The stiffness of carbon fiber laminates is related to the material properties, direction of laying, percentage of angles and sequence of stacking sequence. Therefore, the stiffness matrix of laminates is different under different ply structures. In the design of the general laminate, the thickness of the layer, the angle of the layer and the order of the layer should be taken into consideration.

The angle of ply is usually preferred for 0&deg, 90&deg, &plusmn, 45&deg, and the special angle between &pi and /4 is mainly due to easy operation and precise control and control, and at the same time, large in-plane shear stiffness and strength can be obtained. Generally speaking, 0° monolayer is used to bear axial load; ± 45° monolayer is used to bear shear load, 90° monolayer is used to withstand lateral load and control Poisson effect. After the angle of layer selected, laminate design should follow the following principles: first, except for special needs, should be a balanced symmetry layer, in order to avoid the forming process because of the coupling caused by warping; two is the same angle of layer should be evenly distributed along the thickness direction of laminates, not too concentrated, otherwise easily in the same ply angle of interlayer delamination.

The three most common types of layers are [O]l0, [0/90/0/90/0]s and [0/90/45/90/0]s. Among them, [O]l0 is a unidirectional ply of single ply angle, [0/90/0/90/0]s is an orthogonal ply with two angles, [0/90/45/-45/0]s is a &pi with four angles, and /4 lays.

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