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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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2-D Periodic Unsteady Flow Analysis Using a Partially Implicit Harmonic Balance Method
Im, Dong-Kyun ; Park, Soo-Hyung ; Kwon, Jang-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1153~1161
DOI : 10.5139/JKSAS.2010.38.12.1153
An efficient solution method for harmonic balance techniques with Fourier transform is presented for periodic unsteady flow problems. The present partially-implicit harmonic balance treats the flux terms implicitly and the harmonic source term is solved explicitly. The convergence of the partially Implicit method is much faster than the explicit Runge-Kutta harmonic balance method. The method does not need to compute the additional flux Jacobian matrix from the implicit harmonic source term. Compared with fully implicit harmonic balance method, this partial approach turns out to have good convergence property. Oscillating flows over NACA0012 airfoil are considered to verify the method and to compare with results of explicit R-K(Runge-Kutta) and dual time stepping methods.
Development of Dynamic Balancing Techniques of a Rotor System Using Genetic Algorithm
Kwon, Hyuck-Ju ; Yu, Young-Hyun ; Jung, Sung-Nam ; Yun, Chul-Yong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1162~1169
DOI : 10.5139/JKSAS.2010.38.12.1162
The dynamic balancing of a rotor system is needed to alleviate the imbalances originating from various sources encountered during blade manufacturing processes and environmental factors. This work aims at developing a comprehensive analysis system which consists of cumulative module of test D/B and selection of optimal control parameters. This system can be used for the dynamic balancing of helicopter rotors based on tracking results from the whirl tower test. For simplicity of the analysis, a linear relation is assumed between the balancing input parameters and the blade track responses leading to influence coefficients and thereby the rotor system identification is made. In addition, the balancing parameters of the individual blades are sought using the genetic algorithm and the effectiveness of the proposed method is demonstrated in comparison with the test results.
Pitch-axis Maneuver of UAVs by Adaptive Control Approach
Bang, Hyo-Choong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1170~1176
DOI : 10.5139/JKSAS.2010.38.12.1170
This study addresses adaptive control of UAVs(Unmanned Aerial Vehicles) pitch-axis maneuver. The MRAC(Model Referenced Adaptive Control) approach is employed to accommodate uncertainties which are introduced by feedback linearization of pitch attitude control by elevator input. The model uncertainty is handled by adaptation laws which update model parameters while the UAV is under control by the feedback control law. Steady-state pitch attitude achieved by the stabilizing control law is derived to provide insight on the closed-loop behavior of the controlled system. The proposed idea is free of linearization, gain-scheduling procedures, so that one can design high maneuverability of UAVs for pitching motion in the presence of significant model uncertainty.
Actuator Fault Diagnosis of UAVs using Adaptive Unknown Input Observers
Cho, Shin-Je ; Shin, Sung-Sik ; Choi, Seung-Kie ; Moon, Jung-Ho ; Roh, Eun-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1177~1183
DOI : 10.5139/JKSAS.2010.38.12.1177
In this paper, a parallel bank of multiple adaptive unknown input observers approach suggested by D.Wang is applied to detect a single fault of control surface actuator and to estimate the actuator position of lock-in-place fault using a small fixed-wing UAV model with eight control surfaces. This paper shows that not only the fault diagnosis algorithm detects and estimates each faults of lock-in-place in 1 second by simulation but also it may be unavailable to isolate among two same-shaped rudders.
Optimal Trajectory Design of Descent/Ascent phase for a Lunar Lander With Considerable Sub-Phases
Jo, Sung-Jin ; Min, Chan-Oh ; Lee, Dae-Woo ; Cho, Kyeum-Rae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1184~1194
DOI : 10.5139/JKSAS.2010.38.12.1184
The descent and ascent phases for a lunar lander are composed of several phases. Accordingly, the constraints and control values adequate for each phase are required in order to generate optimal lander`s trajectory. The optimal trajectories for descent and ascent phases are generated by the cost function to minimize fuel consumption & attitude variation rates. In this paper, the optimal control problem to make trajectory uses Gauss pseudo-spectral method which is one of the direct approach method. This problem generates lander`s reference trajectory, states and controls.
An Experimental Study of a Diffuser Starting Characteristics for Simulating High-Altitude Environment by using a Liquid Rocket
Lee, Yang-Suk ; Jeon, Jun-Su ; Ko, Young-Sung ; Kim, Yoo ; Kim, Sun-Jin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1195~1201
DOI : 10.5139/JKSAS.2010.38.12.1195
Performance tests of a supersonic exhaust diffuser were conducted by using a liquid rocket engine for simulating high-altitude environment. The experimental setup consisted of a combustion chamber, a vacuum chamber and a diffuser. The combustion tests for simulating high-altitude environment were carried out at three cases by chamber pressure variation(26, 29, 32barg). The test results showed that the diffuser was started at all case and vacuum chamber pressures were approximately 140torr. The starting pressure using combustion gas was similar with that of cold gas, but the vacuum chamber pressure was relatively high because of high temperature in the vacuum chamber. The results of this test can be used as an essential database for the design of real-scale high-altitude simulation test facility in the future.
Required Pressurant Mass for Cryogenic Propellant Tank with Pressurant Temperature Variation
Kwon, Oh-Sung ; Kim, Byung-Hun ; Cho, In-Hyun ; Ko, Young-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1202~1208
DOI : 10.5139/JKSAS.2010.38.12.1202
The prediction of the required pressurant mass for maintaining the pressure of propellant tanks during propellant feeding is an important issue in designing pressurization system. The temperature of pressurant fed into propellant tank is the critical factor in the required pressurant mass and is one of the most crucial design parameters in the development of pressurization system including designing the weight of pressurant tanks and the size of heat exchanger. Hence a series of propellant drainage tests by pressurizing propellant stored in a cryogenic propellant tank have been performed with measuring the temperature distribution inside ullage and the required pressurant mass according to the temperature condition of pressurant. Results shows that the required pressurant mass decreases as the temperature of pressurant increases. However, the rate of the actual pressurant mass to the ideal required pressurant mass increases.
