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Topology optimization method of wing spar structure based on stress constraints

A technology of topology optimization and stress constraint, applied in special data processing applications, instruments, electrical digital data processing, etc., can solve the problem of large tangential stress on nails, reduce tangential stress, ensure structural stiffness performance, and avoid stress concentrated effect

Active Publication Date: 2016-06-08
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0007] In order to overcome the shortcomings of the existing methods of designing nail-loaded tangential stresses, the present invention provides a topology optimization method for wing spar structures based on stress constraints

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  • Topology optimization method of wing spar structure based on stress constraints
  • Topology optimization method of wing spar structure based on stress constraints
  • Topology optimization method of wing spar structure based on stress constraints

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Embodiment Construction

[0024] The stress constraint-based topology optimization method of the wing spar structure of the present invention specifically includes the following steps.

[0025] The present invention is illustrated by taking the topological optimization design of a cantilever beam with a skin considering nail loading as an example. The thickness of the cantilever beam is 40mm, the length is 1000mm, and the height is 250mm. The cantilever beam is connected to the non-design domain beam by 7 bolts. The thickness of the non-design domain beam is 40mm, the length is 1000mm, and the height is 37.5mm. The length of the bolt is 10, and the section is a square of 20×20. Young's modulus E=2.63GP, Poisson's ratio μ=0.1. A concentrated load P=60N is applied to one end of the cantilever beam, and the direction is upward.

[0026] (a) Establish a topology optimization model, define the cantilever beam as the design domain Ω of topology optimization, and discretize Ω into 9600 3-dimensional unit ...

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Abstract

The invention discloses a wing-spar structure topology optimization method based on stress constraint. The method is used for solving the technical problem that nail load design through an existing method is large in tangential stress. According to the technical scheme, the method comprises the steps that a nail load model is built through a three-dimensional entity unit. Stress serves as the constraint in the optimization process, the tangential stress in the position of a constrained nail load unit is the minimum, nail load sensitivity is obtained through an adjoint method, and nail load flexibility and material utilization amount jointly serve as stiffness optimization constraint to conduct structural topology optimization and obtain the design result. The method can guarantee structural stiffness performance and avoid concentrated stress because structural force transferring paths are reasonably distributed. According to the embodiment of the method, when the constraint structure material body subtraction proportions are 0.3 respectively, the smooth degree function of the constraint structure free of applied stress is 0.0207J, and under the condition that the smooth degree function of the constraint structure with applied stress is not changed, the maximum tangential stress of a bolt is reduced to 11.3MPa from 17.9MPa, and is reduced by 36.8%, and the tangential stress of a bolt unit is reduced.

Description

technical field [0001] The invention relates to a topology optimization method for wing spar structure, in particular to a stress constraint-based topology optimization method for wing spar structure. Background technique [0002] Document 1 "Structure optimization design of wing spar based on ISIGHT / NASTRAN. Wang Xiangsheng et al. Aircraft Design. 2008.28(4): 23-27." proposed a set of ISIGHT / NASTRAN-based optimization design of wing spar structure method. In the case of meeting the strength requirements of the wing, the method takes the structural quality as the target in the structural optimization, and the web VONMISES stress, the axial stress of the flange and the stress of the flange beam element are constrained. The weight of the beam is effectively reduced through size optimization and shape optimization, and the strength requirements are met. [0003] Document 2 "Comprehensive Optimal Design of Topology, Shape and Size of Large Aspect Ratio Flying Wing. Wang Wei, Y...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 张卫红侯杰谷小军朱继宏
Owner NORTHWESTERN POLYTECHNICAL UNIV
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