A method for testing the pressure on the outer surface of a cabin

Abstract

The invention discloses a method for testing the pressure on the outer surface of a cabin. The method for testing the pressure on the outer surface of the cabin includes: obtaining the pressure data on the outer surface of the cabin to be tested by means of computational fluid dynamics; testing the test model of the cabin to be tested through a pressure test, thereby obtaining the pressure data on the outer surface of the test model ; Judging whether there is a distribution point at the position of the pressure mutation in the experimental model in the pressure test; if not, then select the pressure data at the position corresponding to the pressure mutation position in the pressure test in the computational fluid dynamics method, The pressure data is used as the pressure data at the pressure mutation position in the pressure test; thereby integrating the pressure data at other distribution points in the pressure test and the pressure data at the pressure mutation position in the computational fluid dynamics method, thereby Obtain pressure data on the outer surface of the entire cabin. The pressure data on the outer surface of the chamber obtained by this method is accurate and reliable.

Description

technical field [0001] The invention relates to the technical field of aircraft strength testing, in particular to a pressure testing method for the outer surface of a cabin. Background technique [0002] At present, the pressure distribution on the outer surface of the nacelle of the aircraft is usually determined by a CFD (computational fluid dynamics) method or a pressure test method. [0003] However, when the CFD method is used for calculation, the problems of local dispersion and inaccurate integration results appear when the angle of attack of the aircraft is too large or the angle of sideslip is slightly large. [0004] However, if the pressure test method is used, since the model usually needs to be scaled down, there will be a problem that the nacelle is too small and the distribution points are limited, that is, generally, the distribution points cannot be located at the lip and under the wing where the pressure changes suddenly, resulting in the important pressur...

AI Technical Summary

Problems solved by technology

[0003] However, when the CFD method is used for calculation, when the aircraft angle of attack is too large or the sideslip angle is slightly large, it shows the problem of local dispersion and inaccurate integration results

[0004] However, if the pressure test method is used, since the model usually needs to be scaled down, there will be a problem that the nacelle is too small and the distribution points are limited, that is, generally, the distribution points cannot be located at the lip and under the wing where the pressure changes suddenly, resulting in the important pressure distribution in this part.

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