Lightweight Composite Electronics Housing Design of Modular Type for Space Applications
Jang, Tae-Seong ; Cho, Hee-Keun ; Seo, Hyun-Suk ; Kim, Won-Seock ; Rhee, Ju-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1209~1216
DOI : 10.5139/JKSAS.2010.38.12.1209
This paper dealt with an alternative for maximizing mass savings in spacecraft design by replacing conventional aluminum alloy housing used for various spacecraft avionics by composite materials. Key requirements were defined for the purpose of composite housing design with sufficient durability and various functionalities as well as more lightweight characteristics as compared with aluminum alloy widely-used for conventional electronics housing. Conceptual design was also carried out for manufacturing modular, lightweight composite electronic housing equipped with high thermal and electrical conductivities, EMI protection, and radiation shielding characteristics as well as excellent structural performance; feasibility of enhancing mass savings in spacecraft design was presented.
Development of UAV Flight Control Software using Model-Based Development(MBD) Technology
Moon, Jung-Ho ; Shin, Sung-Sik ; Choi, Seung-Kie ; Cho, Shin-Je ; Rho, Eun-Jung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1217~1222
DOI : 10.5139/JKSAS.2010.38.12.1217
This paper describes the Model-Based Development(MBD) process behind the flight control software of a close-range unmanned aerial vehicle(KUS-9). An integrated development environment was created using a commercial tool(MATLAB
), which was utilized to design models for linear/nonlinear simulation, flight control law, operational logic and HILS(Hardware In the Loop Simulation) system. Software requirements were validated through flight simulations and peer reviews during the design process, whereas the models were verified through the application of a DO-178B verification tool. The integrity of automatically generated C code was verified by using a separate S/W testing tool. The finished software product was embedded on two different types of hardware and real-time operating system(uC/OS-II, VxWorks) to perform HILS and flight tests. The key findings of this study are that MBD Technology enables the development of a reusable and an extensible software product and auto-code generation technology allows the production of a highly reliable flight control software under a compressed time schedule.
Multi-band directional antenna for satellite communications
Cheong, Chi-Hyun ; Jeong, Hye-Mi ; Kim, Kun-Woo ; Bae, Ki-Hyoung ; Tae, Hyun-Sik ; Evtyushkin, Gennadiy ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1223~1231
DOI : 10.5139/JKSAS.2010.38.12.1223
The design is presented for a SATCOM antenna capable of simultaneous multi-band (X/Ku/Ka-Band) communications without replacement of feed horns or change of other parts in the application as a ground satellite terminal for large data transfer. The antenna is the offset configuration and consists of a dual-band(X/Ka-band) feed horn, a single-band(Ku-band) feed horn, a frequency selective surface(FSS) sub-reflector and a parabolic main-reflector. The antenna has a main reflector defining a prime focus and a frequency selective surface sub-reflector defining an image focus. A dual-band feed and a single-band feed are provided at each of the prime focus and image focus. The antenna is designed using 3D EM simulator and the gains measured in X/Ku/Ka-band of the complete antenna assembly is more than 31.6dBi, 36.8dBi, 40.8dBi, and the cross polarization is 21.7dB, 26.6dB, 25.2dB, respectively.
Design Verification of Thermal Control Subsystem for EOS-C Ver.3.0 using STM Thermal Vacuum Test Result
Chang, Jin-Soo ; Yang, Seung-Uk ; Jeong, Yun-Hwang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1232~1239
DOI : 10.5139/JKSAS.2010.38.12.1232
A high-resolution electro-optical camera (EOS-C Ver.3.0), the mission payload of an Earth observation satellite, is under development in Satrec Initiative. We designed this system to give improved thermal performance compared with the EOS-C Ver.2.0 which is the main payload of DubaiSat-1 by optimizing the active and passive thermal control design. We developed the Structural-Thermal Model (STM) and verified the design margin by performing the qualification level thermal vacuum test. We also conducted the verification of its Thermal Mathematical Model (TMM) through the thermal balance test. As a result, it was confirmed that TMM faithfully represents the thermal characteristics of the EOS-C Ver.3.0.
Experimental analysis on the characteristics of enthalpy probe immersed in arc plasma flow
Seo, Jun-Ho ; Nam, Jun-Seok ; Choi, Seong-Man ; Hong, Bong-Gun ; Hong, Sang-Hee ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 38, issue 12, 2010, Pages 1240~1246
DOI : 10.5139/JKSAS.2010.38.12.1240
Enthalpy probe with the inner and outer diameters of 1.5 mm and 4.8 mm, respectively, is designed and used to measure the temperatures and velocities along the centerline of Ar arc plasma flow until the probe was destroyed. For this purpose, Ar arc plasma flow is generated by non-transferred type DC arc heater with the power level of 17 kW. From this experiment, it is shown that the designed enthalpy probe can measure the temperature and velocity of arc plasma flow up to 12,000 K and 600 m/s, respectively, without destroy of probe tip. In this extreme case, the arc plasma flow is calculated to transfer the heat flux of
to the probe based on the heat and thermal boundary equations near the forward stagnation point of a body immersed in arc plasma flow. Consequently, the designed enthalpy probe can measure the wide ranges of plasma temperatures, velocities and concentrations simultaneously, which are generated by various types of arc heaters within the heat flux ranges of
on the probe tip.