• Journal of Sensor Science and Technology
• /
• v.7 no.4
• /
• pp.285-292
• /
• 1998

Shape Memory Alloy(SMA) has been used in many engineering fields because of its good characteristics of actuator. For example, SMA wire can be embedded easily in the polymer composite laminate and then be used as actuator for structural control. Since the strain have a significant influence on the electrical resistance of SMA wire, It is a possible to use the SMA wire as a sensor of such physical quantities. In this study, the possibility for the application of Ni-Ti SMA wire as a sensor embedded within a composite laminate is investigated.

• The Journal of the Convergence on Culture Technology
• /
• v.9 no.5
• /
• pp.529-534
• /
• 2023

Although line printing technology is capable of high-speed and large area printing, residual stresses generated during the manufacturing process can deform the feedhole, causing nozzle plate crack or ink leaks. Therefore, in this paper, we propose a new thermal inkjet print head that is robust, reliable and more suitable for line-printing. The amount of deformation of the conventional line printing head measured through the experiment was converted into an equivalent load, and the validity of the load estimation method was verified through FEA analysis. In addition, in order to minimize deformation without increasing the head size, the head structure was designed to increase internal rigidity by reinforcing the unit nozzle with a pillar or support wall or by adding a support beam or dry/wet etched bridge. The FEA analysis results show that the feedhole deformation was reduced by up to 90%, and it is confirmed that the suggested print head with dry etched feedhole bridge operates normally without nozzle plate cracks and ink leakage through fabrication.

• Journal of Adhesion and Interface
• /
• v.9 no.3
• /
• pp.20-26
• /
• 2008

It is well know that the structure of shape memory alloy (SMA) can change from martensite austenite by either temperature or stress. Due to their inherent shape recovery properties, SMA fiber can be used such as for stress or cure-monitoring sensor or actuator, during applied stress or temperature. Incomplete superelasticity was observed as the stress hysteresis at stress-strain curve under cyclic loading test and temperature change. Superelasticity behavior was observed for the single-SMA fiber/epoxy composites under cyclic mechanical loading at stress-strain curve. SMA fiber or epoxy embedded SMA fiber composite exhibited the decreased interfacial properties due to the cyclic loading and thus reduced shape memory performance. Rigid epoxy and the changed interfacial adhesion between SMA fiber and epoxy by the surface treatment on SMA fiber exhibited similar incomplete superelastic trend. Epoxy embedded single SMA fiber exhibited the incomplete recovery during cure process by remaining residual heat and thus occurring residual stress in single SMA fiber/epoxy composite.

• Transactions of the Korean Society for Noise and Vibration Engineering
• /
• v.26 no.5
• /
• pp.584-593
• /
• 2016

In this study, an improvement design method for reducing the vibration of fenders equipped in a tractor is proposed through the establishment of a finite element model and the topology optimization. As the original shapes of the parts cannot be altered, an improved design model was derived in which a stiffener was attached to the border of parts. Thus, the first resonance frequency was increased by approximately 16 Hz, which was confirmed to be the frequency interval for avoiding the idle and operating frequency of the engine. Finally the improved design model was applied to confirm the effect of vibration reduction. Therefore, it can be concluded that the improved design model of the tractor fender is effective at reducing vibrations of the tractor fender.

• Bulletin of the Korean Space Science Society
• /
• 2009.10a
• /
• pp.32.5-33
• /
• 2009

카네기 천문대에서 주도하여 개발 중인 구경 25.4m GMT 망원경 사업에 한국도 공식적으로 참여하였다. 현재 한국천문연구원은 GMT(Giant Magellan Telescope)부경부를 국내에서 개발하고자 이와 관련된 연구를 진행하고 있다. GMT 부경은 직경 1.06m 오목거울 7장이 모여 전체 직경 3.2m인 타원면을 형성하고 초점비는 F/0.7이다. GMT 부경개발 선행 연구과제로 카네기 천문대에서 개발되어 현재 운용중인 구경 6.5m 마젤란 망원경의 부경을 선택하였는데, 이는 마젤란 부경의 형상과 직경, 부경시스템 운영방식이 GMT 와 유사하기 때문이다. 천체관측 망원경에서 거울면의 변형에 가장 큰 영향을 미치는 인자는 거울의 자중이다. 거울의 직경이 커지면 자중이 증가하게 되어 거울면의 처짐이 커지게 된다. 이를 극복하고자 다양한 거울 support들이 개발되었다. 그중에서 counterweight lever 시스템 같은 부양(float) 시스템은 자중의 영향을 보상해 줌으로써 그것에 의한 거울의 변형을 최소화하는 역할을 하는데, GMT 부경 개발에 근간이 되는 마젤란 부경 또한 부양 시스템을 도입하였다. 마젤란 부경의 부양시스템은 counterweight lever 시스템과 유사한 진공 시스템을 도입하였다. 마젤란 부경의 support는 axial 방향으로 거울을 지지하는 axial support와 lateral 방향으로 거울을 지지하는 lateral support가 있는데, 이중에서 axial support가 진공시스템으로 구성된다. Lateral 방향의 지지는 경량화된 거울의 hole 안에 3개의 판스프링을 삽입하여 단지 거울과 판스링의 강성에 의해서만 이루어진다. 이 논문에서는 망원경이 작동을 할때 즉, 천정각(zenith angle)이 변할 때 axial support와 lateral support의 조합(combination)에 의해 지지되는 마젤란 부경의 표면 정밀도 RMS 값을 비교하였다.

• Journal of the Korean Institute of Gas
• /
• v.7 no.3 s.20
• /
• pp.51-57
• /
• 2003

This paper presents the temperature distribution and deformation characteristics of O-ring groove geometry in which is strongly related the sealing performance of pressure vessels. A working gas in pressure vessel may be heated by a heater and pressurized by a gas compressor. Thus, the pressure vessel should keep high Pressure and temperature for a limited working period. For these operation conditions, the working gas in pressure vessels should not leak to the air by two O-rings with a rectangular groove. The FEM computed results indicate that the thermal and mechanical properties of metal sealing material is very important for stopping a leakage of hot gas in a vessel. Based on the results, high thermal conductive and low mechanical strength material is recommended as a metal sealing one. This may improve the sealing characteristics of O-ring sealing mechanism with a rectangular groove, which reduces the sealing gap between a flange and a cylinder and the width of O-ring groove.

• Journal of the Computational Structural Engineering Institute of Korea
• /
• v.27 no.6
• /
• pp.635-642
• /
• 2014

In this paper, an efficient technique is developed to predict failure probability of three failure modes(case rupture, fracture and bolt breakage) related to solid rocket motor case due to the inner pressure during the mission flight. The overall procedure consists of the steps: 1) design parameters affecting the case failure are identified and their uncertainties are modelled by probability distribution, 2) combustion analysis in the interior of the case is carried out to obtain maximum expected operating pressure(MEOP), 3) stress and other structural performances are evaluated by finite element analysis(FEA), and 4) failure probabilities are calculated for the above mentioned failure modes. Axi-symmetric assumption for FEA is employed for simplification while contact between bolted joint is accounted for. Efficient procedure is developed to evaluate failure probability which consists of finding first an Most Probable Failure Point(MPP) using First-Order Reliability Method(FORM), next making a response surface model around the MPP using Latin Hypercube Sampling(LHS), and finally calculating failure probability by employing Importance Sampling.