• 한국항공운항학회지
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• 제23권1호
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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.

• 한국국방경영분석학회지
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• 제30권2호
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• pp.108-121
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• 2004

This paper deals with a procedure of changing the current inspection & replacement periods for ROKAF aircraft parts. ROKAF is mostly operating aircraft of foreign makes, and takes maintenance actions according to Technical Orders(TO.) published by foreign aircraft manufacturers. Therefore ROKAF inspects and replaces specific parts at the time noticed from T.O.. These inspection and replacement periods are determined by manufacturers according to the standard operating environment and parts' durability. But the standard operating environment Is different from operator's environment. Because of this difference, the inspection and replacement periods have to be changed according to operators' operation environment. It is resonable that the manufacturer, having design materials and life test data of parts, changes those periods together with materials of operators' operation environment. But we have many difficulties in obtaining the design materials and life test data. Then this paper proposes a procedure of changing the periods of aircraft's parts with life data obtained during operating aircraft. For the reliability analysis, a software of RELEST (Reliability Estimation Version 1.0) is used.

• 한국주조공학회지
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• 제19권1호
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• pp.7-14
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• 1999

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2005년도 춘계학술발표대회 논문집
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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

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2002년도 춘계학술발표대회 논문집
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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.

• Composites Research
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• 제36권5호
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• pp.361-368
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• 2023

항공기에 사용되는 복합소재는 항공기의 감항성 확보를 위하여 인증된 소재를 사용해야 하며 소재의 물리적 특성 및 공정을 확인하여 재료규격 및 공정규격서등의 인증 문서와 시스템을 승인하는 방식으로 인증이 진행된다. 국내 복합소재 인증시스템은 국토교통부의 항공기용 복합재료 시범인증 사업을 통해 마련되었으며 현재 항공기 전문검사기관인 항공안전기술원에서 인증 및 공유 데이터시스템을 구축하여 운영하고 있다. 본 논문은 실증을 바탕으로 구축된 항공기용 복합소재 인증체계의 개선사항을 식별하고 이에 대한 개선 방안 도출을 통해 국산 항공기용 복합소재의 인증 및 산업 활성화 방안을 제시하였다.

• 항공우주시스템공학회지
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• 제5권1호
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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.

• 한국수소및신에너지학회논문집
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• 제10권1호
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• pp.49-57
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• 1999

In order to study the effect of high energy ball milling on the $Mg_2Ni+Ni$, $Mg_2Ni+0.5Ni+0.5Al$ powders, we have investigated on the discharge properties, microstructures. The powder size of samples decreased as ball milling time. From the XRD results, the crystal structure of $Mg_2Ni+Ni$ mixed powders were changed to amorphous or nano-structure after 60hr ball milling. The discharge capacities of both $Mg_2Ni+Ni$ and $Mg_2Ni+0.5Ni+0.5Al$ powders increased, with increasing ballmilling time, the maximum capacity(342mAh/g) was shown for the 60 hrs ballmilled $Mg_2Ni+Ni$ sample. The capacity decreased drastically after a few charge-discharge cycles.

• 비파괴검사학회지
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• 제29권6호
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• pp.525-533
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• 2009

Emphasis in the paper is placed on describing guided wave successes and challenges for applications in aircraft and composite materials inspection. Guided wave imaging methods discussed includes line of sight, tomography, guided wave C-scan, phased array, and ultrasonic vibration methods. Applications outlined encircles lap splice, bonded repair patch, fuselage corrosion, water loaded structures, delamination, and ice detection and de-icing of various structures.

• 한국수소및신에너지학회논문집
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• 제9권2호
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• pp.85-92
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• 1998

The hydrogenation behavior of $Mg_2Ni$ powder prepared by ball milling has been studied. Ball milled $Mg_2Ni$ was transformed to an amorphous-like state after 200hr ballmilling, and crystallized to $Mg_2NiH_x$ by hydrogenation at got. The hydrogen storage capacity gradually increased as a function of ball milling time. $Mg_2Ni$ by 400hr ballmilling shows higher hydrogen storage capacity (3H/M) than $Mg_2Ni$ by VIM(Vacuum Induction Melting).