• Proceedings of the Korea Information Processing Society Conference
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• 2017.11a
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• pp.961-964
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• 2017

드론의 대중화에 따른 사고위험의 증가로 안전한 조종 방법에 대한 연구의 필요성이 대두되었다. 따라서 조종자의 조종능력에 구애받지 않는 자율비행제어기술이 필요하게 되었고, 이를 보다 안정적으로 구현하기 위하여 자율주행 소프트웨어 플랫폼으로 주목받고 있는 Robot Operating System(ROS)를 사용하였다. ROS를 기반으로 Laser Range Finder(LRF)와 Particle Filter를 사용하여 자율적으로 객체추적이 가능하며 지능적으로 장애물을 회피하여 비행 할 수 있는 안정적인 자율비행제어시스템을 구현하고자 한다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2019.05a
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• pp.185-188
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• 2019

In this paper, the towing stability of the LNG bunker barge is estimated. Currently, LNG bunkering barge is being developed as an infrastructure for the bunkering of LNG (Liquefied Natural Gas), an eco-friendly energy source. Since the LNG bunker barge are in the form of towed ship connected to the tow line, the towing stability of the LNG bunker barge is very important for the safety of not only the LNG bunker barge but also the surrounding sailing vessels. The numerical code for towing simulation was developed to estimate the towing stability of the LNG bunker barge at the initial design stage. The MMG(Manoeuvring Mathematical Group) model was applied to the equations of motion and the empirical formula was applied to the maneuvering coefficients so that they could be used in the initial design stage. To validity of the developed numerical code, it was compared with published calculation and model test results. Towing simulations were carried out according to with and without stern skeg of the LNG bunker barge using the developed numerical code. Through the results of the simulations, the appropriateness of the stern skeg area designed was confirmed.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.44 no.4
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• pp.324-332
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• 2016

In this paper, the terminal homing loop with a IIR-type strapdown seeker and a roll rate gyroscope is proposed. Basically, the proposed homing loop is based on the look-angle-control guidance. Since the range of the seeker is strictly limited, the missile is delivered to a point to lock the target on the seeker via non-guided flight during the midcourse guidance. The non-standard firing table is developed to compensate the wind and the target movement. To secure the delay margin is very important to prevent the instability of the homing loop when the time delay of the seeker is included. To validate the proposed homing loop, the 6-DOF nonlinear simulation is performed, and the Monte-Carlo simulation is also done for checking the robustness for the various kinds of uncertainty.

• Journal of Advanced Navigation Technology
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• v.9 no.2
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• pp.185-192
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• 2005

The aim of this paper is to analyze handling qualities of tiltrotor aircraft(TR-S4) in helicopter flight mode including hovering and forward flight. Analysis of handling qualities is composed of aircraft response to control inputs that effect on stability and controllability. In short term response analysis, bandwidth is the critical parameter for small amplitude motions since it relates to the ability of a pilot to crisply start and stop maneuver. The handling qualities of TR-S4 in helicopter mode are analyzed with a SAS and an attitude controller and are satisfied level 1 in almost criteria with simulation of TR-S4 6-DOF nonlinear model.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.34 no.6
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• pp.83-91
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• 2006

An advanced method of Relaxed Static Stability (RSS) is utilized for improving the aerodynamic performance of modern version supersonic jet fighter aircraft. The flight control system utilizes RSS criteria in longitudinal axis to achieve performance enhancements and improve stability. The flight control law of T-50 advanced trainer employs RSS concept in order to improve the aerodynamic performance and guarantee aircraft stability. The longitudinal center of gravity(X-c.g) varies as a function of external stores, fuel state and gear position. Shifts in X-c.g relate directly to longitudinal static margin in aircraft stability. This paper deals the maximum aft X-c.g for critical aircraft loadings and checks static margin limits using sensitivity such as damping, natural frequency, gain and phase margin. And nonlinear analysis was conducted for such as short period input. And also, this paper shows the T-50 aircraft stability based on the result of high angle of attack flight such as upright and inverted departure.

