• Composites Research
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• v.19 no.6
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• pp.1-7
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• 2006

This is the preliminary study to develop composite window frame of commercial aircraft using VaRTM process. For two candidate carbon fabrics(triaxial overbraid, sleeving braider), specimens were fabricated using VaRTM process, and the physical & mechanical property tests were performed to obtain the material properties according to ASTM. FEM analysis for each candidate carbon fabric was performed to find the minimum number of plies and weight for composite window frame to satisfy the design requirements. In this study, Tsai-Wu strength failure criterion was used to evaluate the safety of structure.

• Journal of Aerospace System Engineering
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• v.16 no.1
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• pp.81-85
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• 2022

In this study, we conducted a structural design and analysis of air intake of aircraft engine using composite materials. First, an investigation on structural design requirement of target structure was carried out. The distributed pressure load and acceleration condition was applied to structural design. To evaluate the structural design result, finite element analysis was carried out. The stress, deflection and buckling analysis for structural safety evaluation was performed. Finally, it was confirmed that the air intake through structural analysis is safety.

• Applied Chemistry for Engineering
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• v.27 no.3
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• pp.252-258
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• 2016

The weight reduction and improved mechanical property are one of the prime factors to develop new materials for the aerospace industry. Composite materials have thus become the most attractive candidate for aircraft and other means of transportations due to their excellent property and light weight. In particular, fiber reinforced polymer (FRP) composite materials have been used as an alternative to metals in the aircraft. The composite materials have shown improved properties compared to those of metal and polymeric materials, which made the composites being used as the skin structure of the airplane. This review introduces different types of materials which have been developed from the FRP composite material and also one of the most advantageous ways to employ the composites in aircraft.

• Journal of Aerospace System Engineering
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• v.14 no.spc
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• pp.22-30
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• 2020

Composite rotor blades for rotorcraft have an intrinsic vulnerability to foreign object impact from its inherent structural characteristics of insufficient strength in the thickness direction, which may easily lead to internal structure damage. Therefore, defects and strength reducing effects caused by foreign object impact should be considered in fatigue evaluation of composite blades. For this purpose, the flaw tolerant safe-life and fail-safe concepts were adopted in fatigue evaluation since 1980s, and recently those concepts have been replaced by the damage tolerance concept. In this paper, the relevant standards for fatigue evaluation are analyzed focusing on fiber reinforced composite rotor blades used in rotorcraft. In addition, fatigue evaluation procedure of composite blades considering impact damages is proposed by reviewing the practices implemented through domestic development projects.

• Composites Research
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• v.23 no.6
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• pp.1-6
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• 2010

The electrical conductivity of carbon-fiber reinforced plastics (CFRP's) has been improved by indium-tin oxide (ITO) nano-particle coating on carbon fibers for the purpose of lightning strike protection of composite fuselage skins. ITO nano-particles were coated on the surface of carbon fibers by spraying the colloidal suspension with 10~40% ITO content. The electrical conductivity of the CFRP has been increased more than three times after ITO coating, comparable to or higher than that of B-787 composite fuselage skins with metal wire-meshes on the outer surface, without sacrificing the tensile property due to the existence of nano-particles at fiber-matrix interface. The damage area by the simulated lightning strike was also verified for different materials and conditions by using ultrasonic C-scan image. As the electrical conductivity of 40% nano-ITO coated sample surpass that of the B-787 sample, the damage area by lightning strike also appeared comparable to that of the materials currently employed for composite fuselage construction.

• Aerospace Engineering and Technology
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• v.6 no.2
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• pp.35-39
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• 2007

In this paper, we have presented structural analysis procedure and full scale test results for 4-seater canard airplane. Construction of the finite element model is critical path for the aircraft structural analysis and directly affects the structural integrity. The refinement of the finite element model should be determined depending on full scale test results. From the results of the structural analysis, 5 design limit loads test conditions and 11 design ultimate loads test conditions were selected. By the presented procedure, the structural integrity of 4-Seater Canard Airplane is successfully obtained.

• Proceedings of the Korean Society of Propulsion Engineers Conference
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• 1999.04a
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• pp.30-30
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• 1999

샌드위치 복합재는 단일 부재의 금속재나 복합재에 비해 높은 비강성과 비강도를 얻을 수 있을 뿐 아니라 면재와 코아를 적절하게 조합하면 우수한 피로특성, 단열성, 흡음성 등을 얻을 수 있기 때문에 항공기, 철도차량, 선박, 냉동컨테이너, 건축재 등에 널리 활용되고 있다. 대부분의 샌드위치 복합재는 면재와 코아를 일차 또는 이차 선착을 통해 제작하기 때문에 운용 중 샌드위치 복합재에 가해질 수 있는 충격하중 등으로 인해 면재와 코아 사이의 층간분리, 면재의 인장파괴, 코아의 압축파괴, 코아의 진단파괴 등과 같은 손상이 생길 우려가 있다. 최근에는 샌드위치 복합재가 갖는 이러한 문제점들을 해결하기 위한 방편으로 코아의 양면에 부착된 면재들을 코아의 두께방향으로 스티칭함으로써 서로 일체형으로 결합시킨 형태인 스티칭된 샌드위치 복합재의 개발이 시도되고 있다.

• Journal of the Korean Society for Nondestructive Testing
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• v.34 no.2
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• pp.155-164
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• 2014

Carbon-fiber-reinforced plastic (CFRP) composites are increasingly being used in a variety of industry applications, such as aircraft, automobiles, and ships because of their high specific stiffness and high specific strength. Aircraft are exposed to high temperatures and high humidity for a long duration during flights. CFRP materials of the aircraft can absorb water, which could decrease the adhesion strength of these materials and cause their volumes to change with variation in internal stress. Therefore, it is necessary to estimate the characteristics of CFRP composites under actual conditions from the viewpoint of aircraft safety. In this study air-coupled ultrasonic testing (ACUT) was applied to the evaluation of water absorption properties of CFRP composites. CFRP specimens were fabricated and immersed in distilled water at $75^{\circ}C$ for 30, 60, and 120 days, after which their ultrasonic images were obtained by ACUT. The water absorption properties were determined by quantitatively analyzing the changes in ultrasonic signals. Further, shear strength was applied to the specimens to verify the changes in their mechanical properties for water absorption.

• 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.

• Journal of the Korean Society of Propulsion Engineers
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• v.11 no.6
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• pp.26-34
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• 2007

The efforts to develop high performance aircraft engines are successively progressed with development of recent technology. The reliability of individual parts and the safety of engine systems are reduced if high efficiency components, high strength materials, and precise controls are applied to the engine with complexity to increase engine performance. In this paper, the regulation requirements and assessment technique for aircraft engine safety are considered, and the result of safety assessment on a turbine case cooling system of high efficiency turbofan engine is presented.