• 제목/요약/키워드: aircraft defect

검색결과 62건 처리시간 0.029초

항공재료 리벳홀에 인접한 원공결함의 위치에 따른 응력집중계수의 변화와 균열발생거동 (The Variation of Stress Concentration Factor and Crack Initiation Behavior on the Hole Defects Around the Rivet Hole in a Aircraft Materials)

  • 송삼홍;김철웅;김태수;황진우
    • 대한기계학회:학술대회논문집
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    • 대한기계학회 2003년도 춘계학술대회
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    • pp.381-388
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    • 2003
  • The material deficiencies in the form of pre-existing defects can initiated cracks and fractures. The stress distribution and fatigue crack initiation life of engineering materials may be associated with the size, the shape and the relative location of defects contained in the component. The objective of this study is to investigate the effect of arbitrarily located hole defect around the rivet hole of a wing section in monolithic aluminum and Al/GFRP laminates under cyclic bending moment during a service load. The stress distribution and the fatigue crack initiation behavior near a rivet hole of on the relationships between stress concentration factor ($K_t$) and relative position of defects were considered. The test results indicated the features of different stress field. Therefore, the stress concentration factor ($K_t$) and the fatigue crack initiation behavior was illustrated different behavior according to each position of hole defect around the rivet hole in monolithic aluminum and Al/GFRP laminates.

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Support Vector Machine과 인공신경망을 이용한 가스터빈 엔진의 결함 진단에 관한 연구 (Defect Diagnostics of Gas Turbine Engine Using Support Vector Machine and Artificial Neural Network)

  • 박준철;노태성;최동환;이창호
    • 한국추진공학회지
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    • 제10권2호
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    • pp.102-109
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    • 2006
  • 본 논문에서 항공기용 터보 축 엔진의 결함 진단 알고리즘을 개발하기 위해 Support Vector Machine(SVM)과 인공신경망(ANN)을 이용하였다. 신경망을 이용한 시스템은 비선형성이 과도한 데이터를 학습할 때 지역 최소점(Local Minima)에 빠져 분류 정확률이 낮아질 수 있다. 이러한 위험성을 보안하기 위해 SVM에 의한 ANN의 분할 학습 알고리즘(SLA)을 제안하였다. 이것은 SVM을 이용하여 결함 위치를 판별 한 후 신경망이 선택적으로 학습을 하는 방법으로 학습 데이터의 비선형성을 줄여 분류 정확률을 높이기 때문에 신경망을 단독으로 사용할 때보다 개선된 성능을 보여주었다.

원공노치 인근에 발생한 결함의 위치변화가 균열성장률(da/dN) 및 응력확대계수범위(δK)의 관계에 미치는 영향 - 단일재 알루미늄과 Al/GFRP 적층재의 피로거동 비교 - (The Effect of Defect Location Near a Circular Hole Notch on the Relationship Between Crack Growth Rate (da/dN) and Stress Intensity Factor Range (δK) - Comparative Studies of Fatigue Behavior in the Case of Monolithic Al Alloy vs. Al/GFRP Laminate -)

  • 김철웅;고영호;이건복
    • 대한기계학회논문집A
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    • 제31권3호
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    • pp.344-354
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    • 2007
  • The objective of this study is to investigate the effect of arbitrarily located defect around the circular hole in the aircraft structural material such as Al/GFRP laminates and monolithic Al alloy sheet under cyclic bending moment. The fatigue behavior of these materials may be different due to the defect location. Material flaws in the from of pre-existing defects can severely affect the fatigue crack initiation and propagation behavior. The aim of this study is to evaluate effects of relative location of defects around the circular hole in monolithic Al alloy and Al/GFRP laminates under cyclic bending moment. The fatigue behavior i.e., the stress concentration factor($K_t$), the crack initiation life($N_i$), the relationship between crack length(a) and cycles(N), the relationship between crack growth rate(da/dN) and stress intensity factor range(${\Dalta}K$) near a circular hole are considered. Especially, the defects location at ${\theta}_1=0^{\circ}\;and\;{\theta}_2=30^{\circ}$ was strongly effective in stress concentration factor($K_t$) and crack initiation life($N_i$). The test results indicated the features of different fatigue crack propagation behavior and the different growing delamination shape according to each location of defect around the circular hole in Al/GFRP laminates.

