Fiber metal laminates: An advanced material for future aircraft

Asundi, Anand Krishna; Choi, Alta Y.N.

doi:10.1016/s0924-0136(96)02652-0

Cited by 319 publications

(180 citation statements)

References 1 publication

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“…Cracks can exist in a component and it can remain safe and useable as long as the crack does not grow to a critical size. The study of fracture mechanics and its importance led to the incorporation of damage tolerance into aerospace design philosophy by the U.S. Air Force in 1974, followed by the Federal Aviation Administration (FAA) and Federal Airworthiness Regulations (FAR) in 1978 [6]. Consequently, soon after the Air Force selected it as its mainline advanced fighter in 1975, the F-16 became the first airplane designed according to damage tolerance specifications and is still flying today in the U.S. and 18 other nations around the world [7].…”

Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Rhymer

2002

International Journal of Fatigue

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Public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Washington Headquarters Services, Directorate for Information Operations and Reports, 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302, and to the Office of Management and Budget, Paperwork Reduction Project (0704-0188), Washington, DC 20503. AGENCY USE ONLY (Leave blank)2. REPORT DATE 24.Jan.00 REPORT TYPE AND DATES COVERED THESIS TITLE AND SUBTITLE FATIGUE DAMAGE MECHANISMS OF ADVANCED HYBRID TITANIUM COMPOSITE LAMINATES AUTHOR(S)CAPT RHYMER DONALD W PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)GEORGIA INSTITUTE OF TECHNOLOGY Comparing the number of cycles between the initial titanium ply damage and specimen failure showed a significant improvement (one order of magnitude for high cycle fatigue) in advanced HTCL due to interface strengthening. The damage progression following the initial ply damage (not performed on initial HTCL) demonstrated the effect of the strengthened PMC/titanium interface. Using acetate film replication of the specimen edges once titanium damage was evident, the advanced HTCL showed a propensity for some fibers in the adjacent PMC layers to fail at the point of titanium crack formation, suppressing delamination at the Ti/PMC interface. Following titanium ply cracking, these fibers would break and either a Mode I/Mode II (for outer ply damage) or Mode II (for inner ply damage) loading condition resulted in damage propagating longitudinally between the PMC fibers, rather then at the interface. The inspection of failure surfaces validated these findings, revealing PMC fibers to remain bonded to the majority of the titanium surfaces. SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)THETension compression fatigue (R = -0.2) was performed on both advanced and initial HTCL in this investigation and the strengthened interface was found superior in damage tolerance. Even though the fatigue lives were decreased for both HTCL constructions, the advanced HTCL endured a far greater number of cycles-to-failure following the initial titanium ply crack than initial HTCL at the same stress level due to resistance to delamination. Failure surfaces revealed a substantial amount of fibers xiv bonded to the titanium in advanced HTCL, while the initial laminate had few if any PMC fibers bonded. While overall fatigue life was not improved for either loading scenario,

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Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Rhymer

2002

International Journal of Fatigue

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“…Along with the host of benefits, the main disadvantage is the fabrication of these composites which is difficult 1 . The aircraft materials are developed based on fiber metal laminates which needs the improved crack growth properties 2 . Competing materials like advanced aluminium alloys and fibre reinforced composites have potential to increase the cost effectiveness of the structure.…”

Section: Introductionmentioning

confidence: 99%

Mechanical Properties Evaluation of the Carbon Fibre Reinforced Aluminium Sandwich Composites

Tamilarasan¹,

Karunamoorthy

Palanikumar³

2015

Mat. Res.

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Sandwich laminates play an important role in industries and they are used in varieties of engineering applications. In the present investigation, carbon fiber reinforced aluminium sandwich laminates are fabricated and their properties such as tensile, flexural and impact are studied for their use in structural applications. All the tests are carried out as per ASTM standard. Scanning Electron Microscope (SEM) analysis is carried out to investigate the structure of the sandwich laminates. The microstructures clearly indicate the fractured surface. The tested specimen clearly indicates the fracture surface of the sandwich composites.

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“…Numerous methods have been employed such as matrix toughening, fibre hybridising and many more. [7][8][9] The major drawback of hybrid FRPs strengthening is the high cost of the different FRPs materials. The FRPs have some drawbacks such as while fitting as well as joining applications in the fibrous environment it will not withstand total failure load.…”

Section: Introductionmentioning

confidence: 99%

Influence of stainless-steel wire mesh on the mechanical behaviour in a glass-fibre-reinforced epoxy composite

Sakthivel¹,

Vijayakumar²

2017

Mater. Tehnol.

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This work covers the fabrication and investigation of the mechanical behaviour of a glass-fibre-reinforced polymer (GFRP) composite embedded with a stainless-steel wire mesh (SSWM) layer. This work takes the hybridising approach in improving the mechanical properties of GFRP through the incorporation of SSWM into the laminates. The structure of the composite is such that the SSWM was placed in the top, middle and bottom of the GFRP. The laminates are fabricated using the hand-layup method with a 40 % weight fractions of epoxy resin, 50 % weight fractions of woven glass fibre and the remainder being SSWM. The mechanical characteristics of the composites are obtained using tensile, flexural, inter delamination and drop weight impact tests. In addition to that, a morphological investigation is made utilizing a scanning electron microscope (SEM). The test outcome demonstrates that the introduction of SSWM leads to far better mechanical properties than GFRP and SSWM in the middle layer has a superior strength compared to other laminates. Keywords: glass fibre reinforced polymer, stainless-steel wire mesh, mechanical tests, ultimate strength, SEM Delo obravnava izdelavo in preiskavo mehanskih lastnosti polimera, oja~anega s steklenimi vlakni (angl. GFRP) v katerem je vgrajena ploskovna`i~na mre`a iz nerjavnega jekla (angl. SSWM). To delo predstavlja hibridiziran pribli`ek za izbolj{anje mehanskih lastnosti GFRP z vgraditvijo SSWM v laminate. Kompozit je sestavljen tako, da je bila SSWM name{~ena zgoraj, v sredini in spodaj. Laminati so izdelani z ro~nim polaganjem 40 masnimi % epoksi smole, 50 masnimi % tkanine iz steklenih vlaken, ostalo pa je SSWM. Mehanske lastnosti kompozitov so dolo~ene z nateznim in z upogibnim preizkusom, z razslojevanjem in z udarno`ilavostjo. Dodatno k temu je izvedena tudi morfolo{ka preiskava s pomo~jo vrsti~nega elektronskega mikroskopa (SEM). Rezultati preizkusov ka`ejo, da vstavitev SSWM bolj izbolj{a mehanske lastnosti kot GFRP, SSWM v sredini pa izbolj{a trdnost v primerjavi z ostalimi laminati. Klju~ne besede: steklena vlakna, jeklo oja~ano s polimeri, ploskovna`i~na mre`a iz nerjavnega jekla, mehanski preizkusi, natezna trdnost, SEM

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Fiber metal laminates: An advanced material for future aircraft

Cited by 319 publications

References 1 publication

Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Mechanical Properties Evaluation of the Carbon Fibre Reinforced Aluminium Sandwich Composites

Influence of stainless-steel wire mesh on the mechanical behaviour in a glass-fibre-reinforced epoxy composite

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