A Design Method for Composite Laminates with Partition and Variable Thickness

Abstract

Provided is a design method for a partition variable thickness composite laminate. In a global optimization stage of continuous variables of an airfoil class structure, with the target of lightest mass, with limitation of buckling, deformation, strength, and a plurality of kinds of angular ply proportional relations of fixation of composite laminates, through finite element modeling and a continuous variable numerical optimization technology, optimization of the integrated structure and proportion of angular plies in each partition of a composite panel is realized. In a discrete variable optimization stage, a composite variable thickness skin plate discrete variable optimization strategy is provided, to realize integrated ply sequence design of the variable thickness plate. A design result needs to ensure mechanical property of the structure and maximum continuity of the plies, and meanwhile engineering constraint and manufacturing requirement are satisfied. The method can realize organic relations of optimization information of continuous variables and discrete variables, and light weight and overall mechanical properties given by a continuous variable optimization result are ensured, and various engineering constraint and maximum continuity requirement of plies are satisfied.

Description

technical field [0001] The invention relates to the design field of composite material laminated boards, in particular to a design method for composite material laminated boards with partitions and variable thicknesses. [0002] An optimized lay-up design method suitable for aircraft wing skin-like structures with variable-thickness composite laminated panels. Background technique [0003] Fiber-reinforced resin-based composite materials have many advantages such as high specific strength, high specific stiffness, excellent thermal stability, good fatigue and fracture characteristics, and strong mechanical properties can be designed. Generally, the structural weight can be reduced by about 30%. Therefore, the amount of advanced composite materials used in aviation and aerospace structures has become a symbol to measure their advanced nature. [0004] The composite laminated board structure is generally formed by stacking single-layer thin sheets with different fiber directi...

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Problems solved by technology

The parameter settings have a great influence on the results. If the parameters are not set properly, the optimal solution may not be found; at the same time, the algorithm requires a large amount of calculation, and may fail to optimize the larger-scale variable-thickness panel plate optimization problem.

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