Abstract
Fiber metal laminates (FMLs) are a novel type of structural material that has been extensively applied in the aerospace field. These laminates are sandwich-type composite materials that comprise alternate metal and fiber-reinforced resin layers. Because of the structural characteristics of the material, it has high-impact resistance from the metal layer and increased fracture toughness and excellent fatigue and damage tolerance properties from the fiber layer. To further develop and apply this new composite material, it is essential to understand the research status on the stress analysis of each component in FMLs and the tensile strength properties of FMLs. Therefore, in this study, the current research status on the residual stress and applied stress of the component materials in FMLs and the tensile strength of the laminates is summarized. The relationship between the applied stress of each layer and the remote stress of laminates and the relationship between the tensile properties of laminates and the component material properties in laminates are clarified. Additionally, the theoretical basis and direction of development of the related models are analyzed and studied. Consequently, all of the above are aimed at laying a foundation for further investigations of the laminate theory and for the improvement of the theoretical research system.
Highlights
Fiber metal laminates (FMLs) constitute a joint scientific and technological achievement of Delft University, Fokker Aircraft Company, and the National Aerospace Laboratory of the Netherlands [1]
While these composites perfectly combine the performance advantages of two different materials, FMLs improve and remedy the individual deficiencies of the two materials. They overcome the shortcomings of low-fatigue strength of aluminum alloys and the low ductility and impact strength, increased cost, and poor processability of fiber layers [3]
According to the characteristics of orthogonal Glass Reinforced Aluminum Laminates (GLARE) laminates in combination with the mixing law of elastic moduli for composite materials, Wang et al [44] modified the metal volume fraction (MVF) theory based on the consideration of the effect of fibers on the performance in two in-plane directions and accurately predicted the elastic modulus, yield stress, and tensile strength of materials
Summary
Fiber metal laminates (FMLs) constitute a joint scientific and technological achievement of Delft University, Fokker Aircraft Company, and the National Aerospace Laboratory of the Netherlands [1]. Different material properties can be obtained by changing the thickness, quantity, and type of the metal layer, the direction and system of fibers, and the thickness, quantity, and layup order of the fiber layer While these composites perfectly combine the performance advantages of two different materials, FMLs improve and remedy the individual deficiencies of the two materials. Compared to traditionally used aluminum alloy materials in aviation, FMLs can reduce weight by 25%–30% and increase fatigue life by a factor of 10–15 [4]. Their performance meets the requirements of the new generation of aviation equipment, their manufacturing is complex and costly [5, 6]. To promote further studies of the FMLs based on the analysis of the existing models, the direction of the anticipated theoretical development is clarified
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