Method for hypersonic wing aerodynamic/thermal analysis in view of geometric uncertainty

Abstract

The invention discloses a method for hypersonic wing aerodynamic/thermal analysis in view of geometric uncertainty. A sample point of uncertain parameters is established according to a Bernstein polynomial approximation model; an aerodynamic/thermal response value, corresponding to a wing shape, of the sample point is calculated by utilizing an aerodynamic/thermal engineering algorithm in a given flight condition; and a fitting coefficient of the polynomial approximation model is obtained by applying a least square method. Based on this, a maximum/minimum value point, about each uncertain parameter, of the aerodynamic/thermal response value is solved by utilizing the established polynomial approximation model; combination is performed to form a vector of a maximum/minimum point; and finally an interval upper bound and an interval lower bound of the aerodynamic/thermal response value are obtained, thereby realizing the hypersonic wing aerodynamic/thermal analysis in view of the geometric uncertainty. An interval boundary obtained in the method is well matched with that obtained in a Monte-Carlo method, and interval envelopment can be realized, so that a new idea is provided for overall design of the hypersonic wing shape.

Description

technical field [0001] The invention relates to the technical field of hypersonic aircraft design, in particular to an aerodynamic / thermal analysis method for a hypersonic wing considering geometrical uncertainty. Background technique [0002] The aerodynamic shape modeling method is an important link in the design and development of hypersonic vehicles. In order to improve modeling efficiency and accuracy, it is generally necessary to control the number of design parameters and adopt parametric modeling methods. Taking the geometric modeling method of airfoil shape as an example, the traditional parametric geometric modeling mainly relies on CAD methods (B-spline curve, NURBS curve and quadratic curve method), but this modeling method has too many expression parameters. It is not conducive to the simplification of the analysis models of various disciplines in the conceptual design. In contrast, the CST (Class function and Shape function Transformation) method based on cla...

AI Technical Summary

Problems solved by technology

The non-probability interval method has achieved certain results in the analysis of static and dynamic characteristics of structures, but it is still in its infancy in modeling the aerodynamic shape of hypersonic aircraft wings, and the relevant research results are very limited.

At the same time, when there is uncertainty in the aerodynamic shape of the wing, especially the geometric fluctuations in the position of the leading edge of the wing, it will cause deviations in the aerodynamic / aerothermal performance of the wing. Such fluctuations or deviations are detrimental to flight safety

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