• Transactions of the Korean Society of Mechanical Engineers A
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• v.41 no.10
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• pp.959-965
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• 2017

In recent years, major airplane manufacturers have been using the laminate failure theory to estimate the strain of composite structures for airplanes. The laminate failure theory uses the failure strain of the laminate to analyze composite structures. This paper describes a procedure for the experimental assessment of laminate tensile failure characteristics. Regression analysis was used as the experimental assessment method. The regression analysis was performed with the response variable being the laminate failure strain and with the regressor variables being two-ply orientation ($0^{\circ}$ and ${\pm}45^{\circ}$) variables. The composite material in this study is a carbon/epoxy unidirectional (UD) tape that was cured as a pre-preg at $177^{\circ}C(350^{\circ}F)$. A total of 149 tension tests were conducted on specimens from 14 distinct laminates that were laid up at standard angle layers ($0^{\circ}$, $45^{\circ}$, $-45^{\circ}$, and $90^{\circ}$). The ASTM-D-3039 standard was used as the test method.

• Composites Research
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• v.34 no.5
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• pp.296-304
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• 2021

This study presented the evaluation of the stamp forming process for L-shape CF/PEKK thermoplastic composite using the finite element model. The formability of three different trimming allowances has been examined for representative product geometry. The results showed that those manufactured by high trimming allowance showed more excellent formability in those areas. Moreover, the effects of the trimming allowances on the stress, thickness, wrinkle distributions of thermoplastic composites fabricated with the stamp forming process were evaluated. The comparison of the simulation and experimental results for the thickness and wrinkle distributions proved the accuracy of the stamp forming model. The crystallinity of the composite was performed by differential scanning calorimetry (DSC). The void content of the composite was evaluated by matrix digestion. Then, the fabricated structure was characterized and achieved high quality in crystallinity and void content. Consequently, the presented FEM modeling shows excellent potential for application in the aircraft product design process. This pragmatic approach could efficiently offer a valuable solution for the thermoplastic composite manufacturing field.

• Journal of the Korean Crystal Growth and Crystal Technology
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• v.20 no.3
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• pp.133-140
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• 2010

Carbon fiber has many potential applications in a wide array of fields of solar cell, fuel cell, batteries, and polymer matrix composites due to an exceptional mechanical properties and chemical stability. In this study, the effects of catalysts on the property of carbon nanostructures grown on the carbon fiber were systematically investigated. The surface treatment of carbon fiber and catalysts synthesis for carbon nanostructures growth were carried out by one-pot ELP method and thermal CVD, respectively. The surface morphology and crystal structure of carbon nanostructures were examined using a field emission scanning electron microscope and transmission electron microscope. Depending on the type of catalysts and the molar ratio, various types of carbon nanostructures like carbon nanotube, carbon nanofilament, carbon nanospring and etc. were synthesized on the surface of carbon fibers surface.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.31 no.4
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• pp.44-52
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• 2003

Shape memory alloys (SMA) are often used in smart structures as active components. Their ability to provide large recovery forces and displacements has been useful in many applications, including devices for artificial muscles, active structural acoustic control, and shape control. Based on the 3-dimensional SMA constitutive equation in this paper, the radial displacement control of externally pressurized circular and semicircular composite cylinders under external pressure with a thin SMA layer bonded on its inner surface or inserted between composite layers in investigated using 3-dimensional finite element analysis. Upon actuation through resistive heating, SMAs start to transform from martensitic into austenitic state, simultaneously recover the prestrain, and thus cause the composite cylinders to go back to their original shapes of the cylinder cross-sections.

• Proceedings of the Korean Society of Dyers and Finishers Conference
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• 2012.03a
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• pp.17-17
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• 2012

