Method for designing structure of large-scale composite material reinforced wall plate

Abstract

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.

Description

technical field [0001] The invention discloses a large-scale composite material reinforced wall board structure, which belongs to the field of aircraft composite material structure design. Background technique [0002] Using the traditional design method, it is often unscientific to determine the ply ratio of the wall panel based on experience in the scheme design stage, and it is not easy to converge during the ply optimization design, because the initial value deviates greatly from the true value and the weight loss is also large. At the same time, the traditional design of composite materials adopts the two-dimensional layer-by-layer drawing method, which is not only difficult to design, but also prone to errors for large-scale reinforced wall panels with many layers of changing areas and more complex areas, and brings great inconvenience to the manufacturer. Secondary workload, weight statistics are not accurate and other shortcomings. Contents of the invention [000...

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Problems solved by technology

[0002] Using the traditional design method, it is often unscientific to determine the ply ratio of the wall panel based on experience in the scheme design stage, and it is not easy to converge during the ply optimization design, because the initial value deviates greatly from the true value and the weight loss is also large

At the same time, the traditional design of composite materials adopts the two-dimensional layer-by-layer drawing method, which is not only difficult to design, but also prone to errors for large-scale reinforced wall panels with many layers of changing areas and more complex areas, and brings great inconvenience to the manufacturer. Disadvantages such as secondary workload and inaccurate weight statistics

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