• Journal of the Society of Naval Architects of Korea
• /
• v.38 no.1
• /
• pp.86-98
• /
• 2001

Due to the rapid growth of ship building industry and the increment of ship construction in Korea, several hundred thousand of lifting lugs per year, have been installed at the lifting positions of ship block and removed after finishing their function, therefore. appropriate design system for the strength check or the optimal design of each lug structure has been required in order to increase the capability of efficient design. In this study, the design system of D-type lifting lug structure which is most popular and useful in shipyards, was developed for the purpose of initial design of lug structure. Developed system layout and graphic user interface for this design system based on the $C^{++}$ language were explained step by step. Through the illustration of one example of D-type lug designs, the efficiency of this design system was proved. Therefore, more efficient performance of practical lug structural design will be expected on the windows of personal computer using this design system.

• Transactions of the Korean Society of Mechanical Engineers A
• /
• v.35 no.7
• /
• pp.821-826
• /
• 2011

CAE-based structural optimization techniques are applied for the design of a lightweight crane. The boom of the crane is designed by shape optimization with the shape of the cross section of the boom as the design variable. The design objective is mass minimization, and the static strength and dynamic stiffness of the system are set as the design constraints. Hyperworks, a commercial analysis and optimization software, is used for shape and topology optimization. In order to consistently change the shape of the elements of the boom with respect to the change in the shape of its cross section, the morphing function in Hyperworks is used. The support of the boom of the original model is simplified to model the design domain for topology optimization, which is discretized by using three-dimensional solid elements. The final result after shape and topology optimization is 19% and 17% reduction in the masses of the boom and support, respectively, without a deterioration in the system stiffness.

• Journal of the Korean Society of Propulsion Engineers
• /
• v.4 no.2
• /
• pp.6-11
• /
• 2000

In the pressurized propellant feed system of liquid rocket, feed pressure is decided chamber pressure of normal combustion state. However, during ignition period the initial chamber pressure is atmosphere. So, it may have overflow, hard-start and even critical damage of engine. This paper proposes an improved propellant feed system for the stable combustion of liquid rocket. Hot test were already performed to verify the presented propellent feed system. The proposed propellant feed system uses two steps - pre and main combustion - to prevent large pressure increase and uses cavitating venturis for stable flow rate in whole combustion. This system feeds the flow rate lesser than the designed flow rate, so combustion pressure reached pre-combustion pressure. Cavitating venturis offer unique flow control capabilities at normal and abnormal combustion state, because flow rate is solely dependent on upstream absolute pressure and fluid properties, but independent on downstream condition.

• Journal of Digital Convergence
• /
• v.16 no.6
• /
• pp.197-204
• /
• 2018

The realistic Visual Effects using fluid simulation in 3D computer graphics are operated as important factors to improve the quality of images. The process of creating realistic motions of water, fire, explosion by controlling each property of fluid is called fluid simulation. In general, the creation of a fluid simulation concentrates on the main simulation work phase, however an effective method for initial set up is important for the main simulation work. The purpose of this study is to analyze the factors involved in the initial emission motion and shape of fluid and propose methods that can efficiently apply this into the initial set up. For the process of the research, first, problems are raised based on related researches, and second, two experiments, 'Dynamic Fluid Emitter Creation' and 'User Design Type Emission Velocity Solution', are conducted for more effective fluid simulation. Through this research, the effective fluid simulation of initial set up phase will be suggested through the user design-type emission control solutions.

• Journal of IKEEE
• /
• v.17 no.2
• /
• pp.168-175
• /
• 2013

The delay times due to the propagating of data on PCB depend on the shape and length of interconnection lines when memory controllers and high speed memories are soldered on the PCB. The dependency on the placement and routing on the PCB requires redesign of I/O logic or reconfiguration of the memory controller after the delay time is measured if the controller is programmable. In this paper, we propose architecture of configuring logic for the delay time estimation by writing and reading test patterns while initializing the memories. The configuration logic writes test patterns to the memory and reads them by changing timing until the correct patterns are read. The timing information is stored and the configuration logic configures the memory controller at the end of initialization. The proposed method enables easy design of systems using PCB by solving the problem of the mismatching caused by the variation of placement and routing of components including memories and memory controllers. The proposed method can be applied to high speed SRAM, DRAM, and flash memory.

• The Bulletin of The Korean Astronomical Society
• /
• v.37 no.2
• /
• pp.198.1-198.1
• /
• 2012

