The invention discloses a method for designing the structure of a large-scale
composite material reinforced
wall plate, and belongs to the field of structural design of aircraft composite materials. The method comprises the steps that according to the design of the composite materials, shearing stress gamma and positive stress epsilon are selected to be used, the specific value of the equivalent
elastic modulus E to the
shear modulus G of a
metal-material box section wall board is calculated, according to the specific value, the layering proportion of a
composite material laminated plate in an inspection area is determined, then the number, angle and sequence of initial layered
layers in the inspection area are determined according to the situation of the stress, the layer angle information and material performance data are input to a finite
element model to solve the stress and check stability, after iteration, the number, sequence and angle of
skin stringer layered
layers are determined, it is ensured that all the
layers are symmetrically balanced, digital modeling is adopted, and three-dimensional annotations, glass cloth layering, materials,
processing notes and other information are digitized. According to the method, the design and manufacturing period of the large-scale
composite material reinforced
wall plate is greatly shortened, and meanwhile the quality of the product is greatly improved.