• Transactions of the KSME C: Technology and Education
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• v.3 no.3
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• pp.183-191
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• 2015

In this study, the finite element analysis was carried out to investigate dynamic characteristics of the AGF(Active Gurney Flap) which is under development for reducing vibration and noise of the helicopter rotor system. The Gurney flap is a kind of small flat plate, mounted normal to the lower surface of the airfoil near to the trailing edge. An electric motor, L-shaped linkages and flap parts were integrated into a rotor bade, and 3~5/rev control was given to the AGF to reduce the vibration in the fixed frame. Thus, an explicit time integration method was adopted to investigate the dynamic response of the AGF with considering both centrifugal force due to the rotor rotation and active control input, and it can be seen that the vertical displacement of the AGF was satisfied to meet the design requirement.

• Fire Science and Engineering
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• v.34 no.1
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• pp.79-88
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• 2020

This study analyzes the issue of the supply of force of fire in the high-rise buildings, and proposes an efficient method to do so. The results are as follows. First, in terms of Detect fire, it is necessary to shorten force of fire supply time by diversifying fire alarms such as alarms, vibrations, and voices from outside, clarification of fire occurrence points, and marking of fire. Second, with regard to communication signals, strengthening the installation target of wireless communication auxiliary facilities, supplementing the installation of repeaters, and constructing a multicommunications network were proposed. Third, in terms of Decide action, it is necessary to supply firefighter and firefighting equipment with the method of crossing of a river in adjacent buildings. Fourth, in terms of Respond to site, helicopters and emergency elevators are used to assist in the supply of firefighting equipment using drones. Easy-to-break glass windows and identification marks are required in every floor. Finally, in terms of applying fire suppressants, water can be supplied by means of a helicopter adjacent to the structure.

• Journal of the Korean Society of Propulsion Engineers
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• v.1 no.2
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• pp.84-90
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• 1997

The turboshaft engine with the free power turbine has been used for various purposes, for instance electric power generator, emergency power source, helicopter powerplant and so on. Steady-state simulation program was developed and experimental tests was carried out for comparing with computer simulation results. The test unit was composed of 1-stage centrifugal compressor, the can type combustor chamber, 1-stage radial type compressor turbine, and radial type free power turbine, and its output power is obtained from 3-phase AC generator. Main component characteristics which was used for the steady state simulation program, were obtained from the manufacturer of the test unit, and modified from experimental results of test unit. In comparison between computer simulation and experimental test results even though the test unit has the operational limit, deviation of component performance characteristics in simulation were within 6％ range of experimental results.

• Journal of Fisheries and Marine Sciences Education
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• v.29 no.1
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• pp.137-147
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• 2017

An accident during pilotage may cause several problems such as crippling the harbour function, environmental disruption, loss of life. Since the pilot plays an important role in the safe operation of the port, securing their safety is directly connected to the vessel's safety coming into port in Korea. Pilotage service is offered on request without distinction of day and night. And traveling by helicopter and boarding/disembarking using a pilot ladder from and to a pilot boat have a high risk of falling into the sea. So, pilots can fall into the sea while boarding/disembarking from ship which can lead to serious injury by cardiac arrest. A number of pilots have died or severely injured due to fall from the pilot ladder during embarkation and disembarkation up to now. Current safety measures at embarkation and disembarkation required by pilotage act and IMO resolutions could not prevent all the pilot related accidents. Therefore, to prevent pilot accident during boarding/disembarking from ship, it is necessary to include safety training requirement for new pilots under the requirements for licensing of pilotage act. It is also necessary to compel pilots to take necessary personal protective equipment when they use a pilot ladder. In addition, the placement of emergency kit on pilot boats and first-aid training are required in order to deal with emergency situation promptly.

