• Proceedings of the Korean Society for Agricultural Machinery Conference
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• 2017.04a
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• pp.153-153
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• 2017

본 연구에서는 농작업지내 모서리 점을 이용하여 자율주행 트랙터의 경로점을 생성하는 알고리즘을 개발하였다. 작업지는 직사각형의 형태에서 거리가 긴 방향으로 직선주행 경로로 하고, 직선경로의 수는 작업폭에 의해 결정되며 홀수 또는 짝수 개일 수 있다. 또한 TM좌표계에서 직선주행 경로의 기울기는 양수 또는 음수 일 수 있으며, 선회시 전체적으로 좌회전 또는 우회전하는 경우로 구분하여, 즉 총 8가지의 경우에 대하여 조건이 주어지면 경로점을 구할 수 있도록 프로그램하였다. 선회를 위한 곡선경로 생성에는 트랙터의 최소 회전반경 데이터를 사용하였으며, 이때 새로 진입할 다음 경로가 충분히 떨어져 있는 경우에는 선회 구간에서도 직선 경로 구간이 생길 수 있음을 고려하였다. 한 주기의 경로점은 직선 경로 구간의 시작점과 끝점, 선회 구간의 시작점과 끝점, 다음 직선경로로 진입을 위해 선회하기 직전까지의 직선 구간에 대한 시작점과 끝점 등 6가지의 경우로 구분할 수 있다. 이때 어떤 끝점 경로점은 다음 조작 구간의 시작점 경로점이 되므로 최종적인 경로점 데이터는 4개가 된다. 여기서, 첫 번째 경로점 생성에서는 직선구간 진입을 위한 선회구간의 시작점과 끝점은 제외하였으며, 작업지로 진입할 수 있는 입구와 출구는 동일한 것으로 가정하여, 작업이 완료되는 지점에서 선회하여 다시 출발점으로 돌아올 수 있도록 추가 구성하였다. 실제 상황에서는 직선주행 경로의 수가 정수가 되지 않을 수 있으며, 이때는 작업 구간이 약간씩 오버랩되도록 작업폭을 조정하여 경로의 수가 항상 정수가 되도록 하였다. 알고리즘 평가에 사용된 작업 패턴은 관행적인 방법으로서 작업 포장을 반으로 나누어 8자형 패턴을 이용하였다.

• Journal of the Korean Society of Propulsion Engineers
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• v.18 no.4
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• pp.33-42
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• 2014

Flame behaviors and interaction between pilot and main flames in a dual swirl combustor were investigated experimentally and numerically. Under the condition of fixed swirl angle of $45^{\circ}$ for main flame, the swirl angle of pilot flame, total heat release rate and equivalence ratio of main flame were used as major parameters. As a result, detailed flame stability diagram of dual swirl combustor was identified in terms of 5 flame modes with the changes in total heat release rate and equivalence ratio of main flame. It was found that the swirl angle of pilot flame plays the most important role in the changes in flame location and overall flow structure inside the combustor, and thus leads to the significant change in the interaction between pilot and main flame.

• Journal of the Korean Society of Hazard Mitigation
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• v.7 no.3
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• pp.59-67
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• 2007

For the time being, HMA test specimen were prepared by Marshall Compaction Method for hot mix asphalt design and evaluated the mechanical properties of HMA at the specified air voids. Gyratory Compaction can simulate the field compaction process and measure the degree of compaction just after field compaction in laboratory. Superpave mix design with Gyratory compactor has been used for characterization of performance. The curve of gyratory compaction can be used to evaluate the permanent deformation potential of hot mix asphalt. In this paper, couple of indices for hot mix asphalt have been showed for hot mix asphalt in Korea. The major properties from gyratory compaction curve are compaction energy index and traffic compaction index. The specific guide line for the potential of hot mix asphalt has been proposed.

• Journal of Navigation and Port Research
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• v.45 no.6
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• pp.298-305
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• 2021

Identifying the effect of turning characteristics on collision avoidance for Maritime Autonomous Surface Ships (MASS) can provide a key to avoid the collision of MASS. The purpose of this study was to derive a method to identify the effect of turning characteristics, which can be changed by various rudder angles and the ship's speed, on collision avoidance. The turning circle was observed using a mathematical model of a 161-meter-long ship, and it was analyzed that the turning circle had an effect on collision avoidance through numerical simulations of collision avoidance for four collision situations of two ships. The evaluation results using the two variables, the minimum relative distance between two ships and the minimum time at the minimum relative distance, demonstrated that the rudder angle has a major influence on the change of the minimum relative distance, and the ship's speed has a major influence on the change of the minimum time. The evaluation method proposed in this study was expected to be applicable to collision avoidance as a measures in remote control of MASS.

