Database based complex-contour aircraft distributed heat environment parameter prediction method

Abstract

The invention discloses a database based complex-contour aircraft distributed heat environment parameter prediction method and belongs to the field of aircraft heat environment design. The method comprises the steps that an aircraft surface heat flow database is established, order reducing processing is conducted on the database by utilizing a POD method to obtain orthogonal basis vectors of the database, and aircraft surface heat environment parameters can be predicted along a ballistic trajectory by combining with a corresponding basic coefficient interpolation method. The method can really reflect the space distribution characteristics and interference characteristics of the aerodynamic heat environment for all points on the surface of a complex-contour aircraft. Value result comparison shows that the method can remarkably improve the computational efficiency, and prediction precision is not lost. A surface distributed heat flow is provided for calculation of a heat proof temperature field through the points along the ballistic trajectory, more exquisite temperature distribution can be obtained, and accordingly the design level of a whole heat preventing and insulation system is improved.

Description

Technical field: [0001] The invention relates to a method for quickly predicting distributed thermal environment parameters, which is mainly used for rapidly predicting the thermal environment parameters of various parts of an aircraft with complex shapes including wings, rudders and other components along a typical trajectory, and belongs to the field of spacecraft thermal environment design. Background technique: [0002] Prediction of aircraft distributed thermal environment parameters is the premise of anti-insulation system design. The traditional simple-shaped spacecraft distributed thermal environment parameter prediction can be obtained by ground wind tunnel thermal test or aerothermal engineering prediction method. However, the shape of high-speed spacecraft is complex, the airflow mutual interference and shock wave interference characteristics are obvious, and it is difficult to accurately predict the thermal environment. The simulation parameters of the ground wind...

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Problems solved by technology

However, the shape of high-speed spacecraft is complex, the airflow mutual interference and shock wave interference characteristics are obvious, and it is difficult to accurately predict the thermal environment. The simulation parameters of the ground wind tunnel test cannot cover and completely simulate the high-speed flight environment, which is suitable for traditional spherical cones. The aerothermal engineering prediction method for simple shapes is not suitable for complex shapes, especially for the prediction of the thermal environment in local interference areas.

At the same time, large-scale parallel numerical calculations can be used to predict aircraft thermal environment parameters, but the prediction cycle is too long, difficult, and inefficient, and it is difficult to provide data for the design of anti-heat insulation systems in the design phase of aircraft with complex shapes

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