유전 알고리즘을 이용한 탈 설계 영역에서의 항공기용 가스터빈 엔진 결함 진단 (A Study on Defect Diagnostics of Gas-Turbine Engine on Off-Design Condition Using Genetic Algorithms)

  • 용민철;서동혁;최동환;노태성
    • 한국추진공학회:학술대회논문집
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    • 한국추진공학회 2007년도 제29회 추계학술대회논문집
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    • pp.350-353
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    • 2007
  • 본 연구에서는 항공기용 가스터빈 엔진의 운용에 있어 실시간 결함 진단을 위해 유전 알고리즘을 사용하였다. 탈 설계 영역에서 성능 저하를 고려한 가스터빈 엔진의 구성요소는 압축기, 가스발생기 터빈, 동력 터빈이다. 지상정지 상태인 설계점에 비해 고도, 비행 마하수, 연료유량에 대한 탈 설계 진단의 경우 학습 데이터는 약 200배 이상으로 증가하였으며, 요구 수렴도를 만족시키기 위해 방대한 학습시간이 요구된다. 탈 설계 영역에서 단일결함에 관한 진단오차를 만족시키고 학습시간을 단축시키기 위해 최적분할을 사용하였고 그 결과, 오차범위 5% 이내로 진단됨을 확인하였다.

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항공기 Bulkhead 체결구조의 균열 원인 및 개선에 관한 연구 (A Study on the Cause and Improvement of Crack in the Installing Structure of the Bulkhead of Aircraft)

  • 최형준;박성제
    • 한국산학기술학회논문지
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    • 제21권6호
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    • pp.448-454
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    • 2020
  • 본 연구는 항공기 운용 중 발생하는 구조결함의 원인을 규명하고 개선형상에 대한 구조 건전성을 확인하고자 한다. 항공기 균열은 Bulkhead 체결구조로서 연료탱크 경계 Web 파열로 인한 연료누유 현상에서 식별되었다. 균열의 특성을 확인하기 위해 파단면을 분석하였고 반복하중에 의해 균열이 진전되어 최종 파단으로 이어지는 피로파괴로 판단하였다. 또한 다중 시작점에서 균열이 시작되는 것으로 소재의 결함이 균열의 주요 원인으로 판단되지 않는다. 항공기 운용 중 발생하는 기동하중에 대한 균열 영향을 확인하기 위해 항공기 지상 및 비행시험을 통해 분석을 수행하였다. 항공기 운용 중 균열 부위의 하중 측정 데이터와 항공기 설계하중과의 비교를 통한 분석 결과 측정하중은 설계 대비 30% 수준으로 파손을 유발할 수준은 아니라고 판단하였다. 항공기 운용 시 진동하중의 원인으로 조립 및 단품 제작공차가 최대 0.06inch 발생할 수 있는 Gap을 검토하였고, 분석결과 균열부위에서 큰 응력인 약 32ksi가 발생하였다. 또한 Pre-Load에 의해 M.S.(Margin of Safety)가 +0.71에서 +0.34로 약 50%이상 감소되는 것으로 확인되어 항공기 설계 하중과 조합 시 균열 가능성이 급격히 증가하였다. 따라서 항공기 균열부위에 대하여 구조 보강 및 Gap 제거를 통해 결함을 개선하였다. 개선형상에 대하여 구조강도 해석 결과 Bulkhead는 허용응력 대비 M.S.가 약 +0.88이고 Fitting 형상은 약 +0.48로서 충분한 마진이 확보되었다. 또한 수명해석 결과 형상 개선 전 수명인 약3,600 시간 대비 개선형상은 약84,000 시간으로서 항공기 설계수명 대비 구조건전성을 확인하였다.