• Journal of Advanced Navigation Technology
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• v.28 no.3
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• pp.272-277
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• 2024

In most countries, instrument flight procedures are designed by applying one of the following standards: the International Aviation Organization's DOC 8168, Air Navigation Services and Operation Procedures (PANS-OPS), or the US Federal Aviation Administration's TERPS, Terminal Procedures. In particular, the circling approach procedure has many differences between the two standards, and the US terminal procedure (TERPS) has become more complicated since 2013 by applying expanded standards depending on altitude. The circling approach procedures are more risky than straight-in approach procedures because it involves maneuvering the aircraft close to the ground at low energy for landing. In order to accurately understand these differences, this study provides to distinguish by what criteria the circling approach procedure is designed according to individual domestic airports in Korea, to calculate the radius for the range of circling approach areas that guarantee minimum obstacle avoidance during circling approach maneuvers, and to present methods for performing safe circling approach procedures.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.25 no.2
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• pp.70-74
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• 1989

This paper, described on the maneuverabilities of M.S. Cheju 402, the stern trawler (159 G.T.), training ship of Cheju National University which carried out the turning circle tests at helm angle 35$^{\circ}$ and 10$^{\circ}$, 20$^{\circ}$, 30$^{\circ}$Ztests of her. The results obtained were as follows; 1. The advances of the starboard and port turning circles were 79.1m, about 2.6 times of the length of the ship, and 81.4m, about 2.7 times of it, respectively. 2. The rates of speed reduction were about 0.49 together, and mean values of turning angular velocity of her at helm angle 35$^{\circ}$ into the starboard and port sides were 4.3$^{\circ}$/sec and 4$^{\circ}$/sec during the turning movement. 3. Overshoot angles of starboard side werelarger than those of port side at all Z tests, and mean values of them of the starboard and port sides at 10$^{\circ}$, 20$^{\circ}$, 30$^{\circ}$Z tests were 110.5$^{\circ}$ 20.5$^{\circ}$, 28.5$^{\circ}$ respectively. 4. The maneuvering indices K and T of experimental ship at 10$^{\circ}$, 20$^{\circ}$, 30$^{\circ}$, Z tests were 0.755 and 3.468, 0.566, and 1.621, and 0.481 and 1.547 respectively. Consequently, the experimental ship showed that her turning ability was more in effective as the helm angle was becomed larger and her obeying ability was more effective as it was becomed larger.

• Journal of the Korea Academia-Industrial cooperation Society
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• v.19 no.4
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• pp.571-577
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• 2018

A gyratory compactor was developed to reflect the field compaction roller, which is commonly used in road construction. Unlike the compaction of the proctor using a conventional impact load, the gyratory compactor simulated the field roller compaction characteristics using the compressive force by the roller weight and the shear force through the rotation of a roller. The purpose of this study was to evaluate the shear stress and density change characteristics during compaction, which are difficult to obtain in the existing compaction process of the proctor, and to utilize it as a basic data for road design. The compaction characteristics of sand and subgrade soils were also analyzed and evaluated using the gyratory compactor. The compaction characteristics obtained using the gyratory compaction are basically the number of gyrations, height of the specimen, compaction density, void ratio, degree of saturation, and shear stress. As the number of gyrations increased, the height of the specimen decreased, the compaction density increased, the void ratio decreased, the degree of saturation increased, and the shear stress tended to increase. The shear stress of the compacted specimens started at 200 kPa in the initial stage of compaction and increased to approximately 330 to 350 kPa at 50 gyrations. The compaction density, degree of saturation and shear stress tended to increase with increasing water content in the same specimens. Compaction using turning compaction has the advantage of measuring the physical properties required for road design, such as density and shear stress, so that more engineering road design will be possible if it is reflected in road design.

• Journal of Power System Engineering
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• v.11 no.4
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• pp.18-25
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• 2007

제 2세대 직접분사식 가솔린 기관에서 6공 연료분사기의 연료분무특성을 관찰하였다. 실험에 사용한 직접분사식 가솔린 기관은 2개의 흡입밸브와 2개의 배기밸브를 갖는 텀블형 Spray Guided 연소실과 Quartz로 제작된 실린더 라이너와 실린더 헤드 창으로 구성되어 있다. 선회유동을 유도하기 위하여 흡입매니폴드에 선회유동 제어밸브를 부착하였다. 2차원 Mie 스캐터링 기법을 이용하여 연료분사시기, 연료분사압력과 실린더 내 유동 및 냉각수 온도가 연료분무에 미치는 영향을 관찰하였다. 실험결과로는 흡기과정동안 흡기 선회유동은 분사된 연료의 공간적 분포에 크게 작용하였고, 압축과정동안에는 텀블 및 선회유동의 영향이 흡기과정에 비해 크지 않음을 확인하였다. 또한 성층연소를 위해서 압축과정에서 연료를 분사하는 경우 고압의 연료분사압은 분무도달거리의 성장을 촉진시키나 상승하는 피스톤과 이로 인한 실린더 압력의 상승으로 분무도달거리의 성장이 억제됨을 확인할 수 있었다.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2007.04a
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• pp.117-120
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• 2007

This study investigated the spray modeling of the pressure-swirl atomizer installed in liquid rocket engine and the effect of drop distribution function especially. The $X^2$, originally implemented to KIVA, Rosin-Rammler and modified Rosin-Rammler distribution functions were investigated theoretically and compared to each other. Also, they were applied to pressure-swirl atomizer similar to the injector installed in liquid rocket engine to evaluate the feasibility for LRE injector. Among the distribution functions, original Rosin-Rammler distribution function was the most compatible with predicting the spray characteristics of pressure-swirl atomizer installed in liquid rocket engine.

• Journal of the Korea Society for Simulation
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• v.19 no.3
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• pp.17-25
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• 2010

It is necessary for the ship dynamic models to realize ship dynamics and to achieve the real-time analysis in the manoeuvring simulation. Generally, simple dynamic models, such as 1st-order differential equation models of turning angle, turning rate, and forward speed, are used in the manoeuvring simulation for multiple ships. Ship dynamic modeling and parameter estimation methods based on its turning test results are proposed in this paper. Parameter estimation methods for the constant speed model and the speed-changing model are mathematically developed and verified by comparing with turning test results of a real ship.