Quick response pressure-sensitive paint temperature effect correction method

Abstract

The invention discloses a quick response pressure-sensitive paint temperature effect correction method, and belongs to the technical field of aerospace aerodynamics wind tunnel tests and image data processing, and the method comprises the steps: calibrating a pressure-sensitive paint, and calculating a calibration coefficient of a relation among three variables of a light intensity ratio, pressure and temperature according to calibration data; test preparation; performing a wind tunnel test, collecting a background image and a windless image, and obtaining a windy image and pulsating pressure sensor data; preprocessing the image data; automatically registering the image; the image data and the pulsating pressure data are aligned; calculating the position temperature of the pulsating pressure sensor according to the pressure measurement value of the pulsating pressure sensor and the light intensity ratio; according to the position of the pulsating pressure sensor and the corresponding temperature, interpolating to obtain the temperature distribution of the whole measurement area; correcting the temperature effect; and storing the pressure data in blocks. The method is suitable for a quick response pressure-sensitive paint test, temperature effect correction is carried out on test data, and the pressure measurement precision of the quick response pressure-sensitive paint is remarkably improved.

Description

technical field [0001] The invention belongs to the technical field of aerospace aerodynamic wind tunnel test and image technology processing, and more specifically, the invention relates to a temperature effect correction method of a fast-response pressure-sensitive paint. Background technique [0002] In terms of military affairs, when flying weapons are cruising, strong pulsating pressures are likely to be generated in parts of protrusions such as antennas, large-gradient non-smooth parts such as projectile shoulders and magazines, and the gap between wings and auxiliary fuel tanks. , the smooth airframe and wing surfaces will also produce non-negligible high-intensity pulsating pressure due to unsteady turbulence, which induces buffeting response of the aircraft structure, which may cause fatigue or even damage to the aircraft structure, reducing the reliability and service life of built-in instruments. , affecting the service life and flight safety of the aircraft struc...

AI Technical Summary

Problems solved by technology

The pulsating pressure sensor has high measurement accuracy, but there are also many defects: 1. Because the sensor will inevitably protrude or sag on the surface of the model, it will interfere with the incoming flow, resulting in inaccurate measurement of pulsating pressure and noise; 2. Installing pulsating pressure The sensor needs to make holes and slots on the model at the installation position and the wiring channel, which increases the difficulty of model design and processing, and increases the cost of model design and processing; 3. The pulsating pressure sensor can only measure several points on the surface of the model. The spatial resolution is very low, and it is impossible to complete the requirements of the full-area surface measurement, and it is impossible to obtain the high-resolution acoustic characteristics of the model surface and the details of the flow field structure

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