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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 42, Issue 12 - Dec 2014
Volume 42, Issue 11 - Nov 2014
Volume 42, Issue 10 - Oct 2014
Volume 42, Issue 9 - Sep 2014
Volume 42, Issue 8 - Aug 2014
Volume 42, Issue 7 - Jul 2014
Volume 42, Issue 6 - Jun 2014
Volume 42, Issue 5 - May 2014
Volume 42, Issue 4 - Apr 2014
Volume 42, Issue 3 - Mar 2014
Volume 42, Issue 2 - Feb 2014
Volume 42, Issue 1 - Jan 2014
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The study of data transfer method non-matching meshes interface using common-refinement method for fluid-structure interface
Han, Sangho ; Kim, Donghyun ; Lee, Changsoo ; Kim, Chongam ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 191~198
DOI : 10.5139/JKSAS.2014.42.3.191
During multi-physics or multi-phase simulations accompanying fluid- structure- thermal interaction, data transfer problems always arise along non- matching interfaces caused by different computational meshes for each physical domain. Common- refinement scheme, among many available methods, is attractive since it is known to yield conservative and accurate data transfer for non- matching interface cases. This is particularly important in simulating compressible unsteady fluid- structure- thermal interaction inside solid propellant rockets, where grid size along solid- fluid interfaces is substantially different. From this perspective, we examine performances of common- refinement- based data transfer scheme between structured quadrilateral (structure part) and unstructured triangular (fluid part) meshes by comparing computed results with other data transfer methods.
Design of an Autonomous Air Combat Guidance Law using a Virtual Pursuit Point for UCAV
You, Dong-Il ; Shim, Hyunchul ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 199~212
DOI : 10.5139/JKSAS.2014.42.3.199
This paper describes an autonomous air combat guidance law using a Virtual Pursuit Point (VPP) in one-on-one close engagement for Unmanned Combat Aerial Vehicle (UCAV). The VPPs that consist of virtual lag and lead points are introduced to carry out tactical combat maneuvers. The VPPs are generated based on fighter`s aerodynamic performance and Basic Fighter Maneuver (BFM)`s turn circle, total energy and weapon characteristics. The UCAV determines a single VPP and executes pursuit maneuvers based on a smoothing function which evaluates probabilities of the pursuit types for switching maneuvers with given combat states. The proposed law is demonstrated by high-fidelity real-time combat simulation using commercial fighter model and X-Plane simulator.
Prediction of Trajectories of Projectiles Launched from Helicopters
Gong, Hyojoon ; Kwak, Einkeun ; Lee, Seungsoo ; Park, Jae Seong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 213~220
DOI : 10.5139/JKSAS.2014.42.3.213
A program that predicts trajectories of projectiles influenced by the interference flow field of helicopters is developed. The interference flow field are computed using a compressible inviscid solver in conjunction with an actuator disc model. The trajectories are predicted using 6-DOF (Degree of Freedom) equations as well as an alternative form of modified point mass equations of motion. The method for the interference flow field prediction method are validated with ROBIN(ROtor Body INteraction) model. A Sierra international bullet and a 105mm projectile are used to validate the trajectory method. Trajectories of a Sierra International bullet and a HYDRA 70 rocket firing from a helicopter are predicted.
Development of Flight Control System for Gliding Guided Artillery Munition - Part I : Operational Concept and Navigation
Lim, Seunghan ; Pak, Changho ; Cho, Changyeon ; Bang, Hyochoong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 221~228
DOI : 10.5139/JKSAS.2014.42.3.221
In this paper, the operational concept and the navigation algorithms for the gliding guided artillery munition are studied. The gliding guided artillery munition has wings for gliding; therefore spin of the munition should be eliminated. The previous navigation algorithms assumed a spinning munition with constant angular velocity; hence, they cannot be applied for the gliding munition. Moreover, lateral stability becomes worse due to decrease of angular momentum. Therefore, side force should be controlled to improve the stability, and the munition should maneuver, then the previous navigation algorithms for typical fixed-wing aircraft cannot be applied. In this paper, we apply the previous navigation algorithms for the spinning munition. Spin is eliminated and wings are deployed based on the estimation results, and the advanced navigation algorithm for the non-spinning munition is introduced.
Development of Flight Control System for Gliding Guided Artillery Munition - Part II : Guidance and Control
Lim, Seunghan ; Pak, Changho ; Cho, Changyeon ; Bang, Hyochoong ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 229~236
DOI : 10.5139/JKSAS.2014.42.3.229
In this paper, the guidance laws and controllers for the gliding guided artillery munition is studied. The gliding guided artillery munition has wings for gliding to increase a range; therefore previous guidance laws and controllers for the guided munition could not be applied. Concepts of vector field guidance and proportional navigation guidance are applied for mid-term and terminal guidance, respectively. The gliding guided artillery munition is operated within wide altitude and speed areas; therefore, the controllers are designed for each area, and gain-scheduling and the linear interpolation technique is applied to compute the appropriate gains.
