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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 40, Issue 12 - Dec 2012
Volume 40, Issue 11 - Nov 2012
Volume 40, Issue 10 - Oct 2012
Volume 40, Issue 9 - Sep 2012
Volume 40, Issue 8 - Aug 2012
Volume 40, Issue 7 - Jul 2012
Volume 40, Issue 6 - Jun 2012
Volume 40, Issue 5 - May 2012
Volume 40, Issue 4 - Apr 2012
Volume 40, Issue 3 - Mar 2012
Volume 40, Issue 2 - Feb 2012
Volume 40, Issue 1 - Jan 2012
Selecting the target year
Development of Multi-body Dynamics Analysis Program with Constraints using CFEM
Park, Sun-Ho ; Lee, Seung-Soo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 101~107
DOI : 10.5139/JKSAS.2012.40.2.101
In this study, Constraint Force Equation Methodology (CFEM) is used to develop a multi-body dynamic analysis program with constraints. Seven constraint models are implemented to analyze constraint motions of multiple bodies. The augmented equations with the constraints are solved with the 4th order Runge-Kutta method for higher degree of accuracy. The analysis code is verified by comparing the analysis results of the motion of bodies with various constraints to published results.
A Performance Comparison of Nonlinear Kalman Filtering Based Terrain Referenced Navigation
Mok, Sung-Hoon ; Bang, Hyo-Choong ; Yu, Myeong-Jong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 108~117
DOI : 10.5139/JKSAS.2012.40.2.108
This paper focuses on a performance analysis of TRN among various nonlinear filtering methods. In a TRN research, extended Kalman filter(EKF) is a basic estimation algorithm. In this paper, iterated EKF(IEKF), EKF with stochastic linearization(SL), and unscented Kalman filter(UKF) algorithms are introduced to compare navigation performance with original EKF. In addition to introduced sequential filters, bank of Kalman filters method, which is one of the batch method, is also presented. Finally, by simulating an artificial aircraft mission, EKF with SL was chosen as the most consistent filter in the introduced sequential filters. Also, results suggested that the bank of Kalman filters can be alternative for TRN, when a fast convergence of navigation solution is needed.
Target Tracking Control of a Quadrotor UAV using Vision Sensor
Yoo, Min-Goo ; Hong, Sung-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 118~128
DOI : 10.5139/JKSAS.2012.40.2.118
The goal of this paper is to design the target tracking controller for a quadrotor micro UAV using a vision sensor. First of all, the mathematical model of the quadrotor was estimated through the Prediction Error Method(PEM) using experimental input/output flight data, and then the estimated model was validated via the comparison with new experimental flight data. Next, the target tracking controller was designed using LQR(Linear Quadratic Regulator) method based on the estimated model. The relative distance between an object and the quadrotor was obtained by a vision sensor, and the altitude was obtained by a ultra sonic sensor. Finally, the performance of the designed target tracking controller was evaluated through flight tests.
Multidisciplinary Design Optimization(MDO) of a Medium-Sized Solar Powered HALE UAV Considering Energy Balancing
Park, Kyung-Hyun ; Min, Sang-Gyu ; Ahn, Jon ; Lee, Dong-Ho ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 129~138
DOI : 10.5139/JKSAS.2012.40.2.129
A MDO study of a midium-sized solar powered High Altitude Long Endurance (HALE) UAV has been performed, focused on energy balance. In the MDO process, Vortex Lattice Method(VLM) is employed for the aerodynamic modeling of the vehicle, of which structural weight is estimated with the modeling proposed by Cruz. Tail volume ratios have been set as constants, while the location of tail surfaces is determined from longitudinal static stability criterion. By balancing the available energy from solar cells, battery, and altitude, with the energy-requirement of the vehicle, the possibility of continuous flight over 24-hours has been investigated. The solar radiation level is set as that of summer at the latitude of
north. During the daytime, the aircraft climbs using solar energy, accumulating potential energy, which supplements energy balance during the night. Optimizations have been sought in size of the vehicle, its weight distribution, and flight strategy.
Low Speed Aerodynamic Characteristic of Modified Sonic Arc Airfoil
Lee, Jang-Chang ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 139~145
DOI : 10.5139/JKSAS.2012.40.2.139
The low speed aerodynamic characteristics of modified sonic arc airfoil which is developed to fit the transonic regime are investigated. This airfoil is designed by using the shape function of sonic arc proposed by Schwendenman, the data of NACA0012, and commercial program Maple. In order to investigate the low speed aerodynamic characteristic of sonic arc airfoil, the numerical analysis is conducted below Mach number 0.3 and the results are compared and analyzed with it of NACA0012 airfoil. At each Mach number, the drag of modified sonic arc airfoil is less 1.5% than NACA0012's drag and the lift of modified sonic arc airfoil is less 2% than NACA0012's lift. The moment coefficient of modified sonic arc airfoil is also less 1.4% than it of NACA0012 at each Mach number.
