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Airplane Airfoil/Wing Inverse Design Method Based on Artificial Neural Network

An artificial neural network and anti-design technology, applied in computing, special data processing applications, instruments, etc., can solve problems such as different intelligent algorithms and unsatisfactory results, and achieve accurate results

Active Publication Date: 2018-01-12
FUDAN UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, due to the complexity of aircraft component design problems, the intelligent algorithms adopted are not the same, and the results obtained are not satisfactory.

Method used

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  • Airplane Airfoil/Wing Inverse Design Method Based on Artificial Neural Network
  • Airplane Airfoil/Wing Inverse Design Method Based on Artificial Neural Network
  • Airplane Airfoil/Wing Inverse Design Method Based on Artificial Neural Network

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Experimental program
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Embodiment 1

[0031] Design requirements: a cruising Mach number Ma=0.785, the design state is an airfoil with the following parameters:

[0032] Design Mach number Ma =0.71

[0033] Design angle of attack á=2.53

[0034] Reynolds number Re =23,000,000

[0035] First create the airfoil database. In terms of shape structure, the airfoil is relatively simple. In this example, the airfoil database contains 208 reconstructed airfoils. Each airfoil in the database must have good aerodynamic performance; and the geometric configuration of the airfoil must have as large a span as possible, that is, there must be obvious shape differences between the airfoils. Only in this way can the efficiency and integrity of the airfoil database be guaranteed. Table 1 and Table 2 summarize the span of airfoil movement parameters and shape parameters, respectively.

[0036] Table 1 Summary of airfoil aerodynamic parameters

[0037]

[0038] Table 2 Summary of airfoil shape parameters

[0039] ...

Embodiment 2

[0047] Design requirements: The designed lift-to-drag ratio is 25.8, the lift coefficient is 0.5, the form drag coefficient is 0.0105, the induced drag coefficient is 0.009, the shock wave drag coefficient is 0.00017, and the moment coefficient is 0.23; the wing lift coefficient is 0.43, and the drag coefficient is Wing profile with a moment coefficient of 0.0095 and -0.13.

[0048] The main aerodynamic parameters (wing lift-to-drag ratio and lift coefficient) are proposed by the designer, and the rest of the secondary aerodynamic parameters are given by interpolation method with reference to the main aerodynamic parameters and the 214 sets of aerodynamic input ranges in the database, as shown in Table 5.

[0049] Table 5 Summary of wing aerodynamic parameters

[0050] .

[0051] First use the SOM neural network to classify the wing data in the database according to the aerodynamic performance, take out a set of data corresponding to the target aerodynamic input, and select...

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Abstract

The invention belongs to the technical field of aircraft design, in particular to an aircraft airfoil / wing inverse design method based on artificial neural network. The method of the invention includes: using the airfoil / wing PARSEC parameterization method to reconstruct the expression mode of the airfoil / wing, and realizing the reverse design technology through the artificial neural network (ANN) algorithm. The present invention puts aside the cumbersome and inefficient enumeration-iteration method (cut-and-try) of traditional airfoil / wing design, and directly establishes the relationship between the aerodynamic performance of the airfoil / wing and the geometric shape of the airfoil / wing, The parametric inverse design of airfoil / wing based on artificial neural network is realized. The characteristics of the present invention are as follows: firstly, it is fast, and is very suitable for the overall design of the aircraft, especially in the initial design; secondly, due to the application of the artificial neural network algorithm in place, the generated results are very accurate.

Description

technical field [0001] The invention belongs to the technical field of aircraft design, and in particular relates to an aircraft airfoil / wing reverse design method. Background technique [0002] The inverse design method in the design of aircraft components is a kind of "what you need is what you get", which can directly obtain the geometric data of aircraft components that meet the requirements according to the given aerodynamic performance requirements. At present, the usual method of aircraft airfoil / wing design is the traditional, cumbersome and inefficient enumeration-iteration method (cut-and-try), that is, the aerodynamic analysis of the design results of the aircraft airfoil / wing is obtained through calculation. Performance, feed it back to make new changes to geometric data (often such changes are not very related to aerodynamic performance, and show greater randomness), and then perform new aerodynamic performance calculations, so iteratively Until a new airfoil / w...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G06F17/50
Inventor 孙刚王舒悦孙燕杰陶俊
Owner FUDAN UNIV
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