Parameterization method for deformation appearances of front and rear edges of wing airfoil meeting structural constraints

Abstract

The invention discloses a parameterization method for deformation appearances of front and rear edges of a wing airfoil meeting structural constraints. According to the method, the deformation appearances of the front and rear edges of the wing airfoil are represented by adopting camber lines and thickness lines corresponding to the front and rear edges of the wing airfoil. The method is applied to the design of the deformation shape of the front edge and the rear edge of the variable camber wing section, the problems that an efficient aerodynamic configuration structure cannot be achieved and the aerodynamic efficiency of the structure achievable shape is low can be effectively solved by accurately describing the configuration characteristics and the structure constraint characteristics at the same time, and the aerodynamic design efficiency of the front edge and the rear edge deformation shape is greatly improved; and the engineering realizability of front and rear edge deformation appearances is ensured.

Description

technical field [0001] The invention belongs to the field of aircraft design, and in particular relates to a method for parameterizing the deformed shape of the leading and trailing edges of wing airfoils satisfying structural constraints. Background technique [0002] With the continuous improvement of the technical maturity of the flexible deformation structure of the wing, the adaptive deformation technology of the front and rear edges of the wing based on the flexible structure has received more and more attention. The expression of the shape of the edge deformation mainly adopts two ideas based on the different content of concern: one is to focus on the aerodynamic gains of the front and rear edge deformation, and the conventional two-dimensional curve parameterization method is mainly used for the shape description of the front and rear edges, which can only guarantee The described geometric shape is smooth and has enough design space, but the geometric shape expressed...

AI Technical Summary

Problems solved by technology

[0002] With the continuous improvement of the technical maturity of the flexible deformation structure of the wing, the adaptive deformation technology of the front and rear edges of the wing based on the flexible structure has received more and more attention. The expression of the shape of the edge deformation mainly adopts two ideas based on the different content of concern: one is to focus on the aerodynamic gains of the front and rear edge deformation, and the conventional two-dimensional curve parameterization method is mainly used for the shape description of the front and rear edges, which can only guarantee The described geometric shape is smooth and has enough design space, but the geometric shape expressed by different parameter combinations lacks correlation, and the achievability of the structure for different deformation shapes cannot be guaranteed; the second is to focus on the internal deformation structural characteristics of the front and rear edges, The deformation shape of the front and rear edges is mainly determined by the shape of the internal structure, and there is a problem that the ability to describe the deformation shape of the front and rear edges is obviously insufficient

In order to solve the problem that the aerodynamics and the structure cannot be considered in the parameterization of the deformation shape of the leading and trailing edges of the airfoil in the research of the adaptive deformation technology of the leading and trailing edges of the wing, it is necessary to establish a parameterization of the shape of the deformation of the leading and trailing edges of the wing airfoil that meets the structural constraints. method, so that it can not only have enough deformation space, but also ensure the realizability of the structure

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