• Journal of the Korean Society of Propulsion Engineers
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• v.20 no.4
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• pp.40-49
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• 2016

This study aims to confirm the characteristics of low swirl combustion at our low swirl model combustor. To do it, it is experimentally conducted by evaluating the flame shape, stability region and emissions according to the swirl angle. The most significant feature of low swirl combustion is a occurrence of lifted flame. Such lifted flames happen to combine exquisitely propagating feature of premixed flame with diverging flow. This feature of lifted flame was confirmed through a velocity flow field and visualized the flame in this model combustor. The visualized flame was classified according to the thermal power and equivalence ratio. The variation study in swirl angles showed that the lean flammable limit could be extended only by swirl angles. Also, as the swirl angle increased, it was confirmed that the NOx and CO emissions were decreased due to the mixing enhancement and shorter resident time.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2011.06a
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• pp.346-348
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• 2011

해상에서 예부선이 항행시 부선의 선회운동으로 인하여 예부선의 안전운항에 많은 어려움을 겪고 있다. 본 연구에서는 안전한 예항업무를 위하여 실무에서 많이 사용되고 있는 2가지 부선 모델을 대상으로 skeg의 설치 유무 및 skeg의 설치 위치에 의한 부선의 선회운동과 이에 따른 예인장력을 알아보기 위해 정수중에서의 수조실험을 실행하였다. 실험결과 예인삭의 선회각도는 skeg을 설치하지 않았을 때 가장 크게 나타났고, center skeg을 설치했을 때부터 작아지기 시작하여 side skeg을 설치했을 때 예인삭의 선회각도가 급격히 작아지는 것으로 파악되었으며, 이러한 특성은 선수형상에 따라 조금씩 다르게 나타나고 있음을 확인하였다. 또한 예인삭의 선회각도가 커질수록 예인장력이 커지는 것을 알 수 있었다. 따라서 부선에 skeg을 설치하여 운항하는 것이 부선의 선회 운동을 감소시켜 최종적으로 예인장력이 작아지게 하여 안전예항업무에 도움이 될 것으로 판단된다.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2018.11a
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• pp.7-8
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• 2018

파 중 선박 조종운동시험을 위하여 선박해양플랜트연구소 공학수조 내 자유항주시험 시스템을 구성하였다. 모형선 내에 제어계측 장비와 PC를 탑재하고 육상 관제 PC에서 원격 통제, 모니터링하며, 레이저 추적 방식으로 모형선 실시간 위치를 계측하였다. 준비된 시스템으로 KVLCC2 1/100 축소모형선의 규칙파 중 선회시험을 수행하였다. 파 중 선회성능은 초반의 전진거리, 전술직경, 정상선회 시의 궤적밀림 거리, 각도 등으로 지수화할 수 있다. 각 지수를 추출하여 분석하였고, 동일한 파장 조건에 대한 궤적밀림 경향은 유사함을 보였다.

• Journal of the Korean Society of Fisheries and Ocean Technology
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• v.37 no.4
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• pp.275-284
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• 2001

The for this study, turning circle tests and maneuvering indices were conducted to study and evaluate the maneuverabilities of the fishery training ship M.S. A-RA(G/T : 990tons). The results obtained were summarized as follows : 1. The advances of the starboard and port of the turning circle were measured based on the dumb card test method were 198m, 192m, the size of tactical diameters of them were 194m, 188m, respectively. 2. The advances at the starboard and port of the turning circles were measured according to the DGPS positioning obtained 196m, 194m, the size of tactical diameters of them were 194m, 190m, respectively. 3. The results were compared which came from the sizes of turning circle measured up with the dumb card test method during the trial test and from the size of turning circle measured according to the DGPS positioning. The advance of the turning circle measured at the time of the starboard turning according to the DGPS positioning was 1m longer than that of the trial test. And it was 21m shorter at the time of the port turning. 4. The rudder was steered at $35^{\circ}$ of rudder angle each starboard and port while the ship M.S. A-RA was advancing at full speed of 13 k't. The velocity of the ship was reduced to 7.8 k't at $180^{\circ}$ of turning angle and 6.0 k't at $360^{\circ}$ of turning angle and mean values of turning angular velocity of the port and starboard were $2.4^{\circ}$/sec and $2.3^{\circ}$/sec, respectively. 5. The Z test at each $10^{\circ}$, $20^{\circ}$, and $30^{\circ}$ of rudder angle was carried out to have the maneuvering indices K and T measured. K for the each rudder angle were 1.24, 1.45, and 1.65 while T for the each rudder angle were 0.33, 0.20, and 0.14. That is, K at the Z test at $30^{\circ}$ was greater than at the Z test of $10^{\circ}$ and $20^{\circ}$ while T at the $30^{\circ}$ Z test was less than at the Z test of $10^{\circ}$ and 20.