기판온도 및 열처리온도에 대한 CdS 박막의 전기적 및 광학적 특성 (Dependence of the Electrical and Optical Properties of CdS Thin Films on Substrate and Annealing Temperatures)

  • 박기철;심호섭;김정규
    • 센서학회지
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    • 제6권2호
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    • pp.163-171
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    • 1997
  • CSVT(close spaced vapor transport)증착시스템으로 태양전지의 창재에 적합한 CdS박막을 기판온도에 따라 증착하였으며, 실온에서 증착된 CdS박막을 온도를 변화시켜 가면서 열처리하였다. 증착 및 열처리후의 CdS박막의 구조적, 전기적 및 광학적 특성을 조사하였다. 증착조건에 무관하게 CdS박막들은 육방정계구조로 (002)면으로 기판에 수직으로 성장함을 확인하였다. 기판온도가 $25^{\circ}C$에서 $300^{\circ}C$까지 증가함에 따라 비저항은 $60{\Omega}cm$로 부터 $2{\times}10^{4}{\Omega}cm$로 단순증가하였으며 기판온도 $25^{\circ}C$에서 가시광영역에서의 광투과도가 80%정도로 가장 높았다. 열처리온도가 증가함에 따라 막내의 결정결함의 증가에 따라 비저항은 현저하게 증가하였으며 광투과도는 현저하게 감소하였다.

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항공기(航空機) 사고조사제도(事故調査制度)에 관한 연구(硏究) (A Study on the System of Aircraft Investigation)

