• Journal of the Korean Society for Aeronautical & Space Sciences
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• v.50 no.6
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• pp.377-384
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• 2022

In the design of composite aircraft structures, it is very important to set material allowables and design values, which take into account certification. And when determining the material allowable and design value of composite structures, the static strength, damage tolerance requirements, and environmental effects should be considered. The building block approach has been applied to the civil and military aviation industry for a long time and provides the principal certification methodology. This current certification methodology is based on extensive testing including coupon, element, sub-component, and full scale test. In this paper, some examples of composite allowable tests have been presented and the fundamental background and application methods of the building block approach have been presented.

• Journal of Aerospace System Engineering
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• v.11 no.4
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• pp.1-7
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• 2017

The development of effective design allowable values for unmanned composite aircraft is an issue of paramount concern for the industry. The application of conventional manned aircraft structural certification methods to unmanned aircraft such as prototype and technology demonstrators, can lead to excessively long development time and costs. In this paper, the determining method of composite structure design allowable values for light composite unmanned aircraft is presented to reduce to the structural weight. This paper seeks to show the applicability of composite B-basis material values as a design allowable of light composite unmanned aircraft structures. A review of different civil and UAV targets failure probability is given. From the results, the researchers can know that the requirements of light composite unmanned aircraft design allowable should be alleviated, compared to manned composite aircrafts.

• 한국항공운항학회:학술대회논문집
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• 2015.11a
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• pp.272-276
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• 2015

원재료 성분, 프리프레그 제작공정, 재료 취급, 부품 제작 기술, 적층순서, 환경조건, 그리고 시험방법 등 여러 요인으로 인해 복합재 물성치는 일반적으로 금속재에 비해 변동성이 높다. 따라서, 이러한 높은 변동성을 고려하기 위해서는 엄격한 통계분석기법을 적용하여 복합재의 기계적 물성에 대한 설계 허용치를 계산해야 한다. 1990년대 후반 미국에서는 FAA와 NASA를 중심으로 표준화된 절차에 따라 항공기 설계에 적용가능한 복합재 물성 데이터베이스를 구축하고 공유하기 위한 프로세스를 개발하기 시작하였고, 현재 NCAMP를 중심으로 복합재 데이터베이스 구축 작업이 진행되고 있다. NCAMP는 기본적으로 CMH-17에서 채택한 통계분석기법을 이용하여 허용치를 계산하고 있으며, 본 논문에서는 복합재 허용치 계산 기법 중 점추정 방법을 이용한 통계분석 기법과 그 적용에 대해 논하고자 한다.

• Proceedings of the Korean Society of Computer Information Conference
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• 2015.01a
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• pp.289-290
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• 2015

본 연구에서는 인쇄회로기판(PCB)용 재료로 널리 사용되는 고분자에 대해서 와이블 분포 방정식의 시뮬레이션을 수행하여 절연 신뢰도 특성 데이터를 분석하였다. 와이블 분포에 대한 분석 시뮬레이션을 통하여 일반적으로 허용 절연 파괴 확률을 0.1[%] 이하라고 설정하였을 때, 첨가제 배합비를 5종으로 구분한 각 시편에 대해서 인가 전계의 허용치를 각각 계산할 수 있었다.

• Proceedings of the Korean Society For Composite Materials Conference
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• 2004.04a
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• pp.258-261
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• 2004

This paper contains the tension-tension, the tension-tension bearing and the tension-tension steel bolt joint fatigue characteristics of glass fabric/phenol composite laminates. The experimental results show that the bearing and the steel bolt joint fatigue characteristics of the material is so excellent compared with the simple tension fatigue characteristics, that there are no needs of additional strengthening for mechanical joint parts when the parts are properly designed.

• Proceedings of the KAIS Fall Conference
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• 2008.05a
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• pp.46-48
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• 2008

나노복합 블레이드가 반도체 웨이퍼 가공을 위한 마이크로급 나노장치나 그 이상의 나노급 구조체를 위해 사용되었다. 금속 블레이드는 실리콘 웨이퍼 가공을 위해 사용되어 왔다. 그러나, 최근 레진 복합 블레이드는 반도체나 핸드폰의 쿼츠 웨이퍼 가공에 사용된다. 유기 또는 비유기 재료 선정은 기계가공성, 전기 전도성, 강도, 연성 및 웨이퍼 저항을 가진 블레이드를 만드는데 중요하다. 고성능 응용의 증대 요구에 따라 개발된 고기술 비유기성 재료의 혼합은 낮은 가격에 고기능의 신뢰도를 필요로 한다. 나노 입자의 크기를 가진 레진 복합물의 마이크로 설계는 입자간 상호작용의 제어가 필요하다. 형상 제작 동안 마이크로 차원에 두께를 유지하기 위해서는 마이크로/나노급 제작을 위한 가공기술이 중요한 것 중의 하나이다. 본 연구에서는 핫 프레스 구조물이 원래 설계 기준과 두께 차이의 실험 접근법을 사용해 만들어졌다. 다른 습식 공정 기술은 차원의 허용치를 개선하기 위해 만들었다. 실험들과 해석들은 신뢰성 결과가 사용가능함을 보여주었다. 반도체 시장에 사용될 레진 복합 블레이드의 개선 효과가 논의되었다.

