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A wing design method considering pneumatic and structural multi-type design variables

A technology of design variables and design methods, applied in calculation, special data processing applications, instruments, etc., to achieve the effects of reducing design cycle and economic cost, improving accuracy, and convenient interface

Active Publication Date: 2019-05-03
BEIHANG UNIV
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

However, it must be pointed out that, on the one hand, the real three-dimensional airfoil cannot simply be replaced by the ruled surface obtained by expanding certain sections, and in the actual design iteration process, how to extract The key design parameters and how to quickly adjust the wing model according to the shape requirements of some parts of the experiment are difficult to solve by existing methods; on the other hand, for the representative wing structure, how to maximize the Minimize the workload of repeated modeling and how to efficiently adjust the structural finite element model according to different shape inputs. The existing technology has not given complete and targeted consideration to this

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  • A wing design method considering pneumatic and structural multi-type design variables
  • A wing design method considering pneumatic and structural multi-type design variables
  • A wing design method considering pneumatic and structural multi-type design variables

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Embodiment

[0046] In order to fully understand the characteristics of the invention and its applicability to engineering practice, the present invention aims at Figure 5 The wing model shown performs aero-structural integrated design. The overall parameters of the wing are: wing area S=12.705m 2 , Aspect ratio AR = 1.63, leading edge sweep angle SWP0D0 = 59°, tip root ratio TR = 0.1615, the torsion angle of 7 aerodynamic sections along the span direction {α i ,i=1...7}={6.7166°,3.0131°,-0.6782°,-1.2067°,-2.0301°,-2.5773°,-3.7500°}, dihedral angle {θ i ,i=1...7}={0.0000°, 0.00807°, 0.05729°, 0.10679°, 0.31130°, 0.51217°, 0.83520°}, and the airfoil point data of NACA0012 airfoil.

[0047] First, set the number of sections to be acquired (41) and the airfoil point data on each aerodynamic end face (101 on the upper airfoil, 101 on the lower airfoil), and normalize the initial partial section of the airfoil Point data (ψ, η, z) into the equation Solve the shape function by the least square met...

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Abstract

The invention discloses a wing design method considering pneumatic and structural multi-type design variables, which comprises the following steps of: firstly, constructing a parameterized shape by utilizing a three-dimensional category / shape function according to a shape control variable obtained in a pneumatic design process, obtaining Cartesian coordinates of a pneumatic shape point, and generating a smooth pneumatic shape curved surface on the basis of the shape point; By picking up controllable design variables in the wing structure tree, the internal structure arrangement of the wing under a given appearance is realized; By utilizing a neighborhood interpolation technology represented by RBF interpolation and taking an aerodynamic shape as a constraint, efficient follow-up matching of the structure arrangement and the shape parameters is realized; and finally completing the three-dimensional wing design under the coupling effect of the pneumatic / structural subject according to the independent or dependency relationship of different types of design variables on the model tree through a file positioning analysis method. Contents of two subjects of a pneumatic / structure are considered, linkage updating of the model is achieved, and the method has the advantages of being high in universality, wide in application range and convenient to use.

Description

Technical field [0001] The present invention relates to a comprehensive modeling technology of aerodynamics and structural mechanics of a winged aircraft, in particular to a three-dimensional wing external and internal morphological characterization technology that considers the combination of category / shape function technology and software secondary development technology and based on The wing shape / structure coordinated change of the neighborhood conversion interpolation technology is used to obtain a high-efficiency and high-precision parameterized model of multi-type design variables that meets multi-disciplinary and multi-physics analysis. Background technique [0002] In the aerodynamic shape design of aerospace vehicles, the parameterized aerodynamic shape model is the basis of aerodynamic optimization design and aerodynamic index analysis. In the traditional design concept, on the one hand, based on the airfoil database data, the aerodynamic cross-sections at different po...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCY02T90/00
Inventor 王晓军丁旭云倪博文李豪罗振先黄勇
Owner BEIHANG UNIV
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