Efficient optimization method for variable stiffness composite material plate shell structure

A composite material board and optimization method technology, which is applied in design optimization/simulation, special data processing applications, instruments, etc., can solve the problems of low efficiency in the optimization design of variable stiffness composite material board and shell structures, and avoid high time-consuming problems, Improve optimization efficiency and reduce the effect of R&D cycle

Active Publication Date: 2017-09-29
DALIAN UNIV OF TECH
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Problems solved by technology

[0005] The present invention mainly solves the technical problem of low efficiency in optimization design of the variable stiffness composite material plate and shell structure in the prior art, and proposes an efficient optimization method for the variable

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  • Efficient optimization method for variable stiffness composite material plate shell structure
  • Efficient optimization method for variable stiffness composite material plate shell structure
  • Efficient optimization method for variable stiffness composite material plate shell structure

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Embodiment Construction

[0030] In order to make the technical problems solved by the present invention, the technical solutions adopted and the technical effects achieved clearer, the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described here are only used to explain the present invention, but not to limit the present invention. In addition, it should be noted that, for the convenience of description, only parts related to the present invention are shown in the drawings but not all content.

[0031] figure 1 The implementation flow chart of the efficient optimization method for the variable stiffness composite shell structure provided by the embodiment of the present invention. Such as figure 1 As shown, the high-efficiency optimization method for the variable stiffness composite shell structure provided by the embodiment of the present invention includes:

[0032] S...

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Abstract

The invention relates to composite material structure design in aerospace structures, and provides an efficient optimization method for a variable stiffness composite material plate shell structure. The method includes the steps: performing curve fiber path accurate modeling and buckling analysis on the variable stiffness composite material plate shell structure based on an isogeometric method; building an isogeometric buckling design model of the structure; deriving total analytical sensitivity of buckling response of the variable stiffness composite material plate shell structure; efficiently optimizing fiber paths of the variable stiffness composite material plate shell structure by a gradient-based method to obtain an optimal structure meeting process manufacturing constraints. According to the structure, the carrying efficiency of the variable stiffness composite material plate shell structure can be remarkably improved, and the development period of products is greatly shortened.

Description

technical field [0001] The invention belongs to the technical field of load-bearing structure design in aerospace structures, and relates to an efficient optimization method for a variable stiffness composite material plate shell structure. Background technique [0002] The lightweight of the load-bearing structure of the spacecraft can reduce the resources and energy consumption required to manufacture the structure, which will undoubtedly reduce the huge cost. Due to the high specific stiffness and specific strength, composite shell structures are becoming more and more common in the application of complex load-bearing structures in the modern aerospace industry. At present, fiber-reinforced composite laminates are mostly formed by laying parallel and straight fibers, and the angle of the fibers in the same layer is fixed. Considering the manufacturing process constraints, the lay-up directions of 0°, 90° and ±45° are often used in engineering. The lay-up fibers lack a ri...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/23G06F2113/24
Inventor 郝鹏袁枭桀王雨田刘晨王博牛飞
Owner DALIAN UNIV OF TECH
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