수송용 섬유소재는 자동차, 항공기 또는 선박 등의 교통 및 운송 분야에 기여하는 사용되는 섬유소재를 말하며, 내장재, 각종 호스류, 벨트류, 타이어, 안전용품, 필터류 등을 포함하고 일반적으로 섬유, 발포체, 고무, 플라스틱, 접착제 등 유기소재가 결합된 복합체이다. 기존 섬유기술의 혁신과 더불어 IT, NT, BT, ET 등 첨단 기술과의 융합에 의한 고성능 극한 슈퍼섬유, 나노 복합섬유 등의 신소재를 개발하여 산업 전반에서 플라스틱의 금속소재 대체수요를 증가시키고 산업자재의 고성능화, 고기능화, 다양화를 이루기 위해 다양한 노력이 진행하고 있다. 현재 수송용 섬유소재 산업은 기술의 연결고리가 부족하며, 선도기업 및 원천기술이 부족하며, 자동차용 섬유부품소재 관련 기업의 역량도 부족한 실정이다. 이에 광역경제권 연계협력사업을 통해 생산기반의 대경권(대구경북)과 수요중심의 동남권(부산경남)의 네트워크를 강화하여 완성품 업체 및 수요기업과의 네트워킹을 강화하고자 한다. 따라서 본 연구에서 수송용 섬유소재개발, 수송용 친환경 oam-skin 일체형 표피재 개발, 고속성형 복합소재 및 수송용 경량부품 개발, 초경량 고내열 고강도 섬유활용 하이브리드 wire & cable 개발 등 수송용 섬유소재를 개발하고, 또한 수송용 섬유소재의 생산-수요 연계를 통한 투자활성화, 기술개발, 소재 산업 육성을 강화하여, 산학연네트워크구축, 지역 간 협력 및 국제적 협력, 생산-수요기반의 연계협력시스템을 활용한 자립형 수송용 소재 공급기지 완비하는 데 목적이 있다.

• Journal of the Korean Society of Propulsion Engineers
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• v.19 no.4
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• pp.94-101
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• 2015

Each of power systems of solar cell and fuel cell were configured and validated for long endurance UAV, as the preliminary research for the integration of power systems. Solar power system consisted of solar modules fabricated by solar cells of Sunpower's C60, commercial solar MPPT controller and Li-po battery, and then was validated. The re-start characteristics of hydrogen production from $NaBH_4$ hydrolysis was validated for operating the commercial fuel cell. The average voltage drop of Li-po battery in solar power system was -2.9 V/hour. The performance of re-start characteristics of $NaBH_4$ hydrolysis was stable in sequence mode of mission profile. Each of single systems were satisfied for the proposed mission profile.

• Journal of the Korea Convergence Society
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• v.9 no.6
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• pp.25-31
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• 2018

Captive Flight Test (CFT) is one of the most important tests to acquire data when developing complex weapon systems. In this paper, we introduce the design and test result of our POD system for CFT. POD system uses POD set which consists of left and right POD. The exterior and mass properties of POD set are equal to those of fuel tank for aircraft so that we can omit Airworthiness Certification. Also, we adequately placed inner-equipments in order to acquire data including target image, navigation result and reference data to verify and analyse software algorithm. The POD system for CFT we developed is complex system as both mechanical and electronic factors are applied. As we repeatedly performed CFT, useful and various data for weapon development were acquired.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.35 no.6
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• pp.629-633
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• 2011

Recently, systems such as aircraft, trains and ships have become larger more complex. Therefore, the reliability calculation of these systems is more difficult. This paper presents a reliability calculation algorithm for a complex system with a solution that is difficult to analyze. When the system has a very complex structure, it is very difficult to find an analytical solution. In this case, we can assess system reliability using the failure enumeration method of the reliability path. In this research, we represent the reliability block diagram by an adjacent matrix and define the reliability path. We can find any system status by the failure enumeration of the reliability path, and thus we can calculate any kind of system reliability through this process. This result can be applied to RCM (Reliability-Centered Maintenance) and reliability information-management systems, in which the system reliability is composed of the reliabilities of individual parts.

• Transactions of the Korean Society of Mechanical Engineers A
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• v.34 no.11
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• pp.1697-1703
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• 2010

Hydraulic hoses are used as pipelines for transferring power from hydraulic systems in various machineries such as construction equipments, automobiles, and aircraft. Hydraulic hoses protect the system from vibration or impacts, and they are being used to transfer energy in all segments of the industry. In order to protect the system from various external environmental conditions, hydraulic hose assemblies must be able to withstand a wide range of temperatures and pressures, as well as variations in other factors. In previous studies, an acceleration model for the hydraulic hose assembly was developed by taking into account only one of the acceleration factors (temperature or pressure). Therefore, the objective of this study is to develop a comprehensive acceleration model that takes both temperature and pressure into consideration.

• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.37 no.8
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• pp.751-758
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• 2009

Failure strengths of composite single-lap adhesive joints were investigated with various parameters such as manufacturing method, overlap length and adherend thickness. A total of 335 single-lap joint specimens were tested under tension. Specimens were fabricated with 4 different manufacturing processes; cocuring without and with adhesive, secondary bonding and co-bonding. Each manufacturing process has 5 different overlap lengths and 4 different thicknesses, respectively. As expected, failure strength is higher in thicker adherend joints and lower in larger overlap length specimens. Interesting result is that the secondary bonded joints show the higher strength than the cobonded and cocured joints with adhesive, and give close or even higher strength compared with non-adhesive cocured case.