, Kee-Young ; Jang, Se-Ah ; Kim, Yong-Ho ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 234~239
DOI : 10.5139/IJASS.2010.11.3.234
The utilization of micro-electro-mechanical system (MEMS) gyros and accelerometers in low-level inertial measurement unit (IMU) influences cost effectiveness in a positive way under the condition that device error characteristics are fully calibrated. The conventional calibration process utilizes a rate table; however, this paper proposes a new method for achieving reference calibration data from the natural motion of pendulum to which the IMU undergoing calibration is attached. This concept was validated with experimental data. The pendulum angle measurements correlate extremely well with the solutions acquired from the pendulum equation of motion. The calibration data were computed using the regression method. The whole process was validated by comparing the measurement from the 6 sensor components with the measurements reconstructed using the identified calibration data.
Model Identification and Attitude Control Methodology for the Flexible Body of a Satellite
Lho, Young-Hwan ;
International Journal of Aeronautical and Space Sciences, volume 11, issue 3, 2010, Pages 240~245
DOI : 10.5139/IJASS.2010.11.3.240
The controller of a model reference adaptive control monitors the plant's inputs and outputs to acknowledge its characteristics. It then adapts itself to the characteristics it encounters instead of behaving in a fixed manner. An important part of every adaptive scheme is the adaptive law for estimating the unknown parameters on line. A more precise model is required to improve performance and to stabilize a given dynamic system, such as a satellite in which performance varies over time and the coefficients change due to disturbances, etc. After model identification, the robust controller (
) is designed to stabilize the rigid body and flexible body of a satellite, which can be perturbed due to disturbance. The result obtained by the
controller is compared with that of the proportional and integration controller which is commonly used for stabilizing a satellite.