• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2001.07a
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• pp.1088-1091
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• 2001

Temperature-dependent current-voltage characteristics of Organic Light-Emitting Diodes(OLEDs) were studied. The OLEDs were based on the molecular compounds, N,N'-diphenyl-N,N'-bis(3-methylphenyl)-1, 1'-diphenyl-4, 4'-diamine (TPD) as a hole transport and trim(8-hydroxyquinoline) alulninum(Alq$_3$) as an electron transport and emissive material. The current-voltage characteristics were measured in the temperature range of 10[K] and 300[K]. A conduction mechanism in OLEDs was interpreted in terms of tunneling and trap-filled limited current.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 1997.04a
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• pp.249-252
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• 1997

Electroluminescence(EL) devices based on organic thin layers have attracted lot of interests because of their possible application as large-area display-emitting display. One of the problems of such devices is lifetime of the cell, where the degradation of the cell is partially due to the crystalliyzation of organic layers. In large part, this problem can be solved by using a multilayer device structure prepared by vapor deposition technique. In this study, blue light-emitting multilayer organic electroluminescence devices were fabricated vsing Poly (9-vinylcarbaEole) (PVK) and 2- (4-tert-butylphenyl)-5-(4$^{#}$-bis-phenyl) 1,3,4-oxadiazole (PBO) as hole trasport and electron transport material, respectively, where trim(8-hyd roxyquinolinate) aluminum (Al $q_3$) was used as a luminescenct material. A cell structure of glass sub- strate/indume-tin-oxide(ITO)/PCK/Al $q_3$/PBD/Mg:In was employed. Blue emission peak at 510nm was observed with this cell structure.e.

• 제어로봇시스템학회:학술대회논문집
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• 1996.10b
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• pp.1300-1303
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• 1996

In this paper a typical problem is examined that a light, general aviation airplane, such as Cessna or Navion, in gliding turn flight shows helical-dive phenomenon when pilots try to stop the descent by using elevator only. It is known from pilot's experience that in a certain flight trim it is impossible to recover from helical-dive by using elevator only. From this study it is shown that helical-dive phenomenon is involved with longitudinal/lateral dynamics coupling to airplane's aerodynamics. Also this phenomenon consists of three parts of flight dynamics; first of all, fast longitudinal motion occurs, then is followed by a little slow lateral motion, and finally logitudinal/lateral coupled motion is fully developed.

• 제어로봇시스템학회:학술대회논문집
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• 1996.10b
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• pp.1308-1311
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• 1996

We propose a new linearized model which can be used very efficiently for the design and analysis of the autopilot of aerodynamically controlled skid-to-turn missiles. Proposed model is based on the linearized equations of the missile dynamics derived in the aerodynamic frame where xz plane contains the missile longitudinal axis and velocity vector. However, to take the effect due to the small perturbation of the missile body into consideration, we introduce a new frame which is identical to the aerodynamic frame in the trim state but after small perturbation it moves fixed with the missile body, and finally, the proposed model is set up in this frame. It is shown by nonlinear simulations and stability analysis of a numerical example that the new model describes the missile motion better than the conventional one linearized in the body frame with a certain amount of simplification.

• Journal of Contemporary Eastern Asia
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• v.11 no.1
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• pp.43-56
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• 2012

The paper chooses the "Asian Financial Crisis" as a case study to examine its impact on Malaysian economy and describes how Malaysian government responded to the crisis. It also focuses on the Asian financial crisis' impact on the employment of banking sector in Malaysia. In the finance, insurance, real estate and business service sector, a number of 6,596 workers were retrenched. Banks were forced into mergers and acquisition as well as downsizing, trim lean, organizational changes and introduction of new technologies. Excess workers were offered a "voluntary separation scheme." These retrenched workers became the urban poor facing high cost of living and no opportunity for jobs as there is no safety net provided.

