Composite laminates

Composite laminates

Assemblages of layers of fibrous composite materials (see illustration) which can be tailored to provide a wide range of engineering properties, including inplane stiffness, bending stiffness, strength, and coefficients of thermal expansion.

The individual layers consist of high-modulus, high-strength fibers in a polymeric, metallic, or ceramic matrix material. Fibers currently in use include graphite, glass, boron, and silicon carbide. Typical matrix materials are epoxies, polyimides, aluminum, titanium, and alumina. Layers of different materials may be used, resulting in a hybrid laminate. The individual layers generally are orthotropic (that is, with principal properties in orthogonal directions) or transversely isotropic (with isotropic properties in the transverse plane) with the laminate then exhibiting anisotropic (with variable direction of principal properties), orthotropic, or quasi-isotropic properties. Quasi-isotropic laminates exhibit isotropic (that is, independent of direction) inplane response but are not restricted to isotropic out-of-plane (bending) response. Depending upon the stacking sequence of the individual layers, the laminate may exhibit coupling between inplane and out-of-plane response. An example of bending-stretching coupling is the presence of curvature developing as a result of inplane loading. See Composite material, Metal matrix composite

Classical lamination theory describes the mechanical response of any composite laminate subjected to a combination of inplane and bending loads. The laminate in Fig. 1 uses a global x-y-z coordinate system with z perpendicular to the plane of the laminate and positive downward. The origin of the coordinate system is located on the laminate midplane. The laminate has N layers numbered from top to bottom. Each layer has a distinct fiber orientation denoted Θk. The z coordinate to the bottom of the kth layer is designated zk with the top of the layer being zk-1. The thickness, tk, of any layer is then tk = zk - zk-1. The top surface of the laminate is denoted z0, and the total thickness is 2H.

It is assumed that (1) there is perfect bonding between layers; (2) each layer can be represented as a homogeneous material with known effective properties which may be isotropic, orthotropic, or transversely isotropic; (3) each layer is in a state of plane stress; and (4) the laminate deforms according to the Kirchhoff (1850) assumptions for bending and stretching of thin plates: (a) normals to the midplane remain straight and normal to the deformed midplane after deformation, and (b) normals to the midplane do not change length.

The wide variety of coefficients of thermal expansion are possible through changes in the stacking arrangement of a given carbon/epoxy. The coefficient of thermal expansion is the strain associated with a change in temperature of 1°. Most materials have positive coefficients of expansion and thus expand when heated and contract when cooled. The effective axial coefficient of thermal expansion of the carbon/epoxy can be positive, negative, or zero, depending upon the laminate configuration. Laminates with zero coefficient of thermal expansion are particularly important because they do not expand or contract when exposed to a temperature change. Composites with zero (or near zero) coefficient of thermal expansion are therefore good candidates for application in space structures where the temperature change can be 500°F (from -250 to +250°F) [278°C (from -157 to +121°C)] during an orbit in and out of the Sun's proximity. There are many other applications where thermal expansion is a very important consideration.

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- High Compatibility of Nomex Honeycomb with Composite Laminates Favors Market Growth in Different Applications
The project exhibition also declared special awards including "Best Mechanical Design" which was awarded to the group for "Fatigue testing machine for composite laminates"; "Best Research Design award was conferred to the students who developed "Modification of UHM-WPE for different joint replacement" and "Best Mechanical Green project" who made the project titled, "Comparative study of carbon capturing techniques with design and fabrication of prototype and "University-Industry Linkage award for the "Effect of traffic induced vibration in gas pipelines suspended with bridges".
The low-cost stretchable composite sensor has also shown a high sensitivity and can detect small deformations such as yarn stretching as well as out-of-plane deformations at inaccessible places within composite laminates.
The automated digital manufacturing system was built at Airborne's facility and is capable of producing four thermoplastic composite laminates every 60 seconds
Through its Innovations of Scale theme, the company is celebrating an important milestone for this major project, which will help industrialize thermoplastic composite laminates, enabling broader adoption of this material across industries, such as consumer electronics, aerospace, automotive, sporting goods, healthcare, and mass transportation.
core-shell rubber) are on the other hand commonly assumed to be suitable for resin infusion processes due to their small physical size [16-19], Sprenger [20] recently reviewed the use of silica nanoparticles in fiber reinforced composites, including details for the variety of methods used in the production of the composite laminates. Resin infusion methods ranged from hand lay-up (impregnation layer by layer) [21], single-line-injection (SLI) [22], resin infusion under flexible tooling (RIFT) [11, 16], pultrusion [23], vacuum-assisted resin infusion (VARI) [24, 25], vacuum-assisted resin transfer molding (VARTM) [26-28], and resin transfer molding (RTM) [29].
[8] to find optimal autoclave temperature and pressure histories for curing of thermoset-matrix composite laminates. In this study the objective is to minimize the total time of the cure cycle, while the constraints include a maximum temperature in the laminate (to avoid thermal degradation) and a maximum deviation of the final fiber volume fraction from its target value.
Currently, macro mechanics is used in the designing of composite laminates because macro mechanical equations of this type of designing are well established therefore macro mechanics is also used to analyse buckling of composite plates.
Finite element model for piezoelectric composite laminates, Smart Mater.
Ostachowicz, "Guided wave-based detection of delamination and matrix cracking in composite laminates," Proceedings of the Institution of Mechanical Engineers, PartC: Journal of Mechanical Engineering Science, vol .
Composite laminates are frequently used in the modern automobile, aerospace, and manufacturing industries due to their excellent mechanical properties and lightweight characteristics.
Cawley, "The interaction of Lamb waves with delaminations in composite laminates," The Journal of the Acoustical Society of America, vol.

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