• Composites Research
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• v.16 no.2
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• pp.33-40
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• 2003

In order to overcome one of the most pronounced shortcomings of conventional laminated composites, such as the low damage tolerance due to delamination, the thermoplastic materials and 3D (three-dimensional) preforms have been utilized in the manufacture of composite materials. From the newly developed process termed as the co-braiding, hybrid yarns of the thermoplastic fibers (PEEK) and reinforcing fibers (carbon) have been fabricated. In order to further enhance the delamination suppression, through thickness fibers have been introduced by way of 3D weaving technique in the fabrication of textile preforms. The preforms have been thermoformed to make composite materials. Complete impregnation of the PEEK into the carbon fiber bundles has been confirmed. For the comparison of mechanical performance of 3D woven composites, quasi-isotropic laminates using APC-2/AS4 tapes have been fabricated. Tensile and compressive properties of both the composites have been determined. Furthermore. the open hole, impact and CAI(Compression After Impact) tests were also carried out to assess the applicability of 3D woven textile reinforced thermoplastic composites in aerospace structures.

• Journal of Aerospace System Engineering
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• v.16 no.3
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• pp.35-41
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• 2022

UAM (Urban Air Mobility) is a new safe, secure, and more sustainable air transportation system for passengers and cargo in urban environments. Commercial operations of UAM are expected to start in 2025. Since production rates of UAM are expected to be closer to cars than conventional aircraft, the airworthiness methodology for UAM must be prepared for mass production. Composite materials are expected to be mainly used for UAM structures to reduce weight. In this paper, the composite material qualification method was derived and the materials were applied for small aircraft application. It is expected to reduce the airworthiness certification time by applying composite material qualification system and its database.

• Proceedings of the Korean Institute of Surface Engineering Conference
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• 2013.05a
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• pp.117-118
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• 2013

증기발생기 화학세정 모사 장치를 이용하여 고농도 화학세정(EPRI/SGOG) 용액인 EDTA(20%)가 인위적으로 제작한 결합 시편에 미치는 영향 평가를 수행하였다. 평가 방법은 세정 전 후 표면 산화막 성분, ECT 분석값 비교, 증기발생기 구성 재료 부식률를 이용하였다. 화학세정 전후 부식률은 A508은 $8.023{\mu}m$, Alloy 600(HTMA)은 $0.007{\mu}m$이며 갈바닉 시편의 경우 $63.193{\mu}m$로 모두 부식 허용치 이내이다. 표면 산화막 성분 및 ECT 분석값 역시 변함이 없었다. 이와 같은 결과로 화학세정 용액인 EDTA는 결함 튜브에 미치는 영향이 없는 것으로 판단된다.

• Journal of dental hygiene science
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• v.12 no.2
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• pp.123-129
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• 2012

The aim of study was to compare the color parameters and mean color difference of porcelain specimens by different veneering technique in order to examine the effect of veneering technique on esthetics of yttria-stabilized tetragonal zirconia polycrystalline(Y-TZP) all ceramic restoration. Three groups of square-shaped core ceramic specimens(14mm in diameter and 0.3, 0.5, 0.7 mm) and two groups of veneering ceramic specimen were prepared for analysis. Color parameter($L^*,a^*,b^*$) and color difference of zirconia core squares and core-veneer specimens were measured with ShadeEye $NCC^{(R)}$ spectrophotometer, respectively. Mean color difference(${\Delta}E^*$)were calculated using color difference formula. Two-way analysis of variance(ANOVA) combined with a Tukey multiple-range test were used to analysis the data(${\alpha}=0.05$). ${\Delta}E^*$ values were not significantly affected by core thickness and veneering porcelain(p=0.083). The color differences(${\Delta}E^*$) of core-veneer specimens with 0.5, 0.7 mm-A1,A2,A3.5 shade were mostly below 3.7 which was within the clinically acceptable range, while color differences between 0.3 mm-A1,A2 showed more than 3.7. All-ceramic system has color characteristics that clinicians have to consider when selecting materials. Also, manufacturers of different porcelain systems must make every effort to achieve color reproducibility.