• Proceedings of the KOSOMBE Conference
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• v.1994 no.12
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• pp.71-74
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• 1994

In cementless total hip arthroplasty(THA), an initial stability of the femoral component is mandatory to achieve bony ingrowth and secondary long term fixation. Bone ingrowth depends strongly on relative micromotion and stress distributions at the interface. Primary stability of the femoral component can be obtained by minimizing the magnitude of relative micromotions at bone-prosthesis interface, Hence an accurate evaluation of interface behavior and stress/strain fields in the bone implant system may be relevant for better understanding of clinical situations and improving THA design. However, complete evaluation of load transfer in the bone remains difficult to assess experimentally, Hence, recently finite element method (FEM) was introduced in orthopaedic research field to fill the gap due to its unique capacity to evaluate stress in structure of complex shape, loading and material behavior. The authors developed the 3-dimensional numerical finite element model which is composed of totally 1179 elements off and 8 node blick. We also analyzed the micromotions at the bone-stem interface and mechanical behavior of existing bone prosthesis for a loading condition simulating the single leg stance. The result indicates that the values of relative motion for this well fit Multilock stem were $150{\mu}m$ in maximum, $82{\mu}m$ in minimum, and the largest relative motion developed in medial region of proximal femur with anterior-posterior direction. The proximal region of the bone was much larger in motion than the distal region and the stress pattern shows high stress concentration on the cortex near the tip of the stem. These findings indicates that the loading in the proximal femoral bone in the early postoperative situation can produce micromotions on the interface and clinically cementless TEA patient should not be allowed weight bearing strictly early in the postoperative period.

• Composites Research
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• v.29 no.6
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• pp.369-374
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• 2016

In this study, a structural optimal design of 10 MW composite blade was performed using bend-twist coupled(BTC) design concept. Bend-twist coupling of blade means the coupling behavior between the bending and torsional deflections due to the composite lamina with fiber angle biased from the blade longitudinal axis. This can potentially improve the overall performance of composite blade and reduce the dynamic loading. Parametric studies on layup angle, thickness and area of off-axis carbon UD were conducted to find the optimum coupling effect with weight reduction. Comparing the results of fatigue load analysis between conventional model and BTC applied model, the damage equivalent load(DEL) of blade root area were decreased about 3% in BTC model. To verify the BTC effect experimentally, a 1:29 scaled model was fabricated and the torsion at the tip under deflection behavior of blade stiffener model was measured by static load test.

• Journal of Technology Innovation
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• v.8 no.2
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• pp.19-65
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• 2000

This study analyzes the development of technological infrastructure(TI) and technological infrastructure policy(TIP) to enhance the technological capabilities of small and mid-sized manufacturing enterprises(SMEs) in the U.S. and Korea in terms of the technological system(TS) concept, which is composed of technological infrastructure, industrial organization, and institutional infrastructure. In order to analyze the internal dynamics of the system, such as incentive mechanisms, the interaction among economic actors, and the policy implementation process, we compare the MEP(Manufacturing Extension Partnership) system of the U.S. and the Joong-Jin-Gong system of Korea. Among many similarities, contrasts, and insights from each country's effort to construct TI and TS, the main findings are as follows. (1) Both the MEP system and the Joong-Jin-Cong system are TI-led or government-led type TS. However, the nation-wide picture is different: in the U.S., most TSs including the MEP system., are classified as TI-led type; in Korea, many TI-assisted or private sector-led TSs have been developed since the early 1960s. (2) the MEP system, as a representative case of the U.S., is less stable than the Joong-Jin-Gong system of Korea in terms of financing and political cycle. (3) The MEP system is a more complex and cooperative network than the Joong-Jin-Gong system. NIST, as a critical mass, generates the system, bridges various institutions, and influences the development of the system by providing funding. (4) Regarding TI components, TSs in both countries focus on utilizing off-the-shelf technologies rather than advanced technologies. However, the direction of movement is different: in the U.S., TSs have come to emphasize existing technologies to counterbalance an innovation system that has been highly focused toward new technologies; in Korea, TSs have been moving from focusing on a higher diffusion rate of imported process technologies to stressing new technology development. (5) Personnel and staffing, embodying technological capability, is an important concern in both countries. But the human capital infrastructure of the U.S. system is more efficient and industry-oriented than that of the Korean system due to a more flexible labor market. (6) While the U.S. has a strong tradition of state and local autonomy in constructing TI and TS to fit SMEs's specific need, Korea has a centralized and bureaucratically-led policy implementation process.

