Feature-driven airfoil structure topology optimization method

A topology optimization and airfoil technology, applied in the field of topology optimization of airfoil structures, can solve problems such as poor practicability, and achieve the effects of good practicability, improved effectiveness and practicability

Active Publication Date: 2017-12-29
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

[0004] In order to overcome the shortcomings of poor practicability of the existing topological optimization methods for airfoil structures, the present invention provides a feature-driven topological optimization method for airfoil structures

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  • Feature-driven airfoil structure topology optimization method
  • Feature-driven airfoil structure topology optimization method
  • Feature-driven airfoil structure topology optimization method

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Embodiment Construction

[0022] Reference Figure 1-2 . The specific steps of the feature-driven wing surface structure topology optimization method of the present invention are as follows:

[0023] (a) Establish an airfoil topology optimization model. The airfoil is a trapezoidal surface with variable cross-sectional thickness, and the ratio of thickness to length is 1:15. There are frames around and outer skins on the upper and lower surfaces, and the thickness is 2mm. Define the topologically optimized design domain Ω inside the airfoil structure d , The frame and skin are non-design domains. Design domain Ω d Discrete into 313,440 three-dimensional units as a fixed grid.

[0024] (b) Set the number of initial beams, layout angle, position and size value, use level set function and Boolean operation to establish the initial layout of airfoil reinforcement, the mathematical model is expressed as:

[0025] Φ=Φ 1 (x)∪Φ 2 (x)∪…∪Φ n (x) (1)

[0026] In the formula, Φ-reinforced feature of airfoil, n-number o...

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Abstract

The present invention discloses a feature-driven airfoil structure topology optimization method, in order to solve the technical problem of poor practicability of the existing airfoil structure topology optimization method. The technical scheme comprises: determining a feature shape of a beam in an airfoil structure in accordance with the engineering practice; defining an angle, a location and a dimension of the feature shape as design variables; using the fixed grid method, and then using the level set method and the Boolean operation to obtain an initial structure of an airfoil feature layout; in each step of iteration of optimization, updating the airfoil feature layout according to an optimization variable result; and taking a certain material volume as a constrained structure and taking a minimum strain energy as a target to carry out topology optimization to obtain an airfoil stiffener layout design result. By using the method disclosed by the present invention to carry out topology optimization on the airfoil structure, the layout optimization result combined and formed by the beams taken as features can directly guide and be applied to the engineering practice, and good practicality is achieved.

Description

Technical field [0001] The invention relates to a topological optimization method of an airfoil structure, in particular to a topological optimization method of an airfoil structure based on feature driving. Background technique [0002] The literature "Research on the comprehensive technology of aircraft wing structure layout based on hierarchical optimization. Deng Yangchen, Zhang Weihong, Zhang Yining. Strength and Environment, 2005, 32(1): 27-35." The surface layout design is divided into three levels of topology optimization. The size optimization and stability criterion optimization finally result in the wing surface structure layout design that has certain guidance and reference value for aircraft designers. This method is based on the results of airfoil topology optimization based on pseudo-density, and adds dimensional optimization and stability criteria optimization. The rigidity is the objective and the structural lightweight is the constraint. The optimization finally...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20
Inventor 赵宇博朱继宏周莹王杰张卫红
Owner NORTHWESTERN POLYTECHNICAL UNIV
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