• 대한조선학회논문집
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• 제58권3호
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• pp.198-205
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• 2021

In this paper, the effect of trim variation on the required power of 11,000TEU container ship was investigated under conditions considering the actual operation speed and draft. For each draft condition, the effective power (P_E) and delivered power (P_D) trends were investigated with changes in trim and ship speed. At this time, the displacement volume was fixed same as the value of the even trim condition and the both sinkage at the fore and after perpendicular are confirmed. The test ship speeds were determined by considering the operating speed. Both numerical and experimental methods were used to analyze the effects of trim variation. Numerical analysis results were used for evaluating the resistance performance, and the self-propulsion performance was estimated using experimental data obtained from model test.

• 한국해양공학회지
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• 제29권6호
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• pp.411-417
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• 2015

The shipping and shipbuilding industries have had business difficulties since the implementation of regulations on the CO₂ emissions from ships by IMO and the occurrence of the global financial crisis in 2008. Under this global recession, most shipping firms have started to operate their fleets at slow steaming rates with the goal of improving the profit ratio per transported unit. This study analyzed the resistance performance of a 6,800 TEU container ship corresponding to its trim variation with slow steaming, compared with that at its original design speed. Two different grid systems were used for the numerical calculation, one that considered the free surface allowing the capture of the dynamic trim and one that did not. This made it possible to clearly classify each resistance component to provide useful information to hull-form designers. In addition, a form factor assumption method using CFD was used for a reasonable effective power prediction in compliance with the 1978 ITTC performance prediction method. It was found that the total resistance of a 6,800 TEU container ship was reduced by 2.6% in the case of a 1-m trim at the bow at 18 kn.

• 수산해양교육연구
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• 제9권2호
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• pp.179-187
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• 1997

경상대학교 해양과학대학 실습선 경양호 기관의 회전수와 추진기의 핏치각을 전속(全速)(R.P.M. 680, P.A. $18^{\circ}$), 반속(半速)(R.P.M. 640, P.A. $16^{\circ}$), 미속(微速)(R.P.M. 580, P.A. $10^{\circ}$)의 상태로 하고, 이들 각각에 따른 시험선의 트림을 2.45m, 2.15m, 1.45m 선미 트림으로 조정하여 마일 포스트를 왕복하여 도플러 로그의 대지 속력과 실속력을 측정하여 비교 분석한 결과 도플러 로그 지시속력은 트림의 변화에 큰 영향을 받았으나 속력에는 그다지 큰 영향을 미치지 않음을 알 수 있었다. 한편 세 경우 모두 선의 트림이 2.15m 선미 트림 일때 속력 변화의 폭과 오차가 가장 적어 선체가 안정되고, 트림의 순간적 변화가 적으므로 최적의 상태라 할 수 있다. 그리고 미속 전진중 일때 속력 변화의 폭이 가장 크게 나타났는데 이것은 마일 포스트 사이를 통과 하는데 소요되는 시간이 전속, 반속 전진중 일때 보다 많이 소요되므로 그 간에 외력의 영향을 많이 받았기 때문이라 추정되었다. 특히 세 경우 모두 처음 마일 포스트를 통과한 후 약 30초 사이에는 도플러 로그의 지시속력이 저속임과 동시 속력 변화의 폭이 아주 크게 되었다가 그 후는 완만한 속력 변화를 보였는데 이러한 원인은 기관의 회전수와 핏치각을 변화시킨 후 최적의 상태가 되기 이전에 마일 포스트를 통과한 때문이라 생각된다.

• 산업경영시스템학회지
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• 제39권1호
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• pp.116-122
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• 2016

Recently, the production cycle in manufacturing process has been getting shorter and different types of product have been produced in the same process line. In this case, the control chart using coefficient of variation would be applicable to the process. The theory that random variables are located in the three times distance of the deviation from mean value is applicable to the control chart that monitor the process in the manufacturing line, when the data of process are changed by the type of normal distribution. It is possible to apply to the control chart of coefficient of variation too. ${\bar{x}}$, s estimates that taken in the coefficient of variation have just used all of the data, but the upper control limit, center line and lower control limit have been settled by the effect of abnormal values, so this control chart could be in trouble of detection ability of the assignable value. The purpose of this study was to present the robust control chart than coefficient of variation control chart in the normal process. To perform this research, the location parameter, ${\bar{x_{\alpha}}}$, $s_{\alpha}$ were used. The robust control chart was named Tim-CV control chart. The result of simulation were summarized as follows; First, P values, the probability to get away from control limit, in Trim-CV control chart were larger than CV control chart in the normal process. Second, ARL values, average run length, in Trim-CV control chart were smaller than CV control chart in the normal process. Particularly, the difference of performance of two control charts was so sure when the change of the process was getting to bigger. Therefore, the Trim-CV control chart proposed in this paper would be more efficient tool than CV control chart in small quantity batch production.

• 한국소음진동공학회논문집
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• 제16권12호
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• pp.1252-1261
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• 2006

This paper summarizes theoretical work on the multichannel decentralized feedback control of sound radiation from aircraft trim panels using piezoceramic actuators. The aircraft trim panels are generally honeycomb structures designed to meet the design requirement of low weight and high stiffness. They are resiliently-mounted to the fuselage for the passive reduction of noise transmission. It is motivated by the localization of reduction in vibration of single channel active trim panels. 12-channel decentralized feedback control systems are investigated in terms of the reduction of noise and vibration for three configurations of sensor actuator pairs. Local coupling of the closely-spaced sensor and actuator pairs was modeled using single degree of freedom systems. The multichannel control system is characterized using the state-space model. For the stability point of view, the relative stability or robustness is evaluated by comparing the real part of eigenvalues of the system matrix for the three configurations. The control performance is also evaluated and compared for the three configurations. It is found that the multichannel system can lead to the globalization of the reduction in vibration and radiated noise. It does not appear to yield a significant improvement in the vibration because of decreased gain margin. However, the reduction in the radiated noise is remarkably improved due to the variation of the vibration pattern with the actuation configurations.