Control System of Turbofan Engine with Variable Inlet Guide Vane
Bae, Kyoungwook ; Min, Chanoh ; Cheon, Bongkyu ; Lee, Changyong ; Lee, Daewoo ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 237~242
DOI : 10.5139/JKSAS.2014.42.3.237
Surge phenomenon can be occurred in a compressor when the performance of turbofan engine for an aircraft is changed considerably such as take-off phase. This study is aimed to avoid surge phenomenon. This paper propose the PID and Fuzzy control System for the turbofan engine with control inputs, the VIGV(Variable Inlet Guide Vane) in closed loop, and the fuel mass flow in open loop. We design the Dynamic modeling, NPSS S-function, which is connection block of simulink between NPSS(Engine analysis program) and Simulink. Finally, we certify the performance to prevent a serge phenomenon in the VIGV control system using the both methods, PID and fuzzy.
Attitude Control using Quantitative Feedback Theory of a Quad-Rotor Vehicle with Plant Parametric Uncertainty
Lee, ByungSeok ; Heo, Moon-Beom ; Lee, Joon Hwa ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 243~253
DOI : 10.5139/JKSAS.2014.42.3.243
This paper deals with the Quantitative Feedback Thoery(QFT) guaranteeing robustness in spite of the plant parametric uncertainty. In the frequency domain, the QFT guarantees the robustness of the design specification on the uncertainty of plant parameters and disturbance. In order to use the QFT, a selected plant is a Quad Rotor Vehicle(QRV) which has excellent maneuverability and possibility of vertical take-off and landing like the helicopter. And attitude control is examined the possibility satisfied the requirement specification under the setting parametric uncertainty of motors driving 4-blades. Additionally, in an attitude control, the pre-filter considering parameter range and operating range of a QRV was used. For these purpose, in this paper, by using QFTCT, that is the QFT Control Toolbox designing the controller in MATLAB by the QFT, each design phases are introduced.
Task Scheduling and Multiple Operation Analysis of Multi-Function Radars
Jeong, Sun-Jo ; Jang, Dae-Sung ; Choi, Han-Lim ; Yang, Jae-Hoon ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 254~262
DOI : 10.5139/JKSAS.2014.42.3.254
Radar task scheduling deals with the assignment of task to efficiently enhance the radar performance on the limited resource environment. In this paper, total weighted tardiness is adopted as the objective function of task scheduling in operation of multiple multi-function radars. To take into account real-time implementability, heuristic index-based methods are presented and investigated. Numerical simulations for generic search and track scenarios are performed to evaluate the proposed methods, in particular investigating the effectiveness of multi-radar operation concepts.
Flight data analysis and visualization program development
Park, Young-Keun ; Lee, Sung-Jin ; Lee, Gi-Doo ; Lim, Sang-Soo ; Lee, In-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 263~269
DOI : 10.5139/JKSAS.2014.42.3.263
Flight test data visualization functions can improve an understanding of flight test results, test procedures, and the performance of a flight vehicle after flight tests. FlyingView was developed for researchers to analyse flight test data in a 3D virtual environment. It also can display X-Y plots using flight test data. It was developed and applied to flight tests of an air-to-ground weapon system of ADD. This paper describes the capabilities of FlyingView.
A Study on Enhancement of Orbit Prediction Precision for Space Objects Using TLE
Yim, Hyeonjeong ; Jung, Ok-Chul ; Chung, Dae-Won ;
Journal of the Korean Society for Aeronautical & Space Sciences, volume 42, issue 3, 2014, Pages 270~278
DOI : 10.5139/JKSAS.2014.42.3.270
This paper describes an improvement of space objects orbit prediction. To screen possible collisions between operational satellites and space objects, the TLE (Two-Line Element) was used as pseudo-measurement and than the orbit determination and orbit prediction were performed through the flight dynamics system. For determining the orbits, the state vectors were assumed by a series of TLEs within a certain period. The propagation error was analyzed according to the fitting period and a number of pseudo-observations. In order to find out the improvement of orbit prediction with the proposed method, KOMPSAT-2, 3 having the precise orbit in the meter-level range were first applied. Then the result applied to space objects under the same conditions was analyzed. As a result of the RMS error comparison with the orbit prediction of space object, the precision of orbit prediction was improved by approximately 90% for seven days prediction. The improved orbit prediction of space objects can be utilized in the daily analysis for initial screening of the close space objects at high risk.