A parameterization method suitable for designing a non-axisymmetric laminar flow nacelle

A non-axisymmetric, parametric technology, applied in computing, electrical digital data processing, special data processing applications, etc., can solve problems such as long computing time, achieve high efficiency, strong robustness, and easy parallelism

Inactive Publication Date: 2019-05-07
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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Problems solved by technology

This method can be easily integrated into the traditional modeling system, can maintain the continuity of the guide vector at any order, and can be used as a wh

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  • A parameterization method suitable for designing a non-axisymmetric laminar flow nacelle
  • A parameterization method suitable for designing a non-axisymmetric laminar flow nacelle
  • A parameterization method suitable for designing a non-axisymmetric laminar flow nacelle

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Embodiment 1

[0038] This embodiment provides a parametric method suitable for the design of a non-axisymmetric laminar flow nacelle, such as figure 1 shown, including the following steps:

[0039] (1) if Figure 2a-2c As shown, the nacelle to be deformed is divided into computational grids for numerical simulation; specifically, a non-axisymmetric laminar flow nacelle is used as the nacelle to be deformed, and a structured grid or an unstructured grid can be used for numerical simulation The calculation grid of the numerical simulation is divided, and the calculation grid nodes of the nacelle surface are extracted from the calculation grid of the numerical simulation.

[0040] (2) if Figures 3a-3c As shown, a control frame is built on the surface of the nacelle to be deformed and control points are arranged; the control frame can only be built using a structural grid, and the coordinate information of the control points of the control frame is exported in the form of a grid file.

[00...

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Abstract

The invention discloses a parameterization method suitable for designing a non-axisymmetric laminar flow nacelle. The parameterization method comprises the following steps: step 1, dividing a to-be-deformed nacelle into calculation grids for numerical simulation; 2, building a control frame on the surface of the nacelle to be deformed, and arranging control points; Step 3, giving a displacement variation of the control point according to a demand; 4, calculating the displacement variation of a calculation grid node on the surface of the nacelle to be deformed according to the control point onthe surface of the nacelle to be deformed, the displacement variation of the control point and the calculation grid node by utilizing a radial basis function interpolation method; And 5, superposing the coordinates of the calculation grid nodes on the surface of the nacelle to be deformed and the displacement variation of the calculation grid nodes on the surface of the nacelle to be deformed to obtain the deformed nacelle. According to the method, the control framework of the surface of the nacelle to be deformed is built, the control points are arranged, the radial basis function interpolation technology is adopted, and the laminar nacelle configuration after deformation is quickly and accurately calculated according to the displacement variation of the control points.

Description

technical field [0001] The invention relates to the field of aircraft aerodynamic optimization design and shape parameterization, in particular to a parameterization method suitable for the design of a non-axisymmetric laminar flow nacelle. Background technique [0002] In the process of aerodynamic optimization design of aircraft and its components, the nature of the aerodynamic shape parameterization method has a very profound impact on the calculation time, the nature and scope of the design space. The calculation amount of searching the design space increases exponentially with the increase of the design parameters. The parameterization method selected for the optimization design must be able to use as few parameters as possible and a sufficiently high Precision to define the geometric shape to reduce the amount of calculation in the design process. [0003] Existing parameterization methods can be divided into two categories: [0004] 1) Direct geometric shape paramet...

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Application Information

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IPC IPC(8): G06F17/50
Inventor 刘红阳黄江涛周铸余婧余雷
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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