Optimization design method of composite material wing panel

Abstract

The invention discloses an optimization design method of a composite material wing panel. The optimization design method comprises the following steps: (1) carrying out finite element simulation modeling on the main structure of a wing; (2) applying a load and boundary condition to a finite element wing box section model; (3) calculating an integral wing box finite element model, and extracting the internal load of a structure; (4) designing a layup library, and calculating the laminate attributes of all layers in the layup library to obtain a rigidity matrix and an equivalent elastic modulus; (5) aiming at the calculation requirements of different structural unit initial dimensions and different failure modes of a skin stringer to carry out secondary distribution calculation on the load; (6) calculating the design allowable value of each structure failure mode of the panel; (7) calculating the safety margin of each BAY of a panel structure; (8) setting a maximum slope rate of panel layup arrangement and an adjacent area laminate throwing layer, setting the Poisson ratio difference value coefficient and the stiffness ratio of the stringer and the skin, and regulating the layer if a design range is not met; (9) if the design does not meet weight requirements, requiring to circularly carrying out the steps (1) to (8) to regulate the lay and the dimension until structure weight requirements are met. According to the method, the design and optimization working efficiency of the integral panel of the composite material is improved, and research and development cost is saved.

Description

technical field [0001] The invention relates to an optimization and design method for a T-shaped long truss reinforced wall plate of a civil transport aircraft wing, and belongs to the field of civil aircraft composite material structure design. Background technique [0002] In recent years, with the improvement of composite material design capabilities, the development of manufacturing technology and the reduction of production costs, a large number of civil aircraft structural parts have begun to use composite materials. Composite material elements were only used in the secondary structure of passenger aircraft at first, and now they are used in the main structures such as the wings and fuselage panels of Boeing B787 and Airbus A350, which not only shows that the design and manufacture of large and complex main bearing structures Breakthroughs have been made in key technologies such as testing, repairing, and maintenance, and it marks that advanced composite materials are ...

AI Technical Summary

Problems solved by technology

At this stage, the design of wing panels does not effectively coordinate the relationship between the two, resulting in the loss of material properties and aircraft weight, and does not maximize the role of composite material structures

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