• Proceedings of the KIEE Conference
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• 2007.07a
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• pp.463-464
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• 2007

본 논문은 경제성 및 안정성을 유지하는 최적의 전압유지범위 설정을 위해 다양한 목적함수를 최적조류계산에 이용하였다. 경제성을 위해 융통전력 최대화와 유효전력 손실최소화를 목적함수로 하였고 안정성을 위해 무효전력예비력 최대화를 목적함수로 하였다. 또한 경제성과 안정성을 모두 반영하기 위해 다목적 함수를 구성하였다. 최적화기법을 실계통에 적용하였을 때 목적함수를 얼마나 잘 만족시킬 수 있는지 각종 지표를 통해 살펴보았다. 그리고 모니터링 모선의 전압 변동 추이를 살펴보고 이를 통해 경제성 및 안정성을 유지하는 최적의 전압유지 범위설정을 하는데 활용할 수 있도록 하였다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.43 no.9
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• pp.781-786
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• 2015

An aeroelastic stability can be degraded due to an aeroelastic modeling error and a structural uncertainty. Therefore it is necessary to predict the aeroelastic stability boundary considering an aeroelastic modeling error and a structural uncertainty. Robust aeroelastic analysis was proposed to predict the aeroelastic stability boundary considering these error and uncertainty. In the present study, the robust aeroelastic modeling and analysis were performed by using the ${\mu}$ analysis technique and the aeroelastic model of the control fin with modal approach and MSA. The computer program for the robust aeroelastic analysis was developed and verified by comparing its results with those of conventional aeroelastic analysis methods.

• Proceedings of KOSOMES biannual meeting
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• 2003.05a
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• pp.105-110
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• 2003

현대의 선박운항에 있어서 선내 노동의 경감과 운항의 안정성 및 경제성 확보를 위하여 선박 자동차 및 원격 조종화가 이루어지고 있다. 또한, 선박조종 및 작업제어를 위하여 컴퓨터를 이용한 통합제어 시스템에 관한 연구도 활발하게 진행되고 있다. 그러나 소형선박 및 어선과 같은 환경에서의 지능형 시스템에 관한 연구는 많이 부족한 실정이다. 본 논문에서는 지능형 선박을 구현하기 위한 기반 연구로서 선박 운항자의 원격지시로 선박의 조타기를 제어하는 지능형 조타제어시스템을 구축하여 실용화를 위한 방안을 모색하였다. 구체적인 연구결과로는 지능형 학습 기법을 바탕으로 하는 퍼지 조타수 조작 모델을 구축하여 조타제어 시스템을 구현하였고. 모형선박(Miniature Ship)의 조타 시스템을 PC 상에서 원격으로 제어하기 위한 시뮬레이션 시스템을 구축하여 그 유효성을 확인하였다.

• Journal of Navigation and Port Research
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• v.43 no.3
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• pp.143-152
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• 2019

In this paper, the towing stability of the LNG bunker barge was estimated. Currently, LNG bunkering barge is being developed for the bunkering of LNG (Liquefied Natural Gas), an eco-friendly energy source. Since the LNG bunkering barge assumes the form of a towed ship connected to the tow line, the towing stability of the LNG bunker barge is crucial f not only for the safety of the LNG bunker barge but also the neighboring sailing vessels. In the initial stages, a numerical code for towing simulation was developed to estimate the towing stability of the LNG bunkering barge. The MMG (Maneuvering Mathematical modeling Group) model was applied to the equations of motion while the empirical formula was applied to the maneuvering coefficients for use in the initial design stage. To validate the developed numerical code, it was compared with published calculation and model test results. Towing simulations were done based on the changing skeg area and the towing position of the LNG bunkering barge using the developed numerical codes. As a result, the suitability of the designed stern skeg area was confirmed.

• Journal of the Korean Society for Aviation and Aeronautics
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• v.1
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• pp.81-93
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• 1993

창공-91의 비행 시험의 목적은 성능 측정과 비행 특성의 확인이며 교통부의 기준은 주로 비행기의 운항에 따르는 안정성에 주안점을 두고 있다. 비행 시험으로 실속 속도와 이착륙 성능 그리고 상승 성능을 측정하여 비행 교범에 수록하였고, 안정성과 조종성의 적절함을 판단하였다. 창공-91 A2기의 비행 시험에 소요된 비행 시간은 81. 5 시간이다. (창공-91 $A_1$기 : 52.8시간)