• 한국항행학회논문지
• /
• 제28권4호
• /
• pp.386-392
• /
• 2024

본 논문은 도심항공교통(UAM; urban air mobility) 시뮬레이션 제작을 위해 회전익 모델링과 성능 분석에 특화된 프로그램인 flightlab을 활용하여 정밀 동역학 모델을 구축하였다. flightlab은 저고도 및 도심풍에 의해 로터의 상세 공력 특성이 요구되는 UAM 상세 모델링에 적합하다. 따라서, 본 연구에서는 flightlab을 활용하여 UAM 기체 형상으로 주목받고있는 분산추진방식의 lift-cruise UAM 모델을 UAM 모델 구현 및 성능 분석을 수행하였다. lift-cruise 형상의 UAM 모델은 수직 이착륙과 고정익 비행을 각각 담당하는 모터들로 구성된 비행체이다. 현 시점에서는, UAM 모델링에 대한 flightlab 활용 사례가 부족하며, 기존의 고정익이나 드론 모델로는 충분한 평가를 수행하기에는 어렵다. 이에 따라, 본 연구에서는 동일한 lift-cruise 형상의 모델을 matlab을 이용해 구현하고 성능을 확인한 후, flightlab에서의 결과와 비교하여 모델링의 타당성을 심층적으로 검토하였다. 이 과정을 통해 flightlab을 활용한 UAM 상세 모델링의 가능성을 탐구하고, 미래 교통사업 기술적 진보에 이바지하고자 한다.

• 한국안전학회지
• /
• 제8권2호
• /
• pp.78-86
• /
• 1993

This study was aimed at analyzing the mangment system and problem situation related to the lift operation. To this end, 61 construction sites of‘H’construction Co., througnout the nation were surveyed for March 1992-May 1992.

• Structural Engineering and Mechanics
• /
• 제34권3호
• /
• pp.319-334
• /
• 2010

The dynamic response of a finite Bernoulli-Euler beam resting on a tensionless Pasternak foundation and subjected to a concentrated harmonic load is investigated in this study. This load may be applied at the center of the beam, or it may be offset from the center. Since the elastic foundation is assumed to be tensionless, the beam may lift off the foundation, resulting in contact and non-contact regions in the system. An analytical/numerical solution is obtained from the governing equations of the contact and non-contact regions to determine the coordinates of the lift-off points. Although there is no nonlinear term in the equations, the problem appears to be nonlinear since the contact regions are not known in advance. Due to that nonlinearity, the essentials of the problem (the coordinates of the lift-off points) are calculated numerically using the Newton-Raphson technique. The results, which represent the symmetric and asymmetric responses of the beam, are presented graphically in this work. They illustrate the effects of the forcing frequency and the beam length on the extent of the contact regions and displacements.

• 대한설비공학회:학술대회논문집
• /
• 대한설비공학회 2009년도 하계학술발표대회 논문집
• /
• pp.1465-1469
• /
• 2009

Darrieus wind turbine blade is one of the vertical wind power system in which the lift of blade is used. In the calculation of wind power for the type of that, the multiple streamtubes method is known as an effective method. But it has big difference in the region of higher tip speed ratio because the incoming air velocity is used in the calculation of lift. The incoming air velocity is reduced from inlet to outlet continually by transferring energy to the wind blade. In this study, the air velocity on the blade, which is called blade velocity, is obtained with newly developed algorithm and used to determine the lift. And it is verified that applying blade velocity on the lift calculation cause the power prediction to improve dramatically in the region of higher tip speed ratio.

• 한국소음진동공학회:학술대회논문집
• /
• 한국소음진동공학회 2000년도 춘계학술대회논문집
• /
• pp.1473-1478
• /
• 2000

Severe fork-lift truck noise is annoying to an operator as well as one of the noise pollution elements. This paper presents the noise contribution analysis of a cabin type fork-lift truck to identify the major sources and its usage to reduce the interior noise level. The methodologies for this work are sound field analysis, sound intensity test, insertion loss test of duct system and etc. An effective method to suppress interior noise level of fork-lift truck and design guides are suggested.

