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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
Journal Basic Information
Journal DOI :
The Korean Society for Aeronautical & Space Sciences
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Volume & Issues
Volume 43, Issue 12 - Dec 2015
Volume 43, Issue 11 - Nov 2015
Volume 43, Issue 10 - Oct 2015
Volume 43, Issue 9 - Sep 2015
Volume 43, Issue 8 - Aug 2015
Volume 43, Issue 7 - Jul 2015
Volume 43, Issue 6 - Jun 2015
Volume 43, Issue 5 - May 2015
Volume 43, Issue 4 - Apr 2015
Volume 43, Issue 3 - Mar 2015
Volume 43, Issue 2 - Feb 2015
Volume 43, Issue 1 - Jan 2015
Selecting the target year
Development of robust flocking control law for multiple UAVs using behavioral decentralized method
Shin, Jongho ; Kim, Seungkeun ; Suk, Jinyoung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 859~867
DOI : 10.5139/JKSAS.2015.43.10.859
This study proposes a robust formation flight control technique of multiple unmanned aerial vehicles(UAVs) using behavior-based decentralized approach. The behavior-based decentralized method has various advantages because it utilizes information of neighboring UAVs only instead of information of whole UAVs in the formation maneuvering. The controllers in this paper are divided into two methods: first one is based on position and velocity of neighboring UAVs, and the other one is based on position of neighboring UAVs and passivity technique. The proposed controllers assure uniformly ultimate boundedness of closed-loops system under time varying bounded disturbances. Numerical simulations are performed to validate the effectiveness of the proposed method.
Study on Spray characteristics of Dual-Manifold Injector with Various Tangential Entries
Lee, Ingyu ; Jeong, Seokgyu ; Yoon, Jungsoo ; Park, Gujeong ; Yoon, Youngbin ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 868~874
DOI : 10.5139/JKSAS.2015.43.10.868
Thrust variation is an essential parameter in a space mission such as landing on an atmosphereless planet or docking a spacecraft. In order to achieve the thrust variation control, using throttleable injector is a representative and general method. A dual-manifold injector, one of throttleable injectors, was used to control mass flow rate. Five kinds of injectors were designed and investigated in order to compare the spray characteristics of the dual-manifold injector with various tangential entries. Spray angles and patterns were measured to determine external flow characteristics and film thicknesses were measured in order to investigate the internal flow patterns.
3D Optimal Layout Design of Satellite Equipment
Yeom, Seung-Yong ; Kim, Hong-Rae ; Chang, Young-Keun ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 875~887
DOI : 10.5139/JKSAS.2015.43.10.875
The optimal layout design is used in the development of various areas of industry. In the field of space systems, components must be placed properly in the limited space of spacecraft by considering mechanical, thermal and electrical interfaces. When applying optimal layout design, a proper, even ideal placement of components is possible in the limited space of a satellite platform. Through the optimal placement design, the minimized moment of inertia enhances efficient attitude control, rapid maneuver and mission performance of the satellite. This paper proposes 3D optimal layout design that minimizes the spacecraft`s moment of inertia and effect of thermal dissipation between inner components as well as interference between inner components based on a cubic-structure satellite platform. This study proposes the new genetic algorithm for 3D optimal layout design of the satellite platform.
Prediction of the Blade Flapping Angle for Korean Utility Helicopter by Applying Indirect Method
Kim, Young-Jin ; Lee, Sang-Gi ; Lee, Seung-Jae ; Chang, In-ki ; Shim, Dai-Sung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 888~895
DOI : 10.5139/JKSAS.2015.43.10.888
This paper shows an approximate equation which calculates a flapping angle of blade for verification of KUH safety area. The flapping behavior of blade must be reviewed in an aspect of safety because of a collision possibility with airframe. However, it is difficult to measure an exact flapping angle during flight. A prediction equation of a coning angle is derived from aeromechanics and that of a dynamic flapping angle is derived from analysis results in development phase, respectively. Following, the equations are verified by comparison the flapping angle through an aircraft simulation test to a calculation. Finally, the safety area, which was established in development phase, is verified by calculating a flapping angle during the flight which is required by the terms of safety based on AC29 and FAR29.
Investigation of thermal deformation of wing skin induced by temperature gradient
Kim, Jeong-Beom ; Kim, Hong-Il ; Kim, Jae-Young ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 896~901
DOI : 10.5139/JKSAS.2015.43.10.896
The skin-frame type structure is designed to investigate the thermal deformation of the wing skin induced by the temperature gradient. In order to effectively simulate the temperature gradient on the wing specimen, a water cooling system is devised on the frame of the specimen. Out of surface skin deformation of the skin-frame type structure made of SUS304 material with respect to the temperature is successfully measured using the digital image correlation (DIC) technique including quantitative evaluation of the measurement uncertainty.