저궤도 위성이 발사체에서 분리된 후 탑재 소프트웨어에 의한 초기 동작이 수행되고 나면 초기 운용이 시작된다. 초기 운용 기간에 수행할 모든 절차와 대처 가능한 긴급 상황이 발생할 경우 수행할 절차는 발사 전에 미리 준비된다. 위성의 각 부분의 설계 마진은 최악 조건을 기준으로 반영되어 있기 때문에 발사 이후의 버스 시스템 관점에서의 위성 특성은 요구 사항을 만족하는 범위가 될 것으로 예상이 가능하다. 실제로 발사 후 위성 텔레메트리 분석을 통해 대부분의 항목에서 요구 조건을 만족하는 것으로 확인되었다. 또한 텔레메트리 분석을 통해 설계 단계에서 예상했던 것 보다 정확한 궤도 특성이 반영된 위성 특성을 파악하였다. 이러한 특성은 설계 시 고려했던 상황과 다르더라도 실제 궤도 특성이 반영된 특성이므로 초기 운용 및 정상 운용 시에 정상적인 상황인 것으로 고려해야 한다. 첫째, 지구 알베도 특성에 따라 태양센서 값이 궤도에 따라 변화한다. 위성의 자세가 정확히 태양을 지향하고 있더라도 태양센서에 지구에서 반사된 빛이 입사되어 자세 제어에 영향을 주게 된다. 알베도의 영향은 적도에서 극지방으로 갈수록 커지며, 계절에 따라 다른 특성을 보인다. 알베도의 영향을 최소화하기 위해 자세 제어 모델에 알베도 효과를 고려하거나 알베도 효과를 무시할 수 있을 정도로 자세 제어 오차 한계를 조정할 수 있다. 둘째, 위성의 지구 회피 회전에 의해 태양 전지판의 온도가 궤도에 따라 변화한다. 위성체는 위성체에 장착된 두 개의 별센서의 가시성 확보를 위해 태양 지향 자세에서 요축으로 일정 속도로 회전한다. 남극 부근에서는 두 태양 센서가 모두 지구의 반대편인 남쪽을 지향하도록 하며, 북극 부근에서는 북쪽을 지향하도록 한다. 이 때 두 태양 센서의 방향에 장착된 태양 전지판은 극지방에서 지구 반대편에 위치하므로 다른 태양 전지판에 비해 낮은 온도를 갖게 된다. 이 논문에서는 위성의 궤도 특성에 따른 고려 사항에 대해 설명하였다.

• Journal of Korean Society of Steel Construction
• /
• v.27 no.1
• /
• pp.23-30
• /
• 2015

Developed in this study were Octagonal-hollow-section(OHS) struts, whose compressive strengths against flexural and local buckling is higher than H-shape or rectangular-hollow-section(RHS) struts with the same unit weight. OHS members are also advantageous in handling and storing compared to circular hollow sections(CHS). OHS members were fabricated from HR Plates by cold forming and fillet welding. 5 numbers of 20m long OHS struts were assembled, each of which consist of two 9.6m long OHS member and two end connection elements made of cast iron. The compressive strength of the OHS strut was evaluated by comparing the test results, design codes and FEM analysis each other. Test results show that all of the struts have almost same or larger compressive strength than Korean Road Bridge Design Code(KRBDC) (2012). The initial imperfections can be estimated by using measured strains and are turned out to be less than L/450 for all the struts tested. The results of FEM analysis show that the variation of initial imperfection has less effects on the compressive strength for struts with vertical surcharge than for those with self-weight only, while the strength decreases as the initial imperfection increases. As the result of this study, the allowable initial imperfection for 20m long OHS struts is recommended to be less than L/350 on job sites.

• Journal of the Institute of Electronics and Information Engineers
• /
• v.49 no.12
• /
• pp.234-241
• /
• 2012

This paper proposes a novel design methodology considering transistor layout variation. The proposed design technique is to improve the transistor's electrical characteristics without performing a circuit simulation to extract transistor layout variation. There are three advantages in the proposed method. Firstly, there is no need to change the normal design flow used in layout designs. Secondly, there is no need to perform simulation in order to extract the transistor layout variation. Thirdly, early warnings in layout design lead to decreasing the number of post layout simulations. Less post layout simulations will decrease the number of iterations in the design cycle and shorten design period. The number of bad transistors in the early design phase were reduced from 17.8% to 2.9% by applying eDRC environment for layout designers to develop Standard Cell Library.

• Journal of the Society of Naval Architects of Korea
• /
• v.28 no.2
• /
• pp.52-68
• /
• 1991

A new propeller series is developed using the newly developed blade section(KH18 section) which behaves better cavitation characteristics and higher lift-drag ratio at wide range of angle-of-attack. The pitch and camber distributions are disigned in order to have the same radial and chordwise loading distribution with the selected circumferentially averaged wake input. Since the geometries of the series propeller, such as chord length, thickness, skew and rate distribations, are selected by regression of the recent full scale propeller geometric data, the performance prediction of a propeller at preliminary design stage can be mure realistic. Number of blades of the series propellers is 4 and the expanded blade area ratios are 0.3, 0.45, 0.6 and 0.75. Mean pitch ratios are selected as 0.5, 0.65, 0.8, 0.75 and 1.1 for each expanded area ratio. The new propeller series is composed of 20 propellers and is named as KD(KRISO-DAEWOO) propeller series. Propeller open water tests are performed at the experimental towing tank, and the cavitation observation tests and fluctuating pressure measurements are carried out at the cavitation tunnel of KRISO. $B_{P}-\delta$ curves, which can be used to select the optimum propeller diameter at the preliminary design stage, are derived from a regression analysis of the propeller often water test results. The KD-cavitation chart is derived from the cavitation observation test results by choosing the local maximum lift coefficient and the local cavitation number as parameters. The caviy extent of a propeller can be predicted more accurately by using the KD-cavitation chart at a preliminary design stage, since it is derived from the results of the cavitation observation tests in the selected ship's wake, whereas the existing cavitation charts, such as the Burrill's cavitation chart, are derived from the test results in uniform flow.

• Proceedings of the Korean Institute of Communication Sciences Conference
• /
• 1995.10a
• /
• pp.979-982
• /
• 1995