To study the mechanical properties of carbon filament wound composites, the tensile,in-plane shearand interface shear tests of filament wound compositeswere carried out by using NOL specimens and shear specimens of filament wound composites which was made by the method of first winding and forming, then unfolding and flattening, and finally curing and forming,the basic mechanical properties parameters of the wound composites were obtained, and the maximum likelihood estimation was used to analyze them. The results show that the in-plane shear strength, tensile strength and interlaminar shear strength of filament wound composites all obey the two-parameter Weibull distribution. The shear stress-strain curve of filament-wound composites presents typical nonlinear characteristics, and the fiber overlap structure hinders the damage expansion inside the structure, resulting in the in-plane shear failure strain being significantly greater than the in-plane shear failure strain of the composite laminate shear failure strain.