• 해양환경안전학회지
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• 제27권4호
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• pp.538-549
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• 2021

본 연구에서는 Froude 수 1.0으로 운항하는 길이 약 10m 급 소형 고속선박의 에너지 효율 설계를 위해 선미부에 트림 탭을 부착하였고, 선저 면과의 각도에 따른 항주자세와 저항성능의 변화를 살펴보았다. 성능 해석은 CFD 해석을 통해 수행되었으며, 축척에 의한 영향을 보기 위해 모형선과 실선에 대해 각각 해석을 수행 후 두 결과로부터 예측된 실선의 성능을 비교하였다. 나선에 대한 해석 결과는 두 결과가 전반적으로 유사하였고, 트림 탭이 부착된 경우 선저 면과의 각도가 동일할 때 자세 변화량이 달라 전 저항의 차이로 이어졌지만 자세에 따른 저항 변화 경향은 유사하였다. 이로부터 축척 효과가 있더라도 저항 저감 경향으로부터 최적 항주자세를 찾을 수 있으나, 트림 탭에 의한 자세 변화와 실선 주위 유동의 특성을 알기 위해서는 실선에 대한 직접적인 해석이 필요함을 알 수 있다.

• 한국항공우주학회지
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• 제41권1호
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• pp.31-39
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• 2013

본 논문에서는 고정익항공기와 회전익 항공기의 장점을 결합시킨 신개념 복합형 무인항공기인 QTW(Quad Tilt Wing)의 종축 동특성을 연구한 결과를 기술하였다. 설계된 QTW 무인항공기는 Tandem Wing 형상을 가지며 각 주익의 끝단에는 프로펠러를 구동하는 모터를 장착하였다. 비행역학적 분석을 위해 모멘텀 이론을 이용해 추력을 계산하였으며, 틸트 각도에 따른 프로펠러의 Slip stream에 의한 양력과 항력을 고려한 비선형 모델링을 구축하였다. 또한 트림분석을 통해 설계된 비행체가 적절한 비행속도 대비 틸팅각을 가짐을 보여주었으며, 각 트림 점에서의 성분별 힘을 분석하였다. 각 비행 모드의 선형모델 고유치 분석하여 동적 특성을 분석하였으며 고정익모드로 전환됨에 따라 안정한 부분으로 극점이 이동함을 확인하였다.

• 한국항공우주학회지
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• 제44권11호
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• pp.989-996
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• 2016

본 연구는 비선형 응답모델과 실수기반의 혼합형 유전자 알고리즘을 적용하여 로터의 트?-발란스(RTB) 기법을 개발하는 데 목적이 있다. 트?-발란스 조절 파라미터의 변화에 따른 트림해석 결과를 이용하여 2차의 근사함수를 이용하는 비선형 응답모델을 개발하였다. 트?편차와 기체의 진동응답을 최소화하기 위해 균형추 무게, 트림 탭(Trim Tab) 및 피치링크 길이를 최적화하기 위한 비선형계획 문제를 정식화하였다. 정식화 결과는 수렴성 향상을 위해 군집최적화 기법을 실변수기반의 유전자 알고리즘에 통합한 혼합형 유전자 기법을 사용함으로써 효율적인 해석이 가능하였다. 비선형 모델을 이용한 본 연구의 방법을 선형모델의 결과와 비교하여 본 연구의 방법을 검증하였으며 비선형모델을 사용하는 경우 선형모델의 결과보다 향상된 응답특성을 계산할 수 있음을 밝혔다.

• 한국자동차공학회논문집
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• 제25권2호
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• pp.257-265
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• 2017

In this work, the effect of field-degradation of automotive polymeric interior parts on the squeak characteristics was studied for a number of used vehicles with various mileages and years of service. The purpose of this study was to characterize the squeak noise related with long-term degradation in service life. The characteristics of field-degraded polymeric samples are analyzed using Fourier transform infrared(FT-IR) spectroscopy and scanning electron microscopy(SEM). Complicated carbonyl spectra from FT-IR were deconvoluted into various carbonyls to trace field-degradation phenomenon. In addition, various mechanical tests, i.e. tensile test, hardness test as well as coefficient of friction test, were performed to analyze the variation in mechanical properties due to field-degradation. Squeak noise was measured and analyzed by frequency analysis. It was shown that the changes in the chemical structures of polymer due to field-degradation influenced the variation in mechanical properties, and squeak noise may worsen by increasing the squeak noise level in the wide frequency range. The results indicated that customer complaints regarding the squeak noise coming from used vehicles might be one of the important reliability issues because the increase in sound pressure level especially in the high frequency range could annoy drivers and passengers.

• 제어로봇시스템학회:학술대회논문집
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• 제어로봇시스템학회 2001년도 ICCAS
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• pp.156.4-156
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• 2001

The uncertainties of an atmospheric re-entry flight with respect to stability and controllability are aerodynamic error, measurement error of the angle of attack, variation of dynamic pressure, wind, and trim position of the control surfaces, etc. During hypersonic flight, a future angle of attack is biased from a nominal schedule. In order words, because the angle of attack is estimated from the navigation data, estimation error occurs due to wind, atmospheric density variation, etc. Error models used in this study, include a standard deviation of +-3 sigma, and are the normal distribution of statistics. This paper shows the appraisement of tracking performance onto the reference trajectory, satisfaction of the initial condition of TAEM about the re-entry system.