• 한국수자원학회논문집
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• 제51권1호
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• pp.35-48
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• 2018

수제는 일반적으로 하천에서의 흐름 방향과 유속을 제어하여 하안 또는 제방을 유수에 의한 침식작용으로부터 보호하기 위한 목적으로 설치될 뿐만 아니라 과거에는 운하를 위한 충분한 수심 확보 목적으로 이용되었다. 2000년대 이후 하천복원 및 자연하천 정비에 대한 관심이 커지면서, 수제 설치로 인해 발생되는 수제주변 국부적인 흐름제어와 다양한 하상조건이 수중서식처 기능을 줄 수 있어 환경적 주요 수공구조물로 제시되고 있다. 수제는 주로 여러 개의 군수제로 설치되는데 설치간격에 따라 주수로에서 변화되는 흐름과 수제역내 흐름이 다양하게 발생하기 때문에 군수제 설계에 있어서 수제의 간격은 중요한 설계인자라 할 수 있다. 본 연구는 수제간격 및 설치각도에 따라 다양하게 변화되는 수제역내 재순환구간의 흐름현상을 검토하여 수제목적에 따른 적정 수제간격을 결정하는데 정보를 제공하고자 하였다. 특히 흐름분석은 수제역내 재순환영역에서 발생하는 와의 형성, 와 중심점의 위치 및 제방부 유속을 주로 분석하여 제방부의 안정성에 영향을 미치는 제방주변에서의 흐름특성을 검토하였다. 실험의 결과는 군수제 설치에 따른 수제역 내의 하상변화와 제방안정성 검토를 위한 중요한 기초자료가 될 것이다.

• Advances in aircraft and spacecraft science
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• 제3권4호
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• pp.399-425
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• 2016

The dynamical requirements are obtained for airplanes to travel on inclined circular trajectories. Formulas are provided for determining the load factor, the bank angle, the lift coefficient and the thrust or power required for the motion. The dynamical properties of the airplane are taken into account, for both, airplanes with internal combustion engines and propellers, and airplanes with jet engines. A procedure is presented for the construction of tables from which the flyability of trajectories at a given angle of inclination can be read, together with the corresponding minimum and maximum radii allowed. Sample calculations are shown for the Cessna 182, a Silver Fox like unmanned aerial vehicle, and a F-16 jet airplane.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 1994년도 Proceedings of the Korea Automatic Control Conference, 9th (KACC) ; Taejeon, Korea; 17-20 Oct. 1994
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• pp.653-658
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• 1994

This paper presents numerical analyses of the low speed yo-yo maneuver of an aircraft to determine controls of thrust, bank-angle and angle-of-attack in the subsonic region in terms of the optimal control theory. Minimum-time flight paths are numerically calculated to overtake an opponent aircraft flying in some steady-state level turnings under several assumptions: both of aircraft are point masses and maneuver in the 3-Dimensional space. Their weights are considered constant in the maneuver. As a result of the analyses, the effectiveness of the low speed yo-yo maneuver is shown.

• 한국군사과학기술학회지
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• 제15권1호
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• pp.101-110
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• 2012

The side jet effects between jet flow and free-stream on a missile body were investigated by experimentally and numerically for modeling aerodynamic coefficients in pitch plane. K-factors for normal force and pitching moment were introduced to estimate the side jet effects. The main parameters of the jet interaction phenomena were angle of attack, jet pressure ratio, Mach number and jet bank angle. The K-factors for normal force coefficient and pitching moment coefficients in pitch plane were analysed.

• 무역학회지
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• 제41권2호
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• pp.231-250
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• 2016

본 연구는 선하증권이 발행된 국제무역거래에서 화물이 서류보다 일찍 도착하여 원본 선하증권 없이 화물을 인도 받기 위해 국제적으로 통용되고 있는 상관행인 수입화물선취보증서를 기존 연구와 다른 관점에서 고찰하고자 한다. 혼합결제방식 하에서 발행된 수입화물선취보증서의 보증책임 범위를 판례를 통해 분석하고 국제적인 상관행으로 자리잡고 있는 수입화물선취보증서의 원활한 활용을 위한 다음 두 개의 대안을 제언한다. 첫째, 혼합결제방식을 이용한 경우, 수출업자는 상업송장을 발행함에 있어 결제방식의 결제대금을 각각 분리해서 발급해야 수입화물선취보증서의 보증책임 한도에 대한 명확한 의사표시가 이루어질 수 있을 것이다. 둘째, 수입화물선취보증서의 발행은행은 보증서 발행의 보증책임 범위를 명확히 하기 위해 기존 양식에 책임한도를 제한한다는 취지의 문구를 추가한 새로운 수입화물선취보증서 양식의 구축이 필요하다.

