• Title/Summary/Keyword: composite aircraft

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A Case Study for Improving the Manufacturing Process of Composite Main Wing for Small Aircraft (소형 항공기 주익 복합재료 적용 사례 분석을 통한 개선 방향 연구)

  • Cho, Il-Ryun
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.23 no.1
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    • pp.96-102
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    • 2015
  • Composite materials are widely used as structural materials for manufacturing an aircraft, due to their : low weight, low thermal expansion coefficient, production efficiency, anisotropy, corrosion resistance and long fatigue life. The range of using composite materials has been extended from the fuselage and the wings to the entire aircraft structure. In this paper, by analyzing the problems which were generated while designing and fabricating aircraft structures using composite materials, the differences between metallic structures and composite structures are described. In addition, the methodological improvement directions on design and fabricating are described.

Structural Health Monitoring Techniques for Composite Aircraft (복합재료 항공기의 구조진단 기술)

  • Choi, Heung-Soap;Cho, Youn-Ho
    • Journal of the Korean Society for Nondestructive Testing
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    • v.30 no.1
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    • pp.54-59
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    • 2010
  • After the advent of B787(Boeing Co.), a civil aircraft using composite materials more than 50% of it total structural weight for weight savings,best performances and efficiencies, various endeavors to develop and apply the state of art of structural health monitoring(SHM) technologies for composite aircraft have been made for many years. Despite their plentiful advantages composite aircraft structures are susceptible to the hidden or barely visible impact damages(BVID) and excessive loads that if unchecked may lead to lower structural integrity, loss of operational performance and finally a sudden catastrophic failure of the aircraft structure. In this paper background of SHM technology and relevant technologies for application of SHM technology to the composite aircraft in the near future and requirements for certification of SHM system are shortly presented.

Repair methods for aging aircraft and application of composite patch repair (노후항공기의 보수 방법 및 복합재 패치보수의 응용)

  • 김위대;김종진
    • Proceedings of the Korean Society For Composite Materials Conference
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    • 2002.05a
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    • pp.167-172
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    • 2002
  • During the operation of military aircraft, maintenance is divided into organizational, intermediate and depot maintenance. In the depot maintenance, after removal of major parts and removable doors, damage assessment is performed. Locating damage, charactering the damage and determining its extent, zoning the damage on the part being repaired and re-evaluation of the damaged area after damage removal. Repair joints are classified by bonded joints and bolted joints, depending on joining material. In this paper, repair method in aging aircraft is investigated and the possibility of application of copmposite patch is surveyed.

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Qualification of Composite Materials for Small Aircraft (소형 항공기용 복합재료 인증)

  • Suh, Jang-Won;Park, Jong-Hyuk;Lee, Jong-Hee
    • Journal of Aerospace System Engineering
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    • v.5 no.1
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    • pp.17-23
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    • 2011
  • Since the time, cost and lack of regulatory information and guidance, one of the largest regulatory obstacles for an airframe manufacturer of polymer based advanced composite materials in certified aircraft applications, is to generate design allowables that will satisfy Airworthiness Regulations. In the past two decades, the design allowables used in military aircraft had been generated and applied in Korea, however the qualification of composite materials used in certifying airframe structure was not accomplished for design and demonstration of compliance to applicable airworthiness regulation. It is the intend of this paper that provide the basis of composite material qualification for small aircraft certification to the airworthiness regulation.

Study for Determining Design Allowable Values of Light Weight Composite Unmanned Aircraft Structures (경량 복합재료 무인기 구조물 설계 허용치 설정 방안 연구)

  • Kim, Sung Joon;Park, Sang Wook;Kim, Tae Uk
    • 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.