• Proceedings of the Korean Vacuum Society Conference
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• 2000.02a
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• pp.45-45
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• 2000

PDP, FED, 그리고 VFD와 같은 마이크로 전자디스플레이 장치를 제작하기 위한 가장 중요한 기술중에 하나인 패널 내를 고진공으로 만드는 것과 초기의 진공을 유지하는 것이다. PDP 디스플레이는 전면판과 후면판으로 구성되어 있다. 전면판은 ITO전극, 절연체 그리고 MgO보호막으로 구성되어 있으며, 후면판은 어드레스 전극, 반사층, 격벽, 그리고 형광체층이 있다. 기존의 방식은 대기에서 프릿 글라스를 이용하여 두 장의 유리를 봉입하고, 후면판 모서리 부분에 있는 구멍에 배기 글라스 튜브를 붙이고, 튜브를 통해서 배기하고, 플라즈마 가스를 채우고, 최종적으로 tip-off를 한다. 이러한 기존의 방식을 통해서는 배기 컨덕턴스의 한계로 얻을 수 있는 초기 진공도에 한계가 있다. 아울러 두 장의 유리사이는 150$\mu$m 정도의 간격으로 되어 있고, 이웃한 격벽사이는 320$\mu$m 정도의 미세한 공간이 주어지는 구조가 컨덕턴스를 저하시킨다. 이와 같은 초기 진공도의 한계성을 극복하기 위한 연구로서, PDP 패널을 구성하는 두 장의 글라스를 진공 챔버내에서 IR heater를 이용하여 실장하였다. 대개 PbO, ZnO, SiO2,, 그리고 B？로 구성된 프릿 글라스를 대기에서 전면판에 dispensing하고 가소한다. 그리고 프릿 글라스가 형성된 전면판과 후면판을 loading, align 한 다음, 2 10-7torr까지 펌핑한 후 heating, holding 그리고 cooling 공정을 수행하므로 써 두 장의 유리를 실장하였다. 그러나 온도의 non-uniformity, 프릿 성분에 따라서 crack과 기포문제가 진공 실장과정에서 발생하였다. 이와 같은 문제를 개선하기 위해 프릿 글라스의 새로운 조성과 온도 uniformity를 유지하므로써, 프릿 글라스의 기포와 crack 발생없이 재현성 있게 진공 실장하였다. Leak channel 형성유무를 검증하기 위하여 챔버 자체의 펌핑 속도와 제작된 패널의 펌핑 속도를 비교하므로써, leak channel형성 유무를 평가할 수 있는 방법을 이용하였다. 이와 같은 방법을 이용하여, crack 또는 기포가 있는 패널은 leak channel을 형성하여 패널내의 진공을 유지할 수 없음을 검증하였고, crack 또는 기포가 없는 패널은 leak channel없이 패널내의 진공을 유지할 수 있음을 검증하였다. 결과적으로 진공 인-라인 실장시 가장 중요한 요인인 프릿의 변화를 분석하므로써, 고진공을 요구하는 FPD(PDP, FED, VFD)에 적합하게 적용할 수 있으며, 아울러 실장시 진공도를 개선하므로 패널내부의 오염을 최소화하여 디스필레이로서의 효율을 극대화할 수 있을 것이다.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.33 no.2
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• pp.22-31
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• 2005

A design study was conducted for a new concept aircraft(Canard Rotor/Wing: CRW) that has the capability of dual mode flight, a rotorcraft and a fixed wing mode. The CRW can show a vertical take off/landing and a high speed/efficiency cruise performance simultaneously. It is not surprising to develop a new sizing code for this class of aircraft because conventional sizing codes developed solely for either the rotary wing or the fixed wing aircraft are not adequate to design a dual mode aircraft operated both by the rotary wing through tip jet effux and the fixed wing lift. Thus, a new design code was developed based on the conventional sizing code by adding some features including rotor performance, duct flow, and engine flow analysis, hence could eventually predict the performance of reaction driven rotor, the flight performance and the flight characteristics. The various design parameters were investigated to find their influences on the flight performance then, a small UAV(Unmanned Aircraft Vehicle) of 1500 lbs class was optimally designed to have minimum weight using the developed sizing code.

• Molecules and Cells
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• v.22 no.2
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• pp.146-153
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• 2006

Cell polarity is critical for the division, differentiation, migration, and signaling of eukaryotic cells. RAX2 of budding yeast encodes a membrane protein localized at the cell cortex that helps maintain the polarity of the bipolar pattern. Here, we designate SPAC6f6.06c as $rax2^+$ of Schizosaccharomyces pombe, based on its sequence homology with RAX2, and examine its function in cell polarity. S. pombe $rax2^+$ is not essential, but ${\Delta}rax2$ cells are slightly smaller and grow slower than wild type cells. During vegetative growth or arrest at G1 by mutation of cdc10, deletion of $rax2^+$ increases the number of cells failing old end growth just after division. In addition, this failure of old end growth is dramatically increased in ${\Delta}tea1{\Delta}rax2$, pointing to genetic interaction of $rax2^+$ with $tea1^+$. ${\Delta}rax2$ cells contain normal actin and microtubule cytoskeletons, but lack actin cables, and the polarity factor for3p is not properly localized at the growing tip. In ${\Delta}rax2$ cells, and endogenous rax2p is localized at the cell cortex of growing cell tips in an actin- and microtubule-dependent manner. However, ${\Delta}rax2$ cells show no defects in cell polarity during shmoo formation and conjugation. Taken together, these observations suggest that rax2p controls the cell polarity of fission yeast during vegetative growth by regulating for3p localization.

