• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.11
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• pp.951-966
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• 2017

In this work, numerical analyses are carried out and the behaviors are investigated for three types of double-acting oleo-pneumatic shock absorbers along with the mathematical models proposed in the part I of this work. After presenting each numerical algorithm corresponding to each model, the numerical algorithms are implemented as user-subroutines in MSC/ADAMS commercial multi-body dynamic software. By using the developed user-subroutines, numerical studies are carried out for compression/stretch test as well as drop test. From the comparative studies, we investigated the salient feature of each double-acting oleo-pneumatic shock absorber. Results identifies that it is possible to increase the absorbing efficiency in accordance with the requirements for aircraft landing conditions.

• Journal of the Computational Structural Engineering Institute of Korea
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• v.14 no.4
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• pp.515-523
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• 2001

In this paper results of a linear structural analysis for design and dimensioning of disposal containers for spent pressurized water reactor nuclear fuel and spent Canadian deuterium and uranium reactor nuclear fuel are presented. The container structure studied here is a solid structure with a cast insert and a corrosion resistant outer shell, which is designed for the spent nuclear fuel disposal in a deep repository. An evenly distributed load of hydrostatic pressure from the groundwater and large swelling pressure from the bentonite buffer are applied on the container. Hence, the container must be designed to endure these large pressure loads. In this study, the array type of inner baskets and thicknesses of outer shell and lid/bottom are attempted to be determined through a linear static structural analysis.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.45 no.11
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• pp.939-950
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• 2017

In this work, mathematical models are newly presented for three types of double-acting oleo-pneumatic shock absorbers as the first part of a comparative study on the several types of double-acting oleo-pneumatic shock absorbers. After a typical single-acting shock absorber model is presented for the sake of completeness, mathematical models of three types of double-acting shock absorbers are proposed. To derive the models, Bernoulli equation and orifice discharge coefficient are utilized along with the assumptions of incompressibility and poly-tropic process. The proposed models are expected to be used for investigation of the salient features of several types of double-acting oleo-pneumatic shock absorbers.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2008.11a
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• pp.734-735
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• 2008

Shock absorber for rotorcraft landing gear should absorb landing impact during landing and isolate vibration to fuselage during taxiing. Double stage oleo-pneumatic shock absorber is known to have better performances than single stage oleo-pneumatic shock absorber. This paper deals with the z-direction translational acceleration at mass center, roil and pitch angular acceleration of fuselage for single and double stage oleo-pneumatic shock absorber at nose landing gear when a 6DOF rigid model is taxiing on the pound.

• Journal of the Korea Institute of Military Science and Technology
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• v.7 no.2 s.17
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• pp.118-125
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• 2004

In anti-ship missile, the seeker and guidance control units are located in front of warhead. When the missile hits target, these structures play an important role to warhead structure like a shock absorber Because the shock waves are attenuated, the survival probability of warhead increases which guarantees the explosive train. In this thesis the role of frontal sections is studies. The theoretical analysis and numerical analyses using LS-DYNA code are performed. To prove the effect of shock absorber, the penetration test using subscale prototype warhead are executed.

• Journal of the Korean Chemical Society
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• v.36 no.3
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• pp.393-404
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• 1992

The response properties of continuous automated system using an enzyme reactor for determination of urea were investigated. The enzyme reactor was constructed to packed-bed form which filled with nylon-6 beads (42∼48 mesh), which immobilized urease with glutaraldehyde, in teflon tube (2 mm I.D., 20 cm length). The system was composed of the enzyme reactor, gas dialyzer, and tublar PVC-nonactin membrane ammonium ion-selective electrode as an indicator electrode in serial order. The response characteristics of this system were as follows. That is, the concentration range of linear response, slope of linear response, detection limit, and conversion percentage were $5.5{\times}10^{-6}$∼$2.4{\times}10^{-3}M$, 57.8 mV/decade, $1.5{\times}10^{-6}$, and 80.8%, respectively. The optimum buffer and life time of urease reactor were 0.01M Tris-HCl buffer solution (pH 7.0∼7.8) and 0.01M phosphate buffer solution (pH 6.9∼7.5) and about 150 days, respectively. And the urease reactor had no interferences of the other physiological materials.