• 산업공학
• /
• 제23권1호
• /
• pp.58-67
• /
• 2010

The purpose of this paper is to present the development processes of the assembly line tester of power transmission for lift truck. Because power transmission is most important part of lift truck, all assembled powertrain parts must be inspected for operational defects, pressures and RPM. Developed assembly line tester is designed to take about 25 minutes for inspecting each assembled power transmission and located it at the end of assembled line. The assembly line no-load tester consists of three parts: (1) the driving hardware part; for installing and operating the transmission. (2) control PCB part; send data from sensors to a computer and control driving part, (3) operation software of no-load tester; for an automatic inspection or manual inspection, for database management and printing transcripts.

• 공학교육연구
• /
• 제13권5호
• /
• pp.8-14
• /
• 2010

This study intends to study about the blade performance loss occurred due to the variation in the shape of an airfoil from attachment/non-attachment of an erosion shield for the hovercraft. The model in this study has used NACA44XXseries, has designed NACA44XX-series by using the Auto CAD, and it designed the shape that has attached an erosion shield to this model according to the thickness and length. By using these models, a grid was generated by GAMBIT and the lift coefficient ($C_l$) and the drag coefficient ($C_d$) were calculated FLUENT code for flow analysis. Through this, the $C_l$ and $C_d$ have calculated and compared the lift-to-drag ratio that an indicator of airfoil performance according to the shape and attachment/non-attachment of erosion shield.

• Journal of Biosystems Engineering
• /
• 제35권1호
• /
• pp.31-36
• /
• 2010

A small unmanned helicopter was suggested to replace the conventional spray system. Aerial application using an agricultural helicopter helps precise and timely spraying, and reduces labor intensity and environmental pollution. In this research, a rotor system (SW05) was developed and its lift capability was evaluated. Lift force for the dead weight of the helicopter was obtained at the grip pitch angle of $12^{\circ}$. As the pitch angle increased to $14^{\circ}$ and $16^{\circ}$, the payload increased to 176 N and 216 N, respectively. Compared with SW04 airfoil performance in the total lift, the SW05 airfoil showed nearly the same capacity, but the payload of the SW05 was reduced because of the increased dead weight. A rated flight condition was defined as lifting mean payload of 294 N with the grip pitch angles of $16{\sim}17^{\circ}$ at the rotor rotating speed of 850~950 rpm for the adjusted engine power. The fuel consumption would be 4.8~6.0 L/hr, and the air temperature of cooling fan should be kept below $160^{\circ}C$.

• 한국기계가공학회지
• /
• 제18권12호
• /
• pp.91-97
• /
• 2019

Since the 2000s, mechanical parking lots have become an increasingly common solution to serious parking difficulties in urban areas. While safety regulations are in place, they can avert or minimize accidents only when drivers understand and comply with them, and so do not always prevent drivers from making mistakes. As a result, the number of serious accidents caused by driver errors continues to increase in proportion to the rapid increase in vehicles. Most of these accidents are caused by abnormal vehicle entry, despite the safeguards already in place. Therefore, in this thesis, we will study the vehicle entry prevention system and suggest how it can be made more effective in stopping or minimizing accidents.

• Journal of Advanced Marine Engineering and Technology
• /
• 제30권1호
• /
• pp.125-133
• /
• 2006

It is important to understand flow characteristics and performances of sails for both sailors and designers who want to have efficient thrust of yacht In this Paper the viscous flows around sail-like rigid wings, which are similar to main and jib sails of a 30 feet sloop, are calculated using a CFD tool. Lift, drag and thrust forces are estimated for various conditions of gap distance between the two sails and the center of effort of the sail system is obtained. Wind tunnel experiments are also carried out to measure aerodynamic forces acting on the sails system and to validate the computation. It is found that the combination of two sails produces the lift force larger than the sum of that produced separately by each sail and the gap distance between the two sails is an important factor to determine total lift and thrust.