• The Bulletin of The Korean Astronomical Society
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• v.36 no.2
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• pp.155.1-155.1
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• 2011

The Korea Astronomy and Space Science Institute (KASI) and the Department of Astronomy at the University of Texas at Austin (UT) are developing a near infrared wide-band high resolution spectrograph, IGRINS (Immersion Grating Infrared Spectrograph). The white-pupil design of the instrument optics uses 7 cryogenic mirrors including 3 aspherical off-axis collimators and 4 flat fold mirrors. Two of the 3 collimators are H- and K-band pupil transfer mirrors and they are designed as compensators for the system alignment in each channel. Therefore, their mount design will be one of the most sensitive parts in the IGRINS optomechanical system. The other flat fold mirrors are designed within the limited area. Each of those includes the features of 3 axial hard points and 2 radial hard points with one spring plunger in order for the proper deflection of the mirror. The design work will include the computer-aided 3D modeling and finite element analysis (FEA) to optimize the structural stability and the thermal behavior of the mount models. The mount body will also include a tip-tilt and translation adjustment mechanism to be used as the alignment compensators.

• Physical Therapy Korea
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• v.13 no.4
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• pp.23-29
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• 2006

The purpose of the present study was to examine gaze effects on spatial and kinematic characteristics during a pointing task. Subjects were asked to watch and point to an aimed target (2 mm in diameter) displayed on a vertically mounted board. Four gaze conditions were developed as combinations of "seeing-aiming" in terms of the eye movements: Focal-Focal (F-F), Focal-Fixing (F-X), Fixing-Focal (X-F), and Fixing-Fixing (X-X). Both the home target and an aimed target were presented for 1 second and then were disappeared in F-F and X-F. In X-F and X-X, only an aimed target disappeared after 1 second. Subjects were asked to point (with index finger tip) to an aimed target accurately as soon as the aimed target was removed. A significant main effect of gaze was found (p<.01) for normalized movement time. Peripheral retina targets had significantly larger absolute error compared to central retina targets on the x (medio-lateral) and z (superior-inferior) axes (p<.01). A significant undershooting to peripheral retina targets on the x axis was found (p<.01). F-F and X-F had larger peak velocities compared to F-X and X-X (p<.01). F-F and X-F were characterized by more time spent in the deceleration phase compared to F-X and X-X (p<.01). The present study demonstrates that central vision utilizes a form of on-line visual processing to reach to an object, and thus increases spatial accuracy. However, peripheral vision utilizes a relatively off-line visual processing with a dependency on proprioceptive information.

• Aerospace Engineering and Technology
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• v.12 no.1
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• pp.22-31
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• 2013

Flight tests on flight control performance of helicopter, conversion and airplane mode for the Smart UAV were completed. Automatic take-off and landing, automatic return home as well as automatic approach to hover were performed in helicopter mode. Climb/descent, left/right turn using speed and altitude hold mode were performed in each $10^{\circ}$ tilt angle in conversion mode. The rotor speed in airplane mode was reduced to 82% from 98% RPM in order to increase rotor efficiency with reducing Mach number at tip of rotors. It reached to the designed maximum speed, $V_{TAS}$=440 km/h at 3 km altitude. This paper presents the flight test result on full envelopment of Smart UAV. Detailed test plan and test data on control performance were also presented to prove that all data meets the flying qualities requirement.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 2004.03a
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• pp.513-520
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• 2004

A steady-state/transient performance simulation model was newly developed for the propulsion system of the CRW (Canard Rotor Wing) type UAV (Unmanned Aerial Vehicle) during flight mode transition. The CRW type UAV has a new concept RPV (Remotely Piloted Vehicle) which can fly at two flight modes such as the take-off/landing and low speed forward flight mode using the rotary wing driven by engine bypass exhaust gas and the high speed forward flight mode using the stopped wing and main engine thrust. The propulsion system of the CRW type UAV consists of the main engine system and the duct system. The flight vehicle may generally select a proper type and specific engine with acceptable thrust level to meet the flight mission in the propulsion system design phase. In this study, a turbojet engine with one spool was selected by decision of the vehicle system designer, and the duct system is composed of main duct, rotor duct, master valve, rotor tip-jet nozzles, and variable area main nozzle. In order to establish the safe flight mode transition region of the propulsion system, steady-state and transient performance simulation should be needed. Using this simulation model, the optimal fuel flow schedules were obtained to keep the proper surge margin and the turbine inlet temperature limitation through steady-state and transient performance estimation. Furthermore, these analysis results will be used to the control optimization of the propulsion system, later. In the transient performance model, ICV (Inter-Component Volume) model was used. The performance analysis using the developed models was performed at various flight conditions and fuel flow schedules, and these results could set the safe flight mode transition region to satisfy the turbine inlet temperature overshoot limitation as well as the compressor surge margin. Because the engine performance simulation results without the duct system were well agreed with the engine manufacturer's data and the analysis results using a commercial program, it was confirmed that the validity of the proposed performance model was verified. However, the propulsion system performance model including the duct system will be compared with experimental measuring data, later.