• Transactions of the Korean Society of Mechanical Engineers A
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• v.25 no.3
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• pp.478-485
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• 2001

A dynamic load simulator(DLS) which can reproduce on-ground the aerodynamic hinge moment of control surface is an essential rig for the performance and stability test of aircraft actuation system. By setting up load actuator as counter acting with the control surface driving actuator and designing an appropriate force control system for load actuator, DLS can be mechanized. Obtaining an accurate mathematical model for the DLS is the first step to successfully design an aerodynamic load replicati on system. Two theoretical models are presented and tested for their validities with the experimental results, which turns out to be not successful. An alternative way of using system identification approaches in investigated to develop a good nominal model for DLS dynamics, and suitable uncertainty bounds for this nominal model are proposed with the consideration of experimental results.

• Journal of Advanced Marine Engineering and Technology
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• v.36 no.4
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• pp.467-475
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• 2012

In this paper, a technical method of reducing torque load of exoskeleton device, with using of a gravity compensator based on a torsion bar, for human leg joints, is proposed. Design and structure analyses and also performance test were performed to estimate and to measure the characteristics of the torsion bar. On the basis of design and structure analysis, a new light and compact exoskeleton device has been developed. For the purpose of lightening and optimizing thickness of the links, FEM analysis has been performed.

• Transactions of Materials Processing
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• v.15 no.8 s.89
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• pp.597-602
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• 2006

Bulk plastic forming characteristics were studied for the magnesium alloy, AZ31 in warm backward extrusion. Effects of process conditions such as extrusion ratio, forming temperature, and punching speed were investigated respectively. Variation of microstructure induced by the warm backward extrusion process was observed. Microstructure of the work piece showed evidences of recrystallization under the experiment conditions. It is estimated that in specific punch speed region fast stroke accelerates recrystllization and reduces the forming load.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.36 no.7
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• pp.658-665
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• 2008

In this study a practical guidance law for missile guidance loop is established by considering the missile dynamics. Assuming the attitude controlled missile, several optimal guidance laws according to missile dynamical characteristics are derived by applying the optimal control theory and an effective guidance law in practical point is presented.

• Proceedings of the Korea Information Processing Society Conference
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• 2016.10a
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• pp.433-435
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• 2016

기술의 발전에 따라 첨단무기체계인 군용항공기는 전투임무 수행시 내장형소프트웨어(Embedded Software)를 통해 기체내의 항공전자 장치, 항법장치, 조종장치 등의 물리적 기계적 움직임을 제어하고 있으며, 내장형 소프트웨어의 비율은 점점 증가하고 있다. 기체의 물리적 기계적 움직임이 내장형 소프트웨어에 의해 제어 되기 때문에 군용항공기의 전투능력 보존과 국방 목적의 수행을 위해선 먼저 내장형 소프트웨어 고유의 특성을 만족하고, 나아가 소프트웨어 안전성, 신뢰성, 보안성을 확보하는 것이 필요하다. 본 논문에서는 설계 단계에서 스케줄성에 대해 정형검증 하여, 내장형 소프트웨어의 실시간성, 결정성, 생존성을 보증하고, 이러한 과정을 통해 전체적인 소프트웨어 안전성, 신뢰성, 보안성을 향상시키는 방안을 연구하며, 추가로 2011년 발표된 항공 소프트웨어 표준인 DO-178C에서 요구하는 정형검증을 적용한 국내 감항인증 표준 제정의 확대방안을 연구한다.

• Proceedings of the Korean Institute of Electrical and Electronic Material Engineers Conference
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• 2001.11b
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• pp.517-520
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• 2001

The optical properties of $TiO_2$ thin films dispersed in epoxy film, which were prepared with bis-(4, 4'-P-toluenesulfonylacidic isoproplyidene) cycolhexadiol(BTSPC) and UVI 6990 in dry sol-gel process, were investigated. In the case of irradiating UV light on $TiO_2$ thin films, how many nanopartlcles of $TiO_2$ are dispersed in epoxy film was investigated by AFM. The absorption peak of the films was showed at 360nm. Squarylium dye was dispersed in $TiO_2$-epoxy film. Photodegration concerned with amount of dye and time of UV light irradiation was investigated. UV light irradiation on the film occurred dramatical photodegration.

• 유체기계공업학회:학술대회논문집
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• 2005.12a
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• pp.324-330
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• 2005

For axial-type turbines which operate at partial admission, a performance prediction model is developed. In this study, losses generated within the turbine are classified to windage loss, expansion loss and mixing loss. The developed loss model is compared with experimental results. Particularly, if a turbine operates at a very low partial admission rate, a circular-type nozzle is more efficient than a rectangular-type nozzle. For this case, a performance prediction model is developed and an experiment is conducted with the circular-type nozzle. The predicted result is compared with the measured performance, and the developed model quite well agrees with the experimental results. So the developed model could be applied to predict the performance of axial-type turbines which operate at various partial admission rates or with different nozzle shape.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2011.10a
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• pp.475-479
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• 2011

Leak problem with large pressure drop occurrs non-periodic shock pulsation due to the deterioration of a isolation valve in feed-water recirculation piping system. This paper discusses on the shock vibration and noise occurred due to the effect of acoustical shock pulsations by degradation of the isolation valve in a power site.

• Proceedings of the Korean Society for Noise and Vibration Engineering Conference
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• 2002.05a
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• pp.848-854
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• 2002

The nonlinear characteristics for the hinge of a deployable missile control fin are investigated experimentally. The nonlinearity is caused by a worn or loose hinge and manufacturing tolerance and cannot be eliminated completely. The structural nonlinearity has an effect on the static and dynamic characteristics of the control fin. Therefore, it is necessary to establish the accurate nonlinear model for the hinge of the control fin. In the present study the existence of nonlinearities in the hinge is confirmed from the frequency response experiments such as tip random excitation and base sine sweep. Using the system identification method, especially, “Force-State Mapping Technique”, the types of nonlinearities are identified and the nonlinear hinge model of the control fin is established.

• Transactions of the Korean Society of Automotive Engineers
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• v.7 no.5
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• pp.186-193
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• 1999

In this paper, a full vehicle model is developed to analyze toe and camber changes due to rack height variation and compliance. The AutoDyn7 program developed in G7 project is used for the computer simulation. Steady state cornering test was done to find the understeer gradient. Imposing a pulse steer input, Frequency Response Function(FRF) of yaw rate and lateral accelerations were evaluated. To verify the stability, the rhombus using four parameters is employed. Steer characteristics were evaluated by changing the rack height and the bushing lateral stiffiness. which installed between the low control arm and the chassis.