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Composite material wing structure design optimization method

A composite material and wing structure technology, applied in design optimization/simulation, computer-aided design, calculation, etc., can solve problems such as large amount of calculation, inapplicability to complex composite material structures, and distribution optimization deviating from the optimal solution, etc. Guaranteed accuracy and great application value

Pending Publication Date: 2022-07-01
HIWING AVIATION GENERAL EQUIP
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Problems solved by technology

[0004] The invention provides a composite material wing structure design optimization method, which can solve the technical problems in the prior art that the result of distribution optimization deviates from the optimal solution, is not suitable for complex composite material structures, and has a large amount of calculation

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  • Composite material wing structure design optimization method

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Embodiment Construction

[0016] It should be noted that the embodiments in the present application and the features of the embodiments may be combined with each other in the case of no conflict. The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only a part of the embodiments of the present invention, but not all of the embodiments. The following description of at least one exemplary embodiment is merely illustrative in nature and is in no way intended to limit the invention, its application, or uses. Based on the embodiments of the present invention, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present invention.

[0017] It should be noted that the terminology used herein is for the purpose of describing specific em...

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Abstract

The invention provides a composite material wing structure design optimization method which comprises the steps of parameterizing a composite material wing structure, determining optimization variable parameters, establishing a finite element model of the composite material wing structure, and determining constraint variables and constraint variable target values. Performing preliminary optimization on the optimization variable parameters by using a multi-island genetic algorithm, and performing further optimization on the preliminary optimization result of the optimization variable parameters by using a sequential quadratic programming method until a constraint variable final value which is converged to a constraint variable target value and corresponds to the lightest wing mass is obtained; and determining the optimization variable parameter value corresponding to the final value of the constraint variable as the final value of the optimization variable parameter. According to the technical scheme, the technical problems that in the prior art, the distribution optimization result deviates from the optimal solution much, the distribution optimization result is not suitable for a complex composite material structure, and the calculated amount is large are solved.

Description

technical field [0001] The invention relates to the technical field of structural design simulation, in particular to a composite material wing structure design optimization method. Background technique [0002] In order to improve the aerodynamic efficiency of UAVs in the near space and at the same time increase their flight time and range, UAVs are usually required to have high aerodynamic efficiency and low structural mass ratio, so large aspect ratio composite material wings are often used. The structure is used as the wing of the near-space UAV to meet the requirements of aerodynamic efficiency and mass ratio, but at the same time, the high aspect ratio composite wing structure also needs to meet the strict requirements of strength, stiffness and stability. Generally speaking, the bending moment of the wing root of a composite wing with a large aspect ratio is large, which makes it difficult to satisfy the compression stability of the upper skin. Secondly, the torsional...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/15G06F30/17G06F30/23G06F111/04G06F113/26G06F113/28G06F119/14
CPCG06F30/15G06F30/17G06F30/23G06F2111/04G06F2113/26G06F2113/28G06F2119/14
Inventor 何丹琪田晓
Owner HIWING AVIATION GENERAL EQUIP
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