Mono-Vision Based Satellite Relative Navigation Using Active Contour Method
Kim, Sang-Hyeon ; Choi, Han-Lim ; Shim, Hyunchul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 902~909
DOI : 10.5139/JKSAS.2015.43.10.902
In this paper, monovision based relative navigation for a satellite proximity operation is studied. The chaser satellite only uses one camera sensor to observe the target satellite and conducts image tracking to obtain the target pose information. However, by using only mono-vision, it is hard to get the depth information which is related to the relative distance to the target. In order to resolve the well-known difficulty in computing the depth information with the use of a single camera, the active contour method is adopted for the image tracking process. The active contour method provides the size of target image, which can be utilized to indirectly calculate the relative distance between the chaser and the target. 3D virtual reality is used in order to model the space environment where two satellites make relative motion and produce the virtual camera images. The unscented Kalman filter is used for the chaser satellite to estimate the relative position of the target in the process of glideslope approaching. Closed-loop simulations are conducted to analyze the performance of the relative navigation with the active contour method.
Computation Algorithm for Launch Acceptability Region of Air-to-Surface Missiles
Park, Sang-Sup ; Hong, Ju-Hyeon ; Ryoo, Chang-Kyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 910~919
DOI : 10.5139/JKSAS.2015.43.10.910
A weapon control algorithm equipped on a fighter is closely related to the mission accomplishment and fighter survivability during the engagement. In the case of a air-to-surface missile, the weapon control algorithm typically provides a pilot the target shoot-down possible region known as launch acceptability region(LAR) in the multi function display(MFD). LAR is produced by the range table(RT) through computation of an engagement range. In this paper, the operation system of AGM-84 and AGM-88 air-to-surface missiles is introduced. And the engagement range computation and LAR algorithm based on the real-time pseudo 6-DOF simulation are proposed. In order to verify the performance of the algorithm, numerical engagement simulations of air-to-surface missiles to produce LAR have been done.
Blade Analysis Library Development of Dimension Reducible Modeling and Recovery Analysis for Composite Rotor Blades
Jang, Jun Hwan ; Lee, Hwan ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 920~927
DOI : 10.5139/JKSAS.2015.43.10.920
In this paper, numerical results of sectional analysis and stress recovery were compared with the results of VABS through the blade analysis library. The results of recovery analysis for one-dimensional model including the stiffness matrix is compared with the calculated three-dimensional stress results of three-dimensionial FEM based on the principle of virtual work. We discuss the configuration of the blade analysis library and compare verifications of numerical analysis results of VABS. Blade analysis library through dimensional reduction and stress recovery is intended to be utilized in conjunction with pre- and post-processing of the analysis program of the composite blade, high-altitude uav`s wing, wind blades and tilt rotor blade.
Low Temperature Structural Tests of a Composite Wing with Room Temperature-Curing Adhesive Bond
Ha, Jae Seok ; Park, Chan Yik ; Lee, Kee Bhum ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 928~935
DOI : 10.5139/JKSAS.2015.43.10.928
This paper presents low temperature structural tests of a UAV wing which has room temperature-curing adhesive bond. The wing structure is made of carbon fiber reinforced composites, and the skins are bonded to the inner structures (such as ribs and spars) using room temperature-curing adhesive bond. Also, to verify damage tolerance design of the wing structure, barely visible impact damages are intentionally created in the critical areas. The attachment fittings of the wing are fixed in a specially designed chamber which can simulate the low temperature environments of the operating altitudes. The test load is applied by hydraulic actuators which are placed outside the chamber. The structural tests consist of strain survey tests and a durability test for 1-life fatigue load spectrum. During the tests, strains of major parts are measured by strain gauges and FBG sensors. The change of the initial impact damages is also monitored using piezoelectric sensors. The 1-life damage tolerance of the composite structure is verified by the structural tests under the simulated environments.
Trend Analysis based Strategy Evaluation for Launch Vehicle Industry in Korea
Hong, Seulki ; Ahn, Jaemyung ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 43, issue 10, 2015, Pages 936~942
DOI : 10.5139/JKSAS.2015.43.10.936
This paper suggests the significant strategies and their priority to deal with space transportation market trends. First, market trends related with technical improvement and change in demand are analyzed by the literature research. The three key trends are obtained: `Increasing Demand of High-Performance Launch Vehicles`, `Rising of Low-Price Launch Vehicles`, and `Rising of Dual/Multi-Launch`. And then, strategies for developing the launch vehicle industry in Korea are selected from several studies about commercialization of Korean launch vehicle. The strategies are evaluated by the experts through pairwise comparison matrix and the criteria for this process is how significantly does the strategy effect on the launch vehicle industry through market assessment. As a result, reliable order of priority among the strategies are obtained. Under the three key trends, strategy to enhance reliability is most important. And, strategy to have price competitiveness has secondary priority to deal with `Rising of Low-Price Launch Vehicles` trend and `Rising of Dual/Multi-Launch` trend. On the contrary, strategy of government`s support is secondary under `Increasing Demand of High-Performance Launch Vehicles` trend.