• 한국항공운항학회:학술대회논문집
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• 2006.05a
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• pp.121-124
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• 2006

• Proceedings of the Korean Institute of Intelligent Systems Conference
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• 1998.06a
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• pp.438-442
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• 1998

The helicopter system is non-linear and complex. Futhermore, because of absence of an accurate mathematical model, it is difficult accurately to control its attitude. But we can control the non-modeled system with the uncertainty and unstructure using the fuzzy control algorithm. Therefore, we apply optimized fuzzy controllers for the control of its elevation angle and azimuth one using expert's intuitions and knowledges. The simulation and experimental results of the hellicopter simulator CE150 with MATLAB shall be introduced.

• 한국전산유체공학회:학술대회논문집
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• 2008.03b
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• pp.358-361
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• 2008

A study is made of thermal plume flow model for the development of helicopter simulator over the forest fire. For numerical analysis, the Boussinesq fluid approximation and line fire model, which is assumed by the shape of forest fire spreading, are adopted. Comparing 3-D full numerical solutions with 2-D similarity solution, it has been built a new model that is capable of temperature prediction along the symmetric vertical axis in both cases of laminar and turbulent flows.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.9
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• pp.796-805
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• 2016

As a part of the first stage in the helicopter flight simulator development, this study numerically evaluates handling qualities of the dynamics model. The flight dynamics model was generated using public information for AS365 N2, the target aircraft of the simulator. The flight simulator is under development as a pilot training and research tool for firefighting missions. The assessment of the model intends to validate general characteristics and suitability before the model is enhanced with flight test data. The evaluation is based on the ADS-33E-PRF(Aeroautical Design Standard Performance Specification Handling Qualities Requirement) criteria, with consideration of category of the aircraft, missions, and environment. The numerical operations follow required or recommended procedures of flight test for compliance demonstration. Evaluation results are evaluated according to the rating specified in maneuverability ADS-33E-PRF. Results have identified to provide a satisfactory platform for flight dynamic model in the general helicopter simulator generated based on the RotorLibFDM, and can be used as a base for basic training and research.

• Journal of Aerospace System Engineering
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• v.14 no.2
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• pp.12-19
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• 2020

In Korea, the regulation is MOLIT Notice 2018-290, Guidance for Approval of Synthetic Flight Trainer as Flight Simulator and Flight Training Device. The FAA (Federal Aviation Administration) categorizes FSTD (Flight Simulation Training Device) into FFS (Full Flight Simulator) and FTD (Flight Training Device), according to its level. Additional categories for regulation are airplane and helicopter, depending on the type of aircraft. In this study, the objective tests for the handling quality of the FAA and Korean regulations were compared and analyzed. In QPS (Qualification Performance Standard), related test titles, flight conditions, and tolerance limits were analyzed for the handling quality. Based on this study, recommendations on amendments to the regulation was presented.

• 한국항공운항학회:학술대회논문집
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• 2007.12a
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• pp.1-4
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• 2007

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.4
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• pp.406-412
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• 2009

Flight simulation model for helicopter simulator is one of the most important models which affect flight performance and handling quality. It is typical to develop the model based on the raw data and models from the helicopter designers/manufacturers. The approaches in this study were to develop the basic model based on the available resources regarding helicopter operation/maintenance and to tune and validate it based on the flight test results. The basic model was developed with maintenance manuals, flight manuals, analyses, measurements, papers and so on considering that KA-32T data could not be obtained from the manufacturer. The flight test for KA-32T was performed and the reference data for the simulation validation tests were acquired. The flight simulation model was validated to have the fidelity compatible with level C of FAA AC120-63 after comparison and tuning with flight test results.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.8
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• pp.731-738
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• 2015

The rapid prototyping process and development tool which enable the control law evaluation efficiently are needed to minimize the development cycle, cost and risk of aircraft flight control system. This paper describes a development process that integrates the designed control law into HETLAS to evaluate simulation effectively using nonlinear mathematical models. The desktop engineering simulator was developed using HETLAS for the piloted simulation evaluation of a various control modes and the procedure was developed, which quickly integrates the HETLAS into HQS(Handling Quality Simulator) and HILS(Hardware In the Loop Simulation) environments. This paper presents a rapid prototyping process using HETLAS that significantly shortens the integration process of the control law into the nonlinear math model, HETLAS, and allows the control law designs to be quickly tested in the piloted simulation and HILS environments.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.25 no.3
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• pp.108-114
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• 2017

A flight simulator is an instrument which lets pilots attain proficiency of handling various emergency situations, and the sense of flying. In this thesis, current status of domestic simulators will be stated, and after showing the problems with the present management of these simulators, comparisons of how and what kind of facilities they are managed around the globe will be made. After comparing and analyzing the difference in the way the simulators are ran, measures of improvement in domestically appropriate simulators and increase of operating facilities will be drawn.

• The Journal of Korean Institute of Communications and Information Sciences
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• v.39C no.11
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• pp.1088-1093
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• 2014

The structure of the fire control system(FCS) of a light armed helicopter and effective logistics support was taken into account in the proposed common weapon interface module(CWIM) for a distributed FCS. The pros and cons of a distributed FCS and a centralized FCS were analyzed, then a CWIM which can be applied to the weapon interface module of a distributed FCS was designed and fabricated. Integration tests between the proposed CWIM and a weapon simulator were conducted to ascertain whether or not the proposed CWIM could be applicable to a distributed FCS. We expect that the CWIM design approach method secured through this study will be helpful in mitigating cable work of the FCS which will be applied to a Light Armed Helicopter and controlling various weapons.