• Bulletin of the Society of Naval Architects of Korea
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• v.9 no.2
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• pp.78-83
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• 1972

• Proceedings of the Zoological Society Korea Conference
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• 2003.08a
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• pp.153.4-153
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• 2003

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.39 no.7
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• pp.634-642
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• 2011

A numerical analysis of steady/unsteady flow applying cavitation model and moving mesh method was carried out in order to analyze flow and response characteristics inside the pilot valve which controls the flight actuator system. The flow of the valve was assessed according to operation temperature and time. This research has found that valve characteristics became stable at above a specific temperature and the cavitation affected valve's performance. Internal pressure and response characteristics of the valve were analyzed and flow characteristics of steady and developed unsteady flow were confirmed to be matched each other.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.49 no.3
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• pp.221-231
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• 2021

In the present study, numerical simulation was performed to investigate aerodynamic characteristics of a ducted fan-upper/lower vanes system in hover. Sensitivity analysis of aerodynamic forces for a system component was conducted with the deflection angle of upper vanes varying but at the constant rotational speed and the collective pitch angle of fan blades. Then, vane control performance and duct airload distributions were analyzed in detail to physically understand operating mechanisms of individual vane and interference effect between duct and vanes. Finally, new control concept of operating upper vanes has been proposed to improve the control performance of the full configuration. It is found that the side force and rolling moment of upper vanes increase linearly with the variation of those deflection angle; however, the total side force is significantly small due to the reaction force acted on the duct. It is also found that upper vanes close to the duct contraction side have a key role in changing vane control forces. It is revealed that the duct suction pressure is induced by the interaction with the suction side of upper vanes, while duct pressure recovery by the interaction with the pressure side, leading to increase in duct asymmetric force. When four upper vanes are kept in situ at 0° deflection angle or removed, the total control performance was improved with duct asymmetric force reduced and the total magnitude of roll remarkably increasing up to 80%.

• Journal of the Korean Institute of Intelligent Systems
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• v.26 no.3
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• pp.218-225
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• 2016

It is important to select the personnel with ideal pilot aptitude considering dramatically advancing aircraft performance and complexity of military operations as a consequence to the highly developed science and technology. The opportunity cost lost from dropouts and human error being the first cause of aviation accidents are the realistic reasons for the significance of personnel selection based on their aptitude. This study analyses the ROKAF pilot aptitude test that was improved in 2004, using various classification models. This study discusses the significance of the selected variables along with the direction of ROKAF pilot aptitude test for its development in the future. The accuracy of the classification models was improved by taking into account differing personnel characteristics of individuals on the test.

• KSCE Journal of Civil and Environmental Engineering Research
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• v.33 no.4
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• pp.1683-1691
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• 2013

Concrete surface grinding is frequently used for flatness of concrete surface, concrete pavement rehabilitation, and adhesiveness in pavement construction. The procedure is, however, labor intensive and has a hazardous work condition. Also, the productivity and the quality of concrete surface grinding highly depend on the skills of worker. Thus, the development of remote controlled concrete surface grinding equipment is necessary to prevent the environmental pollution and to protect the workers from hazardous work condition. However, it is difficult to evaluate the grinded surface objectively in a remote controlled system. Also, The machine vision system developed in this study takes the images of grinded surface with the network camera for image processing. Then, by representing the quality test results to the integrated program of the remote control station, the quality control system is constructed. The machine vision algorithm means the image processing algorithm of grinded concrete surface and this paper presents the objective quality control standard of grinded concrete surface through the application of the suggested algorithm.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.41 no.5
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• pp.357-365
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• 2013

In this study, forces and moments were measured on a projectile which consisted of a missile configuration body(shell) and a head installed control fins. The shell and the head were separated each other and the shell was rotated by an electric motor. The head rotated reversely against the rotational direction of the shell. The rotational force on the head was obtained from a couple of fixed fins of which angular displacement were set to the rotational direction equally. The air velocity was 40m/s on the experiment and the Reynolds number based on the diameter of head was $1.3{\times}10^5$. The other couple of fins were used to control the position and direction of the projectile by changing the angular displacement. From this experiment, the variation of force and moment were measured on the rotating projectile, and the effective amplitude and frequency were obtained through the FFT analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.35 no.4
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• pp.295-301
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• 2007

The aeroelastic characteristics of a wing with control surface freeplay are investigated. The transonic small disturbance equation is used for unsteady aerodynamic forces in subsonic/transonic region. The fictitious mass method is introduced to apply a modal approach to nonlinear structural models. Nonlinear aeroelastic time responses are calculated by the coupled time integration method. Using these methods, an efficient aeroelastic analysis is achieved for aerodynamic and structural nonlinearities simultaneously. The effects of the aerodynamic nonlinearity, initial flap amplitude, and freeplay magnitude in aeroelastic characteristics are investigated in this study.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2010.10a
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• pp.134-136
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• 2010

예선은 일반적인 선박에 비해 협소한 선교를 가지고 있으며, 부선의 상태/상황 및 감시를 하기 위해 후방을 주시해야 한다. 이러한 예선의 특성을 시뮬레이션 시스템에 반영하기 위해서는 여러 고려사항이 있다. 협소한 선교를 가진다는 점은 현재 한국해양 연구원 해양시스템안전연구소가 보유하고 있는 CDS(Collimated Dome Simulator)의 조종실을 사용함으로써 반영할 수 있다. 하지만, 이 시스템은 전방에 대한 가시화만을 지원하며, 후방 가시화를 위해서는 360도 디스플레이 방식을 사용하는 것이 최적이다. 본 논문에서는 현재 보유 중인 CDS에 예부선 시뮬레이션 가시화의 특성을 반영할 수 있는 후방 가시화에 대한 개발 방안에 대해 다루고자 한다. 추가적인 장비를 조종실(선교)의 뒤쪽에 설치함으로써 CDS가 가지는 단점을 해결할 수 있을 것으로 예상된다.

• Proceedings of the KIEE Conference
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• 2007.10a
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• pp.217-218
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• 2007

최근 개발된 비선형 자동조종 제어기를 사용하면 비행 환경에 무관하게 BTT 미사일의 입출력 동특성이 일정한 선형 시스템의 형대로 표현될 수 있다. 본 논문에서는 이와 같은 특성을 바탕으로 BTT 미사일이 목표물의 취약 지점을 정밀하게 요격할 수 있도록 자동조종장치 동역학의 시간 지연 효과를 고려하여 표적 충돌각을 최소화하는 최적 종말 유도 법칙을 설계하였다. 제안된 최적 종말 유도 법칙은 극좌표 변환을 사용하지 않기 때문에 가제어성을 보장하며, 가속도 편향값을 사용하지 않기 때문에 기존의 유도 법칙에 비하여 미사일의 기동성을 향상시킬 수 있는 장점을 갖는다.