• Journal of the Korean Institute of Navigation
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• v.25 no.4
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• pp.417-422
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• 2001

Every ship might be exposed to collision, grounding and/or various accidents. They may make some underwater holes on the hull. An underwater damage would cause her loss of buoyancy, trim, and inclination. Although a ship has some provisions against these accidents, if the circumstance is serious, she would be sunk or upsetted. Because of varieties of type of accidents, one could not prepare all of them. Many subdivision could prevent them, but it is difficult to realize it due to rising costs. This paper deals with physical phenomena of sinkage and an application on box type ship, and some results are earned as follows； 1. sinkage speed up to the level of the damage hole is increased proportionally, and is decreased proportionally after filling the level. 2. the curve of draft shows cup type of second order polynomial up to the damage hole level, and shows cap type of second order polynomial after filling the level. 3. if damage occurs beneath half of the draft, changes of head and displacement, and sinking speed follow almost straight lines. 4. by careful observation, sinkage speed could be predicted.

• Proceedings of the International Microelectronics And Packaging Society Conference
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• 2006.02a
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• pp.1-14
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• 2006

[ $\blacklozenge$ ] PCB에 있어서 Embedded passive 는chip을 직접 내장하는 방법과 특별한 특성을 갖는 재료 및 공법을 사용하여 chip 응 대치하는 방법이 있다. $\blacklozenge$ Embedded passive PCB가 적용될 수 있는 유력한 적용 분야는 소형화가가 요구되는 분야와 고속 특성이 요구되는 분야를 들 수 있고, 따라서, Module, SOP/SIP, Package substrate 등이 우선적으로 적용될 수 있는 분야다. $\blacklozenge$ Embedded capacitor를 적용한 경우, 일반적인 chip capacitor를 적용한 경우보다 더 좋은 전기적인 특성(SRF, Q)을 얻을 수 있으며, solder joint 등의 영향을 포함하면 더욱 좋은 특성이 얻어질 수 있다. $\blacklozenge$ Embedded passive 의 상용화를 위해서, 공차를 관리하는 방법의 개발과 공차에 대한 합리적인 규격을 설정하는 것이 우선 과제이다. $\blacklozenge$ Embedded resistor 의 경우, Laser trim을 적용하여 ${\pm}\;5\%$ 또는 그 이하의 공차를 실현할 수 있고, $30\;K\Omega/sq$. 의 고저항의 적용까지 가능하다. $\blacklozenge$ 고속 신호에서의 noise 감소, module, SIP/SOP 의 소형화를 실현하는데 Embedded passive(혹은 active)PCB 가 기여 할 수 있을 것이고, 이를 위하여 Set 업체, PCB 업체, 재료 업체간의 지속적인 협조가 필요할 것이다.

• 유체기계공업학회:학술대회논문집
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• 2001.11a
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• pp.271-278
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• 2001

Structural and dynamic analyses of inducer and impeller for a oxidizer turbopump are peformed to investigate the safety level of strength and vibration at design point. Due to high rotational speed of turbopump, effects of centrifugal forces are carefully considered in the structural analysis. Hydrodynamic pressure is also considered as an external force applied to inducer and impeller blades. A three dimensional finite element method(FEM) is used for linear and nonlinear structural analyses with modified Newton-Raphson iteration method. After the nonlinear trim solution is obtained from the structural analysis, dynamic characteristics are obtained as a function of rotational speed from the linearized eigenvalue analysis at an equilibrium position. According to the results of numerical analysis, the safety margins of strength and vibration resonances m sufficient enough to be operated safely within the required life cycle.

• 유체기계공업학회:학술대회논문집
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• 2006.08a
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• pp.45-46
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• 2006

Usual LEO satellite for earth observation use a blowdown hydrazine monopropellant propulsion system for attitude hold and orbit maintenance. For precision control, thruster valve has very short closing time, but this can cause water hammering and pressure surge. Since water hammering and pressure surge can cause damage of propulsion system and ununiform thrust, Thruster valve closing is one of the special concern during satellite propulsion system design. In this paper, an analysis for propellant feed system is conducted using the method of characteristics. The results represent water hammer effect is negligible even at the worst case and pressure surge can be decreased effectively with a trim orifice.

• 제어로봇시스템학회:학술대회논문집
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• 2001.10a
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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.