Research on Aircraft Lightning Protection Design and Certification of Fuel System in Composite Material (복합재항공기 연료시스템의 낙뢰보호설계 및 인증 연구)

  • Lee, Young-jae;Cho, Wonil;Jeon, Jeonghwan;Koh, Jinhwan
    • Journal of the Korean Society for Aviation and Aeronautics
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    • v.25 no.4
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    • pp.130-140
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    • 2017
  • Lightning protective design of an aircraft fuel system is closely related to the safety of the flight. Recently, composite material in building an aircraft becomes more important because it can reduce the weight of the aircraft. The composite materials decrease the protection against the effect of lightning. Lightning protective design of metal material aircraft has been researched for a long time and the design technique has been announced widely. However, research on the lightning protective design using composite material aircraft is very limited. In this study, lightning protective design for fuel tank structural component, access cover, fuel filler cap and drain valve in carbon fiber composite material aircraft have been presented. To show the compliance with FAA airworthiness standard regarding the presented protection designs, three steps, including lightning strike analysis, lightning environment analysis and certification test, were conducted in accordance with FAA AC 20-53.

A Study on Technical Trends of Composite Materials for Small Aircraft (소형 항공기용 복합재료의 기술동향에 관한 연구)

  • Lee, Jong-Won;Kim, Jin-Won;Kim, Pil-Jong;Park, Ill-Kyung
    • Proceedings of the Korean Society For Composite Materials Conference
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    • 2005.04a
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    • pp.231-234
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    • 2005
  • The present study provides the legislative backgrounds and contents of the America's General Aviation Revitalization Act of 1994 as well as the general impacts of the Advanced General Aviation Transport Experiments Program on the composite materials and associated general aviation aircraft structures

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Investigation on Damage Tolerance of Thick Laminate for Aircraft Composite Structure (항공기 복합재 구조에 적용된 두꺼운 적층판의 손상 허용 기준 평가)

  • Park, Hyun-Bum;Kong, Chang-Duk;Shin, Chul-Jin
    • Composites Research
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    • v.25 no.4
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    • pp.105-109
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    • 2012
  • Recently, development of a small aircraft has been carried out for the BASA(Bilateral Aviation Safety Agreement) program in Korea. This aircraft adopted all composite structures for environmental friendly by low fuel consumption due to its lightness behavior. However the composite structure has disadvantage which is very weak against impact damages. Therefore, damage allowable design of aircraft structure must be performed considering compressive fracture strength. This point is very important for certification of composite structure aircraft. In this paper, it is performed the research on damage tolerance of thick laminate adopting aircraft structure. The damage tolerance of three different types of thick laminates such as no damage, open hole and impact damage is evaluated under compression loading.

A Study on the Pilot Qualification and Qualification System Establishment of The Aerospace Composite Materials

  • Yong Man Yang;Sung In Cho;Seok Ho Jeong;Je-Jun Kim;Manseok Oh;Young Hwan Kim
    • International Journal of Aerospace System Engineering
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    • v.10 no.1
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    • pp.14-24
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    • 2023
  • The materials applied to the aircraft fuselage, parts, and components must be verified by relative authorities in accordance with the procedures set by the airworthiness authority to achieve the aircraft type certification. There are no examples of domestic composite materials which were verified in order to be applied to aircraft structure. In this study, the composite material certification system of NCAMP, an American composite material standard certification organization, was reviewed and used as the fundamentals of the first aerospace composite material certification system in ROK(Fig 2,8). Also updated material certification documents were developed and confirmed by material certification engineers and inspectors. This aerospace composite material qualification system is intended to modernize the material certification system for AAM(Advanced Air Mobility) as well as aircraft and to enhance the understanding of related technicians and inspectors.

Structural Modelling of Tapered Composite Aircraft Wings with Initial Angle of Attack using Thin-Walled Beam (얇은 벽 보를 이용한 초기 받음각이 있는 테이퍼형 복합재료 항공기 날개의 구조 모델링)

  • Kim, Keun-Taek;Song, Ohseop
    • Journal of Aerospace System Engineering
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    • v.3 no.2
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    • pp.1-11
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    • 2009
  • A structural modelling for study on dynamic characteristics of tapered composite aircraft wings in the form of thin-walled beam is presented. The proposed structural model includes effects of transverse shear flexibility exhibited by the advanced composite materials and warping restraint characterizing elastic anisotropy and induced structural couplings. The complex effects of these factors could have a role in more efficient analysis on those structural models.

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