Scaling Methods for Icing Wind Tunnel Test
An, Young-Gab ; Myong, Rho-Shin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 146~156
DOI : 10.5139/JKSAS.2012.40.2.146
In-flight icing remains as one of the most persistent hazards for aircraft operations. The effect of icing on aircraft performance and safety has to be evaluated during the development and airworthiness certification process. The scaling method is a procedure to determine the scaled test conditions in icing wind tunnels in order to produce the same result as when the reference model is exposed to the desired cloud conditions. In this study, a scaling program is developed to provide an easy-to-use tool to the aero-icing community. The Olsen and Ruff 4th methods are employed for this purpose and the velocity is calculated by matching the dimensionless Weber number. To validate the program, the results are compared with the NASA scaling results. The scaling examples based on FAR (Federal Aviation Regulation) Part 25 Appendix C are also presented. Finally, a validation study using a state-of-the-art icing simulation code FENSAP-ICE is presented.
Study on the Thermal Radiation Performance of the Multi-functional Structure Made of the Carbon Fiber Composite Material
Kim, Taig-Young ; Hyun, Bum-Seok ; Seo, Young-Bae ; Jang, Tae-Seong ; Seo, Hyun-Suk ; Lee, Jang-Joon ; Kim, Won-Seock ; Rhee, Ju-Hun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 157~164
DOI : 10.5139/JKSAS.2012.40.2.157
The design strategy of the multi-functional structure is that the electrical components and the circuits are directly put on their supporting structural panel in which the radiation shields and the thermal control functions are integrated. Applying the multi-functional structure reduces the total mass and size of the space system and makes it possible to lower launch cost. In present study the performance of thermal radiation for six types of multi-functional structure are investigated by the numerical method. The effect of the rib configuration on heat transfer for the multi-functional-structure is not important alone but is meaningful considering with the structural stiffness, difficulty of manufacturing and mass increase. In heat spreading point of view, the thickness of the outer conductive layer is important rather than the rib configuration and the trade-off study with the mass and thickness is required for optimum design.
The Study on Experimental Measurement Method of Hinge Moment Acting on Control Surface of Air Vehicle
Park, Jong-Min ; Chung, Sang-Joon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 165~170
DOI : 10.5139/JKSAS.2012.40.2.165
This paper contains the test method to obtain aerodynamic hinge moments acting on the control surface of air vehicle wing. During the flight, hinge moments make difference between actual control surface angle and control angle which is measured by sensor of actuator. The hinge moments can be obtained by using this difference. Static ground load test and calibration test were conducted to obtain torsional stiffness of control surface actuation system. This results are used to calculate hinge moments. In addition, the mechanical errors of actuation system such as slip angle of mounting point and backlash could be estimated. Using flight test results, this experimental measurement method of hinge moment acting on control surface is conducted. The results of this method are similar to those of numerical simulation method, and the validity of this method is proved.
Research on Algorithm and Operation Boundary for Fault Detection of Onboard GNSS Receiver
Nho, Hyung-Tae ; Ahn, Jong-Sun ; Sung, Sang-Kyung ; Jun, Hyang-Sig ; Yeom, Chan-Hong ; Lee, Young-Jae ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 171~177
DOI : 10.5139/JKSAS.2012.40.2.171
In this paper, we proposed a algorithm and an operation boundary for fault detection of a onboard GNSS receiver. After aircraft exchange corrections computed by an aircraft receiver, a faulty aircraft receiver is detected by checking consistency of correction. For this purpose, PRC residual is used as the test statistic for fault detection of the onboard GNSS receiver. And operation boundaries are set by using DGPS position error increase with respect to the distance from a reference station. If the fault detection is performed by using aircraft only in operation boundary, the more accurate fault detection can be possible.
Analytical Investigation of In-direct Heater to Simulate Space Thermal Environment for Thermal Vacuum Test
Baek, Cheul-Woo ; Shin, So-Min ; Oh, Hyun-Ung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 178~183
DOI : 10.5139/JKSAS.2012.40.2.178
To simulate space thermal environment in thermal vacuum test, direct or in-direct heater has been applied on the radiator. Both of them, direct heater attached on the radiator and indirect heater with a distance from the radiator, simulate the heat fluxes from the Sun radiation, the Earth IR and Albedo. They also supply the heat fluxes to the radiator of spacecraft to achieve the target temperature according to thermal test conditions. In general, indirect heater is used when the heater is not allowed to attach on the radiator directly due to constraints of coating property or contamination. For in-direct heater design, it is needed to estimate the heat power to make the extreme test conditions and minimize the interference with heat exchange of radiator and shroud. In this study, optimized thermal design of in-direct heater is proposed and investigated by commercial S/W SINDA. The effective values of design factors are also derived.
500 lbs-class Air-to-Surface Missile Design by Integration of Aerodynamics and RCS
Bae, Hyo-Gil ; Lee, Kwang-Ki ; Jeong, Jun-O ; Sang, Dae-Kyu ; Kwon, Jang-Hyuk ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 40, issue 2, 2012, Pages 184~191
DOI : 10.5139/JKSAS.2012.40.2.184
Aerodynamic analysis(DATCOM) and radar cross section(RCS) analysis(POFACETS) were integrated for the air-to-surface missile concept design using a design framework. The missile geometry was defined based on the CAD(CATIA) for synchronizing the manufacturing with design processes. Aero/RCS analyses were linked with the CAD process under the ModelCenter framework in order to receive the geometry data automatically. The missile design baseline configuration was selected from ROC(requirement of capability). Then the RCS minimization was performed subject to thelargerthebetter constraint of the missile lift-to-drag ratio. This study demonstrated that various design strategies can be performed efficiently about many missile configurations using this design framework in the missile conceptual design phase.