• Korean Journal of Optics and Photonics
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• v.20 no.3
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• pp.182-188
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• 2009

The surface plasmon resonance ellipsometer (SPRE), using a multiple air injection system with an extraction of air system, has been proposed and developed to minimize measurement error of signals due to diffusion of reagent into running buffer. Since the diffusion of reagent into running buffer affects the refractive index of the running buffer by changing the concentration, characteristics of binding between various bio-molecules don't appear clearly in measurement results. The diffusion between running buffer and reagent can be blocked by using an air bubble injection system. An extraction of air system is used to remove the noise signal due to unnecessary air bubbles flowing in a channel. Reliability of measurement results has been improved by using the valve system.

• Journal of the Korean Society of Manufacturing Process Engineers
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• v.15 no.6
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• pp.9-15
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• 2016

Due to material-specific vulnerabilities, the surfaces of the liquid crystal glasses used in mobile phones can crack easily, with even the smallest cracks undergoing propagation. To protect the glass surfaces, films are attached to the surfaces during the mobile phone production process. However, after machining the liquid crystal, removal of the film on the liquid crystal surface using chemical and mechanical methods is required. In this research, a peeling apparatus was developed for removing the films attached to liquid crystal surfaces during the production process. Mechanical attachment and design automation through experimentation and finite element modelling were performed to confirm the validity of the design.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 1992.10a
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• pp.3-7
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• 1992

포는 대체로 정확도와 최대 발사거리 및 최대 발사속도 등에 의해 그 성능 이 표현된다. 그 중에서도 최대 발사속도는 매우 중요한 인자로서 포의 주퇴 복좌 장치의 성능에 의해 직접적으로 영향을 받게 된다. 따라서 포의 최대 발사속도 향상을 위해서는 주퇴복좌 장치의 동특성 해석 능력을 확보하고, 그로부터 주퇴 장치의 설계 변경이 가능하도록 해야 한다. 한편, 주퇴복좌기 의 주퇴특성은 주퇴시 총주퇴저항력이 전주퇴장에 대해서 거의 일정해야만 포신에 전달되는 힘을 최소로 하면서 주퇴시간을 최소로 할 수 있으며 이러 한 설계 개념으로 주퇴복좌기를 설계한다. 그에 따라 주퇴복좌기는 그 내부 가 가변 오리피스 및 조절 로드로 이루어져 주퇴복좌기의 주퇴 저항력을 주 퇴속도 및 주퇴변위에 따라 변화시키도록 되어 있다. 따라서 주퇴복좌기는 필연적으로 강한 비선형 특성을 나타낸다. 이러한 주퇴복좌기를 모델링할 때 에 기존에는 주퇴복좌기내의 모든 유체역학적 요소를 고려하여 모델링하는 기법이 통용되어왔다. 그러나 이러한 모델링은 각 요소의 모델링 오차가 누 적될 위험이 있으므로 정확한 모델링을 보장할 수 없으며, 매우 복잡한 과정 을 거쳐야 한다. 따라서 본 연구에서는 주퇴 완충기 시뮬레이터를 이용한 실 험에 따른 계의 파라미터 예측을 통하여 모델링하는 기법을 시도하여 보았 다.

• Aerospace Engineering and Technology
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• v.6 no.1
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• pp.19-28
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• 2007

In this study, a nonlinear 2 degree of freedom mathematical model has been developed for impact analysis of the nose landing gear of a light aircraft which is composed of an wheel & tire, an Oleo-pneumatic shock strut and the castering wheel fork for the differential braking steering, and then the response of impact is computed using a numerical method. The mathematical model of a nose landing gear contains nonlinear characteristics which are an impact load - deflection property of a tire and internally frictional forces between an inner surface of an upper cylinder and a bearing of a lower rod due to side forces like the declined angle of strut, the moment due to an wheel fork, the side drag due to a steering and it is computed using the 4th-order Runge-Kutta method. The comparison process between analytical results and experimental results of the other proven nose landing gear is carried out to verify the mathematical model.