Hypersonic velocity wing robust optimization design method considering machining errors

A hypersonic and robust optimization technology, applied in computing, special data processing applications, instruments, etc., can solve the problems of poor robustness and low efficiency of optimization results

Active Publication Date: 2016-11-16
BEIHANG UNIV
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Problems solved by technology

[0004] The technical problem to be solved by the present invention is: Aiming at the problems of low efficiency of traditional hypersonic wing optimization design method and poor robustness of optimization results, a robust optimization design method of hypersonic wing considering machining error is proposed

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  • Hypersonic velocity wing robust optimization design method considering machining errors
  • Hypersonic velocity wing robust optimization design method considering machining errors
  • Hypersonic velocity wing robust optimization design method considering machining errors

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[0071] 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.

[0072] (1) Taking the wing of a hypersonic aircraft like X-37B as the research object, first determine the plane profile parameters of the hypersonic wing, including the wing root chord length C r , aileron width C a , wing aspect ratio AR and slightly root ratio TR. In addition, the wingtip chord length C t =C r · TR, wing half-span The plane profile of the wing is as figure 1 The initial values ​​of relevant parameters are shown in Table 4.

[0073] Table 4 Initial values ​​of wing plane profile parameters

[0074]

[0075] (2) The Clark-Ys airfoil is used as the standard airfoil (see figure 2 ), use the type function / shape function conversion method to set the ex...

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Abstract

The invention discloses a hypersonic velocity wing robust optimization design method considering machining errors and belongs to the technical field of optimization design. The method comprises the following steps: fully considering geometric machining errors existing in hypersonic velocity wing design, and realizing quantitative characterization of a machining error coefficient by utilizing an interval vector under the condition that a probability density function of machining error parameters is unknown; establishing aerodynamic configuration of the hypersonic velocity wing through a parametrization method, and performing nonstructured surface mesh division; combining an interval parameter vertex method with an aerodynamic/thermal engineering algorithm, and calculating upper and lower bound of intervals of total stagnation point heating capacity and lift-drag ratio of the wings; and on the basis, establishing a multi-target interval robust optimization model, and performing optimization design on the wing shape by using a genetic algorithm. The numerical result shows that according to the method, the total stagnation point heating capacity of the designed wing is reduced under the precondition that lift-drag ratio constraint of the wing is maintained; meanwhile, a fluctuation range of the total stagnation point heating capacity is narrowed, and a new thought is provided for shape design of the hypersonic velocity wing.

Description

technical field [0001] The invention relates to the field of wing optimization design, in particular to a hypersonic wing robust optimization design method considering machining errors. Background technique [0002] Aerodynamic shape optimization is an important link in the design process of a hypersonic wing. When optimizing the aerodynamic shape of a hypersonic wing, there are two distinct methods: deterministic optimization and robust optimization. Deterministic optimization is to optimize the shape parameters of the wing in a certain flight state, ignoring various uncertain factors in the wing design process, so as to maximize the aerodynamic performance of the wing in this state. However, due to the limitations of processing technology and manufacturing level, the aerodynamic shape of the hypersonic wing has geometric uncertainties caused by processing errors, so the optimal solution obtained by the deterministic optimization method is more sensitive to these uncertain...

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F17/50
CPCG06F30/15Y02T90/00
Inventor 邱志平郑宇宁王晓军王磊王睿星许孟辉李云龙仇翯辰姜南
Owner BEIHANG UNIV
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