Microstructural Design and Analysis of Composite with a Near-zero Expansion Coefficient
The frontier research missions,including the national space telescope and the space gravitational wave detection,put forwards urgent demand for composite components with thermal stability in dimension.These composite components are crucial for ensuring directional stability for imaging/detection of large precision optical platforms in outer space's alternating high and low temperature environment.However,these composites with obvious anisotropy are highly susceptible to fiber angle deviations during manufacturing.A microstructural model for carbon fiber/cyanate ester composites with carbon fiber wrinkles is established in this paper,the impact of fiber wrinkle geometry on the material's anisotropic thermal expansion coefficient is studied and a thermal analysis model for composite structures with wrinkles is established based on the Layerwise theory.The study indicates that fiber wrinkles primarily influence the thermal expansion coefficient along the fiber direction in composites.The more severe the fiber buckling is,the greater the local thermal deformation after heated is.Employing thinner prepreg to increase the stacking layers can,to some extent,mitigate the effects of carbon fiber wrinkles on the structure's overall thermal stability.
thermal stability in dimensioncompositefiber wrinklesmicroscopic thermal expansioncarbon fibercyanate ester
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