• 제어로봇시스템학회논문지
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• 제10권2호
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• pp.112-124
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• 2004

A neural network based adaptive reconfigurable flight controller is presented for a class of discrete-time nonlinear flight systems in the presence of variations of aerodynamic coefficients and control effectiveness decrease caused by control surface damage. The proposed adaptive nonlinear controller is developed making use of the backstepping technique for the angle of attack, sideslip angle, and bank angle command following without two time separation assumption. Feedforward multilayer neural networks are implemented to guarantee reconfigurability for control surface damage as well as robustness to the aerodynamic uncertainties. The main feature of the proposed controller is that the adaptive controller is developed under the assumption that all of the nonlinear functions of the discrete-time flight system are not known accurately, whereas most previous works on flight system applications even in continuous time assume that only the nonlinear functions of fast dynamics are unknown. Neural networks learn through the recursive weight update rules that are derived from the discrete-time version of Lyapunov control theory. The boundness of the error states and neural networks weight estimation errors is also investigated by the discrete-time Lyapunov derivatives analysis. To show the effectiveness of the proposed control law, the approach is i]lustrated by applying to the nonlinear dynamic model of the high performance aircraft.

• 제어로봇시스템학회논문지
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• 제9권4호
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• pp.329-339
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• 2003

A neural network based adaptive controller design method is proposed for reconfigurable flight control systems in the presence of variations in aerodynamic coefficients or control effectiveness decrease caused by control surface damage. The neural network based adaptive nonlinear controller is developed by making use of the backstepping technique for command following of the angle of attack, sideslip angle, and bank angle. On-line teaming neural networks are implemented to guarantee reconfigurability and robustness to the uncertainties caused by aerodynamic coefficients variations. The main feature of the proposed controller is that the adaptive controller is designed with assumption that not any of the nonlinear functions of the system is known accurately, whereas most of the previous works assume that only some of the nonlinear functions are unknown. Neural networks loam through the weight update rules that are derived from the Lyapunov control theory. The closed-loop stability of the error states is also investigated according to the Lyapunov theory. A nonlinear dynamic model of an F-16 aircraft is used to demonstrate the effectiveness of the proposed control law.

• Journal of Welding and Joining
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• 제34권1호
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• pp.54-58
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• 2016

In this research paper, suggest method of generate same bead as an actual measurement data in virtual welding conditions, exploit morphology information of the bead that acquired through robot welding. It has many multiple risk factors to Beginners welding training, by we make possible to train welding in virtual reality, we can reduce welding training risk and welding material to exploit bead visualization algorithm that we suggest so it will be expected to achieve educational, environmental and economical effect. The proposed method is acquire data to each case performing robot welding by set the voltage, current, working angle, process angle, speed and arc length of welding condition value. As Welding condition value is most important thing in decide bead form, we would selected one of baseline each item and then acquired metal followed another factors change. Welding type is FCAW, SMAW and TIG. When welding trainee perform the training, it's difficult to save all of changed information into database likewise working angle, process angle, speed and arc length. So not saving data into database are applying the method to infer the form of bead using a neural network algorithm. The way of bead's visualization is applying the spline algorithm. To accurately represent Morphological information of the bead, requires much of morphological information, so it can occur problem to save into database that is why we using the spline algorithm. By applying the spline algorithm, it can make simplified data and generate accurate bead shape. Through the research paper, the shape of bead generated by the virtual reality was able to improve the accuracy when compared using the form of bead generated by the robot welding to using the morphological information of the bead generated through the robot welding. By express the accurate shape of bead and so can reduce the difference of the actual welding training and virtual welding, it was confirmed that it can be performed safety and high effective virtual welding education.

• Journal of Biosystems Engineering
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• 제26권1호
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• pp.29-38
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• 2001

A navigation system was developed for autonomous guidance of a combine. It consisted of a DGPS, a machine vision system, a gyro sensor and an ultrasonic sensor. For an autonomous operation of the combine, target points were determined at first. Secondly, heading angle and offset were calculated by comparing current positions obtained from the DGPS with the target points. Thirdly, the fuzzy controller decided steering angle by the fuzzy inference that took 3 inputs of heading angle, offset and distance to the bank around the rice field. Finally, the hydraulic system was actuated for the combine steering. In the case of the misbehavior of the DGPS, the machine vision system found the desired travel path. In this way, the combine traveled straight paths to the traget point and then turned to the next target point. The gyro sensor was used to check the turning angle. The autonomous combine traveled within 31.11cm deviation(RMS) on the straight paths and harvested up to 96% of the whole rice field. The field experiments proved a possibility of autonomous harvesting. Improvement of the DGPS accuracy should be studied further by compensation variations of combines attitude due to unevenness of the rice field.

• 한국추진공학회지
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• 제18권3호
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• pp.8-16
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• 2014

본 논문은 옆미끄럼각에 따른 초음속 흡입구 버즈마진의 영향도에 대해 분석하였다. 버즈마진은 비행체 종축면에서 획득한 측정 물리량 기반으로 제어 명령을 산출하는 제어기에 의해 안정화 된다고 가정하였다. 해당 분석은 3차원 CFD를 통해 획득한 결과를 기반으로 수행되었으며, 3차원 CFD 해석 데이터는 종축면의 센서 측정 물리량을 모사하기 위해 사용되었다. 종축면 측정치 기반의 제어시스템에서는 기대하지 않은 횡방향 유동 섭동이 총 받음각의 증가의 결과로 나타나며, 이는 엔진 흡입구 성능의 감소를 의미한다. 결과적으로, 제어 안정성 또한 줄어들게 되어 보다 큰 제어 마진이 요구됨을 확인할 수 있었다.