  • 김두환
    • 항공우주정책ㆍ법학회지
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    • 제9권
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    • pp.85-143
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    • 1997
  • The main purpose of the investigation of an accident caused by aircraft is to be prevented the sudden and casual accidents caused by wilful misconduct and fault from pilots, air traffic controllers, hijack, trouble of engine and machinery of aircraft, turbulence during the bad weather, collision between birds and aircraft, near miss flight by aircrafts etc. It is not the purpose of this activity to apportion blame or liability for offender of aircraft accidents. Accidents to aircraft, especially those involving the general public and their property, are a matter of great concern to the aviation community. The system of international regulation exists to improve safety and minimize, as far as possible, the risk of accidents but when they do occur there is a web of systems and procedures to investigate and respond to them. I would like to trace the general line of regulation from an international source in the Chicago Convention of 1944. Article 26 of the Convention lays down the basic principle for the investigation of the aircraft accident. Where there has been an accident to an aircraft of a contracting state which occurs in the territory of another contracting state and which involves death or serious injury or indicates serious technical defect in the aircraft or air navigation facilities, the state in which the accident occurs must institute an inquiry into the circumstances of the accident. That inquiry will be in accordance, in so far as its law permits, with the procedure which may be recommended from time to time by the International Civil Aviation Organization ICAO). There are very general provisions but they state two essential principles: first, in certain circumstances there must be an investigation, and second, who is to be responsible for undertaking that investigation. The latter is an important point to establish otherwise there could be at least two states claiming jurisdiction on the inquiry. The Chicago Convention also provides that the state where the aircraft is registered is to be given the opportunity to appoint observers to be present at the inquiry and the state holding the inquiry must communicate the report and findings in the matter to that other state. It is worth noting that the Chicago Convention (Article 25) also makes provision for assisting aircraft in distress. Each contracting state undertakes to provide such measures of assistance to aircraft in distress in its territory as it may find practicable and to permit (subject to control by its own authorities) the owner of the aircraft or authorities of the state in which the aircraft is registered, to provide such measures of assistance as may be necessitated by circumstances. Significantly, the undertaking can only be given by contracting state but the duty to provide assistance is not limited to aircraft registered in another contracting state, but presumably any aircraft in distress in the territory of the contracting state. Finally, the Convention envisages further regulations (normally to be produced under the auspices of ICAO). In this case the Convention provides that each contracting state, when undertaking a search for missing aircraft, will collaborate in co-ordinated measures which may be recommended from time to time pursuant to the Convention. Since 1944 further international regulations relating to safety and investigation of accidents have been made, both pursuant to Chicago Convention and, in particular, through the vehicle of the ICAO which has, for example, set up an accident and reporting system. By requiring the reporting of certain accidents and incidents it is building up an information service for the benefit of member states. However, Chicago Convention provides that each contracting state undertakes collaborate in securing the highest practicable degree of uniformity in regulations, standards, procedures and organization in relation to aircraft, personnel, airways and auxiliary services in all matters in which such uniformity will facilitate and improve air navigation. To this end, ICAO is to adopt and amend from time to time, as may be necessary, international standards and recommended practices and procedures dealing with, among other things, aircraft in distress and investigation of accidents. Standards and Recommended Practices for Aircraft Accident Injuries were first adopted by the ICAO Council on 11 April 1951 pursuant to Article 37 of the Chicago Convention on International Civil Aviation and were designated as Annex 13 to the Convention. The Standards Recommended Practices were based on Recommendations of the Accident Investigation Division at its first Session in February 1946 which were further developed at the Second Session of the Division in February 1947. The 2nd Edition (1966), 3rd Edition, (1973), 4th Edition (1976), 5th Edition (1979), 6th Edition (1981), 7th Edition (1988), 8th Edition (1992) of the Annex 13 (Aircraft Accident and Incident Investigation) of the Chicago Convention was amended eight times by the ICAO Council since 1966. Annex 13 sets out in detail the international standards and recommended practices to be adopted by contracting states in dealing with a serious accident to an aircraft of a contracting state occurring in the territory of another contracting state, known as the state of occurrence. It provides, principally, that the state in which the aircraft is registered is to be given the opportunity to appoint an accredited representative to be present at the inquiry conducted by the state in which the serious aircraft accident occurs. Article 26 of the Chicago Convention does not indicate what the accredited representative is to do but Annex 13 amplifies his rights and duties. In particular, the accredited representative participates in the inquiry by visiting the scene of the accident, examining the wreckage, questioning witnesses, having full access to all relevant evidence, receiving copies of all pertinent documents and making submissions in respect of the various elements of the inquiry. The main shortcomings of the present system for aircraft accident investigation are that some contracting sates are not applying Annex 13 within its express terms, although they are contracting states. Further, and much more important in practice, there are many countries which apply the letter of Annex 13 in such a way as to sterilise its spirit. This appears to be due to a number of causes often found in combination. Firstly, the requirements of the local law and of the local procedures are interpreted and applied so as preclude a more efficient investigation under Annex 13 in favour of a legalistic and sterile interpretation of its terms. Sometimes this results from a distrust of the motives of persons and bodies wishing to participate or from commercial or related to matters of liability and bodies. These may be political, commercial or related to matters of liability and insurance. Secondly, there is said to be a conscious desire to conduct the investigation in some contracting states in such a way as to absolve from any possibility of blame the authorities or nationals, whether manufacturers, operators or air traffic controllers, of the country in which the inquiry is held. The EEC has also had an input into accidents and investigations. In particular, a directive was issued in December 1980 encouraging the uniformity of standards within the EEC by means of joint co-operation of accident investigation. The sharing of and assisting with technical facilities and information was considered an important means of achieving these goals. It has since been proposed that a European accident investigation committee should be set up by the EEC (Council Directive 80/1266 of 1 December 1980). After I would like to introduce the summary of the legislation examples and system for aircraft accidents investigation of the United States, the United Kingdom, Canada, Germany, The Netherlands, Sweden, Swiss, New Zealand and Japan, and I am going to mention the present system, regulations and aviation act for the aircraft accident investigation in Korea. Furthermore I would like to point out the shortcomings of the present system and regulations and aviation act for the aircraft accident investigation and then I will suggest my personal opinion on the new and dramatic innovation on the system for aircraft accident investigation in Korea. I propose that it is necessary and desirable for us to make a new legislation or to revise the existing aviation act in order to establish the standing and independent Committee of Aircraft Accident Investigation under the Korean Government.

