Test model surface temperature correction method

Abstract

The invention is applicable to the technical field of wind tunnel tests, and provides a test model surface temperature correction method. The method comprises the following steps: acquiring a temperature value of each temperature measurement point, and if a temperature factor of the temperature measurement point is not less than a preset parameter, determining that the temperature measurement point is a failure temperature measurement point; and if the temperature factor of the temperature measurement point is smaller than the preset parameter, determining that the temperature measurement point is an effective temperature measurement point. The temperature factor is the stability degree of the temperature value of the temperature measurement point in a preset time length; taking the temperature value of the reference temperature measurement point as the correction temperature of the failure temperature measurement point; and the reference temperature measurement point is a temperature measurement point having the same relative distance with the failure temperature measurement point in the effective temperature measurement area, and the relative distance is the distance between a straight line where the temperature measurement point is located in the temperature measurement direction and a front edge line angular point. According to the test model surface temperature correction method, the surface temperature of the anti-icing and deicing component can be accurately measured, and the anti-icing and deicing test efficiency and accuracy are improved.

Description

technical field [0001] The invention relates to the technical field of wind tunnel tests, in particular to a method for correcting the surface temperature of a test model. Background technique [0002] The icing of aircraft components will destroy the aerodynamic shape of the aircraft and lead to a decrease in aerodynamic characteristics, which is one of the more eye-catching hazards in flight safety accidents. The main purpose of the anti-icing verification test of aircraft components is to assess the anti-icing characteristics of components, which is currently mainly completed by icing wind tunnels. Among them, the hot air anti-icing mainly introduces the hot air generated by the aircraft engine into the anti-icing area, and the electric heating anti-icing mainly uses electricity to heat the anti-icing area of ​​​​the corresponding components, so that the surface temperature of the components can be kept or quickly reached above zero. Therefore, the change of the surface ...

AI Technical Summary

Problems solved by technology

[0005] 1. How to accurately measure the surface temperature of anti-icing components in the hot air and electric heating anti-icing tests in the icing wind tunnel in the prior art;

[0006] 2. In the hot air and electric heating anti-icing tests in the icing wind tunnel in the prior art, the anti-icing components are faced with extreme test environments, and extreme test environments often cause damage to the sensors, which in turn affects the accuracy of temperature distribution measurement and affects The process of anti-icing test reduces the test efficiency

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