Airfoil robust optimization design method based on non-probability interval analysis model

A technology of interval analysis and design method, which is applied in gene models, calculations, instruments, etc., and can solve the problems of poor robustness and low efficiency of optimization results

Active Publication Date: 2016-06-29
BEIHANG UNIV
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Problems solved by technology

[0004] The technical problem to be solved in the present invention is: Aiming at the problems of low efficiency of the traditional airfoil optimization design method and poor robustness of the optimization result, a robust optimization design method of the airfoil based on the non-probability interval analysis model is proposed

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[0057] Hereinafter, design examples of the present invention will be described in detail with reference to the accompanying drawings. It should be understood that the selected examples are only for illustrating the present invention, rather than limiting the protection scope of the present invention.

[0058] (1) With the NACA0012 airfoil as the initial airfoil, use the type function / shape function conversion CST method to set the expression of the parameterized airfoil curve, and the geometric meaning of some parameters is as follows figure 1 shown.

[0059] (2) Extract the geometric parameters in the CST method as optimal design variables, and the value ranges of each optimal variable are shown in Table 3:

[0060] Table 3 Value range of airfoil optimization design variables

[0061]

[0062] (3) The Mach number Ma of the future flow is used as an uncertain design parameter, its interval is Ma∈[0.74,0.76], and the center value is Ma c =0.75, the interval radius is ΔMa=...

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Abstract

The present invention discloses an airfoil robust optimization design method based on a non-probability interval analysis model, and belongs to the technical field of optimization design. According tothe method disclosed by the present invention, an indefinite factor in airfoil design is fully considered, and in the case that a probability density of an indefinite parameter is unknown, quantifiedcharacterization of the indefinite parameter is implemented by using an interval vector. By means of a sample point experiment, a mapping relationship among an airfoil design variable, the indefiniteparameter and an aerodynamic coefficient is established. On this basis, upper and below interval boundaries of the airfoil aerodynamic coefficient are obtained by using a non-probability interval analysis model. Robust optimization model is established, then airfoil optimization design is implemented by using genetic algorithm. As numerical prediction indicates, on the premise of maintaining an airfoil lift coefficient and a geometric shape constraint, the method disclosed by the present invention reduces a resistance coefficient of a designed airfoil, reduces a variation range of the resistance coefficient and provides a new idea for airfoil optimization design.

Description

technical field [0001] The invention relates to the field of airfoil optimization design, in particular to an airfoil robust optimization design method based on a non-probability interval analysis model. Background technique [0002] When performing aerodynamic optimization on an airfoil, there are two distinct methods: the deterministic optimal design and the robust optimal design. Deterministic optimization design is to construct the corresponding airfoil profile under a specific flight state to maximize the aerodynamic performance of the airfoil in this state. It is currently a widely used airfoil optimization method. However, in actual cruising, uncertain factors such as atmospheric incoming flow velocity, air pressure, temperature, and gusts will cause the aircraft service environment to deviate from the design expectation, so that the optimal solution obtained by the deterministic optimization method is relatively stable for these uncertain factors. more sensitive. D...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50G06N3/12
CPCG06F30/367G06N3/12
Inventor 邱志平郑宁宁王晓军王睿星许孟辉李云龙王冲王磊
Owner BEIHANG UNIV
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