Fiber Metal Laminates — The Synthesis of Metals and Composites

Krishnakumar, S.

doi:10.1080/10426919408934905

Cited by 125 publications

(63 citation statements)

References 32 publications

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“…But lastly and perhaps most importantly, this lack of ductility has a significant effect on the damage tolerance and notch root plasticity of composites [4]. This is a major issue in modern aircraft design as all structures inevitably incur some damage and fracture and the inability to absorb such damage prevents widespread usage.…”

Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

“…It possesses the high specific properties of composites while retaining the ductility, machinability, weldability, inspectability, reparability, impact resistance, notch sensitivity, and environmental durability of metals [4]. One of the major reasons these metal advantages are incorporated into this material is by the placement of metal layers on the exterior of the laminate.…”

Section: Laminated Metal Smentioning

confidence: 99%

“…That was the first significant production use of fiber- [4]. Some damage in composites is difficult to find and always difficult to repair.…”

Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

“…This disadvantage manifests itself in several ways. Their brittle nature make composites extremely sensitive to machining and forming, two distinct advantages of metals, particularly in aircraft repair [4]. Secondly, composites can be less forgiving following impact damage.…”

Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

“…Vogelsang and colleagues [11] at Delft first developed ARALL by laminating alternating thin aluminum alloy sheets with aramid-reinforced adhesive prepreg. By 1983, the first production quality ARALL was being manufactured with ALCOA and significant testing has steadily increased ever since [4]. After the initial success of ARALL, a second-generation hybrid composite was developed called GLARE in 1991.…”

Section: Laminated Metal Smentioning

confidence: 99%

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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%

Section: Laminated Metal Smentioning

confidence: 99%

“…That was the first significant production use of fiber- [4]. Some damage in composites is difficult to find and always difficult to repair.…”

Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

Section: Weaknesses In Fiber-reinforced Compositesmentioning

confidence: 99%

Section: Laminated Metal Smentioning

confidence: 99%

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Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Rhymer

2002

International Journal of Fatigue

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Lightweight Structures and Advanced Materials

Das,

Galos

2023

Sustainable Aviation Technology and Operations

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Development of Al–Mg–Sc Thin Foils for Fiber‐Reinforced Metal Laminates

et al. 2018

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The present work is dedicated to studying of a manufacturing process of Al-Mg-Sc thin foils, which are considered as potential candidates to substitute metallic layers made of a conventional Al-Cu based alloy in a new generation of fiber-reinforced metal laminates. For this purpose, a special alloy is designed based on 1570C (Al-5.5Mg-0.23Sc-0.34Mn-0.07Zr-0.03Ti), whereas the content of Mg is reduced and a different Rare Earths Element is used. At the next step, a special rolling technology for production of thin metal foils with a maximal thickness of 0.5 mm is developed. The microstructure is then characterized by using the metallography, EBSD, as well as SEM/EDX techniques. In order to eliminate the rolling defects (waviness of thin foils), thin sheets are subjected to hot pressing. Additionally, numerical simulations of asymmetric hot rolling by using Finite Element Method are performed in order to get a better insight into the formation of foil waviness. The mechanical properties of produced Al-Mg-Sc foils with a thickness of 0.5 mm achieves 377 and 419 MPa for yield and ultimate strength, respectively, with the elongation at break about 11% (in the longitudinal direction). The estimated average corrosion rate of the Al-Mg-Sc sheet material with a thickness of 2.7 mm is not more than 0.006 mm/year. Finally, the rate of fatigue crack growth is found lower than for a conventional AA2024-T3 sheet material as well as the material density (2.65 g cm À3 ).

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Fiber Metal Laminates — The Synthesis of Metals and Composites

Cited by 125 publications

References 32 publications

Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Fatigue damage mechanisms in advanced hybrid titanium composite laminates

Lightweight Structures and Advanced Materials

Development of Al–Mg–Sc Thin Foils for Fiber‐Reinforced Metal Laminates

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