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모바일 디바이스의 원인불명고장에 관한 비용 추정 (Mobile Device NDF(No Defect Found) Cost Estimation)

  • 이제왕;이정우;한창희
    • 산업경영시스템학회지
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    • 제44권2호
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    • pp.102-114
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    • 2021
  • NDF (No Defect Found) is a phenomenon in which defects have been found in the manufacturing, operation and use of a product or facility, but phenomenon of defects is not reproduced in the subsequent investigation system or the cause of the defects cannot be identified. Recently, with the development of the fourth industrial revolution, convergence of hardware and software technologies in various fields is spreading to products such as aircraft, home appliances, and mobile devices, and the number of parts is increasing due to functional convergence. The application of such convergence technologies and the increase in the number of parts are major factors that lead to an increase in NDF phenomena. NDF phenomena have a significant negative impact on cost, reliability, and reliability for both manufacturers, service providers and operators. On the other hand, due to the nature of NDF phenomena such as difficult and intermittent cause identification and ambiguity in judgment, it is common to underestimate the cost of NDF or fail to take appropriate countermeasures in corporate management. Therefore, in this paper, we propose a methodology for estimating NDF costs by the PAF model which is a quality cost analysis model and ABC (Activity Based Costing) technique. The methodology of this study suggests a detailed procedure and the concept to accurately estimate the NDF costs, using ABC analysis, accounting system information, and IT system data. In addition case studies have validated the methodology. We think this could be a valid methodology to refer to when estimating the cost of other parts. And, it is meaningful to provide important judgment information in the decision-making process based on quality management and ultimately reduce NDF costs by visualizing them separately by major variable factors.

An Acoustic Analysis of Noise Environments during Mobile Device Usage

  • Park, Hyung Woo
    • International journal of advanced smart convergence
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    • 제6권2호
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    • pp.16-23
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    • 2017
  • In contemporary modern society, people are constantly exposed to many kinds of noise, such as that from machinery, aircraft, construction sites, or road traffic. Noise is considered one of the most indispensable and influential parts of human life. This study investigates the acoustic characteristics of noise transfer from external sources to the human ear. For this study, we measured and analyzed various types of noise environments, installed monitoring speakers in a semi-anechoic room, and conducted intentional noise-filled experiments. In this environment, the size of the sounds generated by use of a portable device was also measured and the SNR (signal to noise ratio) calculated to study the influence of the noise. As sound is transmitted to the ear and the human body, it affects not only auditory damage but also other parts of the body. In this paper, we propose a proper SNR for noise emitted by portable IT equipment to prevent hearing loss when IT equipment is used.

T형 다조부품의 결함에 관한 연구 (A Study on the Defect of T type Forging Products)

  • 손경호;김영호;서윤수
    • 한국정밀공학회:학술대회논문집
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    • 한국정밀공학회 1997년도 춘계학술대회 논문집
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    • pp.952-956
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    • 1997
  • This paper describes the method that can expand the forming limit of T type forging products used in aircraft and automotive forged products. The forming limitis determined by the ratio of web thickness to rib width in T type and the reduction in height of workpiece and especially depends on the ratio of web thickness to rib width. For this method, the geometric condition that consists of triangle type was introduced and FEM simulations and model exoeriments were carried out and compared with each other. The objective of this paper is to give the method not only that sink mark and folding phenomenon are eliminated but also that the forming limit and the structural strength of rib and web is increased.

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