• Journal of Navigation and Port Research
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• v.36 no.1
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• pp.15-20
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• 2012

In order to investigate the maneuverability of tug-barge, sea trial tests such as speed, acceleration/deceleration, $10^{\circ}$ turning, $20^{\circ}$ turning, $10^{\circ}/10^{\circ}$ zigzag and $20^{\circ}/20^{\circ}$ zigzag were conducted with both tug and tug-barge. From the result of turning test, longer tactical diameter and lower rate of turn of tug-barge than those of tug are obtained. From the result of the zigzag test, bigger overshoot angle of tug-barge than that of tug is obtained. When they turned or changed a course, it showed that the barge turned inner side of the trajectory of tug. For the safe navigation, the helmsman of tug-barge should be aware of these maneuvering characteristics.

• Proceedings of the Korean Institute of Navigation and Port Research Conference
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• 2022.06a
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• pp.31-32
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• 2022

In Early vessels did not provide an exact equation for preventig the capsizing vessels. On land, many vehicle rollover prevention technologies using the steady-state Conrning Equations were developed, which showed better performance than the exiting method at sea. For better performance, It is proposed to improve safety mangement when turning vessel using the Ackerman geometic model-based Cornering Equations in this paper.

• Journal of Navigation and Port Research
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• v.27 no.5
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• pp.465-471
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• 2003

A coastwise chemical tanker sailing at full speed has capsized during turning in calm water. In the previous paper, we investigated the reasons of the accident by demonstrating the proper correction for the free surface effect of the liquid cargo and the bow-sinkage effect. In this paper, we also carry out model experiments of a transverse pressure under the seawater and an outward heel moment according to the heel angle and rudder angle, on the basis of radius of turning circle, ship's speed and drift angle of model ship occurring in turning. It is also shown that the flooding of seawater onto the deck occurring in turning generated a significant outward heel moment and increased the vertical distance between the center of gravity of the ship and the center of lateral water drag.

• Defense and Technology
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• no.7 s.257
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• pp.44-51
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• 2000

자세계는 상승, 하강 및 선회시 항공기 경사 상태를 각(Degree)으로 지시해 주는 장치이다. 이 자세정보들은 항공기의 선회시, 착륙시, 그리고 폭격하기 위해 표적에 접근할 때 매우 중요하다. 자세계는 기본적으로 항공기 기축에 수직인 회전축을 가진 3축 자이로 축에 대한 항공기 자세 즉, 피칭각 및 롤링각을 지시한다.

• Journal of the Korean Society of Propulsion Engineers
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• v.17 no.5
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• pp.70-79
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• 2013

The isothermal flow structure and mixing characteristics of a hybrid/dual swirl jet combustor for micro-gas turbine (MGT) were numerically investigated. Location of pilot burner, swirl angle and direction were varied as main parameters with the identical thermal load. As a result, the variations in location of pilot nozzle, swirl angle and direction resulted in the significant change in turbulent flow field near burner exit, in particular, center toroidal recirculation zone (CTRZ) as well as turbulent intensity, and thus the flame stability and emission performance might be significantly changed. With the comparison of experimental results, the case of swirl angle $45^{\circ}$ and co-swirl flow including optimum location of pilot burner were chosen in terms of the flame stability and emissions for the development of hybrid/dual swirl jet combustor.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.2
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• pp.63-71
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• 2003

This paper presents a robust slewing control of a flexible space structure based on sliding surface design. A sliding surface is designed for a single-axis rest-to-rest slewing in view of target angle, target angular velocity, and root monent of the flexible appendage. In comparison with the Lypunov control law, both controllers guarantee the stability and command tracking capabilities for nominal system. It is also shown that the designed control law provides further robustness to internal/external uncertainties. Extending the results of a single-axis maneuver, a sliding mode control law was sought for an arbitrary three-axis maneuver. Quaternion was used to determine the attitude of a space structure and sliding surfaces were designed for each axis, thereby a robust control law was derived considering the coupling effects between each rotational axis during the maneuver. Several numerical examples were demonstrated to show the effectiveness of the designed control law.