• 한국항공우주학회지
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• 제32권8호
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• pp.101-108
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• 2004

본 연구에서는 비행체 구조재료인 A12024-T3에 대하여 공력가열환경을 모사할 수 있는 복사가열기를 제작하였으며 $1^{\circ}C/sec{\sim}30^{\circ}C/sec$ 가열률 범위에서 열기계적 인장특성을 평가하였다. 가열환경에 따른 재료강도 평가를 위하여 급속가열 인장시험 결과와 일정 온도로 30분 노출후의 인장시험결과를 항복응력 측면에서 비교 고찰하였다. 급속가열 인장시험 결과로부터 시간-온도계수를 응용한 가열률-항복온도 계수를 도출하였으며, 항복응력을 가열률과 항복온도로 표현되는 실험적 master 수식을 제안하였다. 본 연구 결과를 통하여 획득 된 급속가열 안장시험결과들은 초음속 비행체 설계시 선정재료의 안전여유를 판단하는 기초자료로 활용될 수 있다.

• 한국해양공학회지
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• 제11권3호
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• pp.69-75
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• 1997

A A12024-T3 plate has been reinforced with AFRP to be a Hybrid-Composite, APAL. The fatigue life of the APAL has been investigated. The effects of bonding surface, numbers of AFRP bonded and AFRP orientation on fatigue life have been compared with A12024-T3 plate. Fatigue life of APAL has been remarkedly increased compared with that of A12024-T3 plate. The fatigue life has depended on bonding surface and AFRP orientation, but no relationship could be found with numbers of AFRP laminates.

• 대한기계학회논문집A
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• 제21권3호
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• pp.511-518
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• 1997

The technique of fretting fatigue test was developed and fretting fatigue tests of A12024-T4 were conducted under several conditions. The newly developed calibration methods for measuring surface contact tractions showed good linearity and repeatability. The plate type specimen to which tow bridge type pads were attached and vision system was used to observe the crack behaviour. The oblieque cracks appeared in the early stage of crack growth and they became mode I cracks as they grow about 1 mm. The mode I transition points were found to be longer when surface tractions are higher or bulk stress is lower. Before the crack becomes mode I crack, 'well point' where crack grow about rate is minimum, was detected under every experimental condition. The crack behaviour was found to be affected by surface tractions, contact area, bulk stress. It was also found that partial slip and stick condition is most detrimental and the crack starts from the boundary of stick and slip. For gross slip crack started at the outside edge of pad. After crack mode transition, fretting fatigue cracks showed almost same behaviour of plain mode I fatigue cracks. Equivalent stress intensity factor was used to analyze the behaviour of fretting fatigue cracks and it was found that stress intensity factors can be applied to fretting fatigue cracks.

• 대한기계학회논문집A
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• 제24권3호
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• pp.794-802
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• 2000

Since the examination of CTOD problem revealed that the discrepancy among CTOD's was a matte., of definition, the relationships among parameters based on different definitions have been studied Particularly, the relationship between $\sigma$BS R-curve based on BS 7448 and R-curve based on the recently introduced $\sigma$5 parameter was investigated in this research. For the comparison, compact tension specimens of used 1Cr-0.5Mo steel, heat treated 1Cr-0.5Mo steel to mimic the new one, A12024-T6, and A12024-T351 were prepared and tested. Consequently, the relationship between $\sigma$5 and $\sigma$BS R-curves for tested materials were established by shifting the rotational center which could determined by rotation factor and ligament size.

• 한국군사과학기술학회지
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• 제4권2호
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• pp.42-51
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• 2001

The effects of pre-indentation technique are presented for A12024-T3 Alclad alloy using as skin material for aircraft fuselage and wing. Indentations were applied to specimens to be placed on the presumed path of fatigue crack growth before fatigue tests. Tension-tension fatigue tests were conducted on the edge cracked specimens in the L-T orientation. Test results were analyzed to investigate the effectiveness of pre-indentation with the variation of specimen's thickness, position of indentation and applied maximum stress. Fatigue crack retardation by pre-indentation is well recognized in the various conditions.

