Hypersonic velocity pointed conical appearance heat flux density modeling approach based on functional optimization

Abstract

The invention relates to a hypersonic velocity pointed conical appearance heat flux density modeling approach based on functional optimization. The approach comprises the steps of utilizing a hypersonic velocity calorimetric wind tunnel to conduct a ground calorimetric test on n pointed conical models with different shrink ratios of an aircraft; obtaining heat flux density distribution laws of n models with different shrink ratios in the hypersonic velocity calorimetric wind tunnel to obtain heat flux density test values Qwi respectively, wherein 1<=i<=n; adjusting wind tunnel test parameters in the hypersonic velocity calorimetric wind tunnel, and obtaining a first set of heat flux density test values Qwij, wherein j is wind tunnel test times; obtaining heat flux density distribution laws of a first set of aircrafts; totally obtaining heat flux density distribution laws Qwk of k sets of aircrafts; applying a functional optimization algorithm, introducing a wind tunnel quality variable a and a calibration model parameter b, conducting iterative operation on Qwk, solving an optimal spatial alternation, and obtaining pointed conical heat flux density model Qw. The hypersonic velocity pointed conical appearance heat flux density modeling approach based on the functional optimization avoids one-sidedness of a modeling method in the prior art and interference of human experience factors.

Description

technical field [0001] The invention relates to a method for modeling heat flux density of a hypersonic cone shape based on functional optimization, and belongs to the field of modeling. Background technique [0002] Under high-altitude and hypersonic conditions, the surface of the aircraft will generate aerodynamic heat with strong destructive force. Difficult to model. The sharp cone is a typical shape, and the accurate description of its heat flux has fundamental and guiding significance for the design of the entire aircraft. [0003] At present, for hypersonic heat flux, research is being carried out in three aspects: engineering approximation theory methods, fluid calculation numerical simulation methods, and ground / flight test methods. Since the 1970s, the United States has developed a series of aerothermal engineering approximation method software (AEROHEAT, LATCH, MINVER, UNLATCH2, UNLATCH3, etc.) and fluid calculation numerical simulation method software (DPLR, FU...

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Problems solved by technology

[0004] Throughout the country and abroad, although reliable heat flux data can be obtained under local conditions, due to the different simulation ranges of flow parameters in different wind tunnels, the heat flux reflects different physical mechanisms, and the distribution of heat flux is not uniform. Modeling is mainly based on certain experience and assumptions, and engineering approximation and fitting are given, but there is still a lack of objective and universal theoretical methods

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