• Journal of the Korea Society for Simulation
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• v.23 no.4
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• pp.75-83
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• 2014

Most warship combat systems inquire human operator to control several sensor and another equipments as well as decision-modeling. For this reason, many researches with multi-agent based M&S (Modeling and Simulation) have been increasingly conducted. However there cannot find any researches of M&S based analysis for anti-submarine warfare that requires a high level of mission complexity between multiple platforms. In this research, we have been developed various combat platform models such as warship, submarine and helicopter, etc. In order to apply the multi-agent-based M&S technology to the anti-submarine warfare i.e. a HVU (High Value Unit) escort mission scenario. Then we have successfully analyzed the measures of effectiveness according to the different tactics and different situations. In future, the defence engineer maybe employ our methodology and tools to analyze actual tactical problem by simply inserting actual data into our agent model.

• Composites Research
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• v.30 no.1
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• pp.52-58
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• 2017

This paper presents the optimum design methodology for composite wing structure which automatically calculates the safety margin using optimization framework integrating failure modes. Particularly, its framework is possible to optimize sizing procedure to prevent failure mode which has the greatest effect on reducing the sizing time of composite structure. The main failure mode was set as the first ply failure, buckling failure mode, and bolted joint stress field, and the margin was calculated to minimize the weight. The design variable is a laminate sequence database and the responses are strain, buckling, bolted joint stress field. The objective function is the mass of the wing structure. The results of buckling analysis were compared using the finite element model to verify the robustness and reliability of Composite Optimizer.

• Journal of Advanced Navigation Technology
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• v.22 no.3
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• pp.179-188
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• 2018

In developing avionics systems, safety analysis and evaluation specified in SAE ARP4761 (Methods and Guidelines for Civil Aviation System and Equipment Safety Assessment Process) are carried out to prevent air accidents. Safety analysis requires knowledge of the abnormal state of the system, not its normal state, and its interrelationships with other standards. Therefore, a tool that automatically outputs data which proves compliance with safety certification standards is required. In this study,In this study, Schematized the safety analysis procedure of the specification and studied the method of applying the safety analysis CAD tools to individual procedure. As an example study, ARP4761 analysis was performed on the wheel brake system (WBS) of the ARP4761 appendix.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.38 no.12
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• pp.1162-1169
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• 2010

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.

• Journal of the Korean Institute of Landscape Architecture
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• v.35 no.4
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• pp.57-70
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• 2007

As a basic element of Jeju landscape, Oreum offers a beautiful and aesthetic view. Considering topographical and geological research achievements, however, an effort to discover implicit value in terms of landscape characteristics and value has been ignored. This paper has investigated the characteristics and value of landscape by Oreum focusing on Jeju landscape characteristics and eco-touristic value and discussed a scheme to maximize the values. Under a theme of 'Sustainable Development' of the RIO Declaration, tour industry has recently changed its focus from eco-tourism to gee-tourism. Fortunately, Jeju Oreum has very distinctive and unique landscape with depressed crater at a crest. Nevertheless, it's very difficult to see a true aspect of Oreum from the street or over the car window. Therefore, it's urgent to begin a research on how to make advantage of and preserve Oreum landscape in order to maximize its landscape values and improve its potential as a tourist attraction. Through diverse programs such as sky leisure sports(ex: light airplane and helicopter riding, paragliding), sky watching, and mountain hiking, in particular, a possibility that Oreum can succeed as LBD(Learning by Doing)-based tour program with volcanic features needs to be examined. Besides, it's also a good idea to develop Oreum tour program or Oreum Museum as an alternative plan. Above all, however, it's most urgent to protect the existing Oreum and restore ecological and landscape beauty of Oreum through proper land use.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.5
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• pp.1-9
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• 2003

Detailed flow of a shrouded tail rotor in hover is studied by using a compressible inviscid flow solver on unstructured meshes. The numerical method is based on a cell-centered finite-volume discretization and an implicit Gauss-Seidel time integration. Numerical simulation is made for a single blade attached to the center body and guide by the duct by imposing a periodic boundary condition between adjacent rotor blades. The results show that the performance of an isolated rotor without shroud compares well with experiment. In case of a shrouded rotor, correction of the collective pitch angle is made such that the overall performance matches with experiment to account for the uncertainties of the experimental model configuration. Details of the flow field compare well with the experiment confirming the validity of the present method.