• 한국정밀공학회지
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• 제20권3호
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• pp.165-171
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• 2003

In a structure, many components are fastened together using bolts, nuts and rivets through drilled holes. Not only do these fastened joints enable easy assembly and dismantling, they are also able to transfer as well as to distribute loads applied onto the structures. The major drawback of such connections, however, is that the fatigue life of the components is reduced by the presence of the hole since the stress concentration around the hole is increased. In addition, the hole drilling process itself may introduce defects or roughness at the surfaces of the hole that may cause further decrease in fatigue performance of the components. For applications where fatigue loadings are important, one way to compensate the decrease in fatigue life of the components is by introduction of beneficial compressive residual stress around the hole using cold working. The material used for this research were A12024-T351 and A17050-T7451 using the primary member of aircraft. We present, In this paper, the characteristics of coldworking by evaluation of the hole expansion ratio, residual stress distribution, and fatigue properties.

• Journal of Welding and Joining
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• 제12권4호
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• pp.117-126
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• 1994

APAL (Aramid Patched ALuminum alloy) was manufactured, which was a material that was consisting of a A12024-T3 aluminum alloy plate bonded to single-side of it with aramid/epoxy laminates. The aramid/epoxy laminates were bonded to it in condition of 1, 2 ply and fiber orientation of .+-.45, 0.deg./90.deg. Fatigue crack propagation tests were performed at stress ratio R-0.2, 0.5 with Al 2024-T3, APAL 45-1P, APAL 0/90-1P, APAL 45-2P, APAL 0/90-2P specimens to examine behavior of retardation in fatigue crack propagation. All the APAL specimens showed superior fatigue crack resistance. Number of cycle spended for crack to propagate from $a_{M}$=37 to $a_{M}$=65 mm in case of APAL 0/90-2P specimen was half that of Al 2024-T3 specimen. Fatigue crack propagation rate of APAL 0/90 specimens were retarded more compared to APAL 45 specimens and the amounts of retardation at R=0.5 were larger than that at R=0.2. It was found that the retardation in fatigue crack propagation was caused by intact fibers in the wake of crack.ack.

• 한국복합재료학회:학술대회논문집
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• 한국복합재료학회 2000년도 추계학술발표대회 논문집
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• pp.63-66
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• 2000

This research addresses study on thermal residual stress of a composite patch repair of the edge cracked aluminium panel of aging aircraft. Composite patch repair is an efficient and economical technique to improve the damage tolerance of cracked metallic structures. These are thermal residual stresses due to the mismatch of coefficient of thermal expansion, and these are affected by the curing cycle of patch specimen. In this study, three curing cycles were selected for F.E. analysis. This study features the effect on composite patch and aluminum by thermal residual stress during crack propagation in aluminum plate.

• 비파괴검사학회지
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• 제21권4호
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• pp.398-405
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• 2001

리벳이음은 응력집중 등에 의한 피로균열 발생 가능성이 높은 구조특성을 가지므로 구조물의 안전성 확보를 위하여 비파괴 평가 방법에 의하여 리벳홀 주위 균열에 대한 평가가 요구되고 있다. 유도 초음파의 일종인 Lamb파는 판형상의 구조물의 비파괴 평가에 적합하며, 신경회로망은 비파괴 평가 기술에서 결합의 크기 및 종류 인식에 관하여 가장 효율적인 기법으로 많은 연구자들에 의해 적용되어 왔다. 본 연구에서는 항공기의 스킨재료로 적용되는 A12024-T3판재에 대하여 유도초음파의 일종인 판파를 적용하여 리벳홀 주위 균열 신호를 검출하였으며, 또한 리벳홀 주위 균열의 크기 평가를 위하여 백프로퍼게이션 알고리즘을 적용한 신경회로망을 적용하였다. 이때, 초음파 트랜스듀서와 시험편 사이의 불균일 접촉에 의한 오차를 줄이기 위하여 초음파 파형에서 시간 및 주파수 성분의 특성을 추출하여 신경회로망에 적용하였다. 그리고 이들 판파신호에서 추출한 시간 및 주파수 성분의 특성은 균열 크기 결정에 유용하게 적용될 수 있음을 증명하였다.

• 대한기계학회논문집
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• 제14권6호
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• pp.1561-1567
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• 1990

본 연구에서는 고강도 알루미늄합금 A12024-T3재의 통계적시험에 의하여 시험 편두께가 피로크랙 진전속도의 분포에 미치는 영향을 밝히고자 하며, 또한, 통계적시 험의 능률화 및 일관성을 꾀하기 위하여 개발한 새로운 유형의 자동화 다단식 피로시 험기의 개략을 밝힌다.