Results 21 to 30 of about 50,220 (341)

Mass Optimisation of Turbofan Engine Casing Made of Sandwich Structure

open access: yesComputer Assisted Methods in Engineering and Science, 2019
Materials of a high specific strength and stiffness are used in the aerospace industry to obtain the lowest possible aircraft mass. The object of analysis is the casing of the F124 turbofan engine.
Elżbieta Szymczyk   +3 more
doaj   +1 more source

Experimental analysis of aluminium/carbon epoxy hybrid laminates under flexural load

open access: yesFracture and Structural Integrity, 2019
Industry needs new materials that present very high structural characteristic, such as high strength, low weight and high damage tolerance. To obtain these characteristics a new class of materials has been introduced: Fibre Metal Laminate (FML); they ...
Costanzo Bellini   +3 more
doaj   +3 more sources

Interlaminar shear strength study on CFRP/Al hybrid laminates with different properties

open access: yesFracture and Structural Integrity, 2020
FML (Fibre Metal Laminate) is a hybrid material that presents outstanding structural properties, such as resistance to cyclic and dynamic loads, together with low specific weight.
Costanzo Bellini   +2 more
doaj   +1 more source

The Influence of Material Configuration of Fibre-Metal Laminates with Alumina Core on Flexural Strength

open access: yesFatigue of Aircraft Structures, 2023
Fibre metal laminates (FMLs) consisting of layers made of PA6 polyamide prepregs reinforced with glass and carbon fibres and an aluminium alloy core are the new variant of the other types used by aerospace FML materials such as GLARE or CARALL.
Frankiewicz Mariusz   +4 more
doaj   +1 more source

Measuring the notched compressive strength of composite laminates: Specimen size effects [PDF]

open access: yes, 2008
Large fibre reinforced composite structures can give much lower strengths than small test specimens, so a proper understanding of scaling is vital for their safe and efficient use.
C. Soutis   +15 more
core   +3 more sources

Crack propagation behavior on metal laminate of FMLs after a high tensile overload under high constant amplitude load [PDF]

open access: yesFME Transactions, 2020
The crack propagation behaviour on the metal laminate of the FMLs is investigated under constant amplitude loads, which is higher compared to the fatigue strength of the metal laminate, and the subsequent crack propagation behaviours after being highly ...
Purnowidodo Anindito, Iman Hilmi
doaj  

Energy absorption and bending stiffness in CFRP laminates : the effect of 45º plies [PDF]

open access: yes, 2008
The impact characteristics of cross-ply and angle-ply composite laminates were investigated, with an instrumented impact drop tester by performing gravity assisted drop tests on [0/90]6s and [0/45/90]4s laminates.
Alexander, N.V.   +3 more
core   +1 more source

Multi-objective optimization of carbon/glass hybrid composites with newly developed resin (NDR) using gray relational analysis [PDF]

open access: yes, 2020
Purpose: It is seen that little amount of work on optimization of mechanical properties taking into consideration the combined effect of design variables such as stacking angle, stacking sequence, different resins and thickness of composite laminates has
Bhalerao, Yogesh J.   +1 more
core   +1 more source

Feasibility study of fusion bonding for carbon fabric reinforced Polyphenylene Sulphide by hot-tool welding [PDF]

open access: yes, 2011
In recent years, there is a growing interest in joining techniques for thermoplastic composites as an alternative to adhesive bonding. In this article, a fusion bonding process called hot-tool welding is investigated for this purpose and the used ...
De Baere, Ives   +2 more
core   +1 more source

Analysis on drilling of woven glass fibre reinforced aluminium sandwich laminates

open access: yesJournal of Materials Research and Technology, 2019
Fibre metal laminates being used in aerospace industries becomes primary composite material under research, since its application finds on the outer covering of the fuselage skin structure, the holes are need to be drilled on it, to assemble it.
Gopalakrishnan Ramya Devi   +1 more
doaj   +1 more source

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