Abstract:

Fiber reinforced composite materials have been widely used in the aerospace area because of its special properties, such as high specific strength, high specific stiffness and high specific modulus. The composite laminates are the main applicable form in the structural areas. When studying the laminates with holes, in view of the anisotropy of the materials and the hole factor of the structure, it is better to apply numerical method. According to the designable feature of the laminates, with the factors of the layer angle and the layer order taken into consideration, a new symmetrical laminate has been designed. Based on the finite element method, by means of ANSYS computing software, the stress around hole in the designed laminate has been studied and the stress contour graph and stress curve around the hole have been drawn out. The conclusion can be provided as a good reference for the design of the laminates with holes.