Ablation test method of thermal protection structure of high supersonic velocity aircraft

Abstract

The invention discloses an ablation test method of a thermal protection structure of a high supersonic velocity aircraft. The ablation test method of the thermal protection structure of the high supersonic velocity aircraft includes the following steps: placing the thermal protection structure of the high supersonic velocity aircraft in an electric arc wind tunnel to conduct an ablation test. In the ablation test process, a computer utilizes a synchronous device to drive two cameras to conduct collection on an image pair, a filter device is adjusted in real-time to conduct light intensity adjustment to obtain an optical image quality when collection is conducted, and the computer processes the image pair which is collected at the same moment to obtain a three-dimensional morphology information of a measured object at the moment. According to three-dimensional morphology information of the measured object at different moment, ablation amount of the measured object is calculated. The ablation test method of the thermal protection structure of the high supersonic velocity aircraft is simple in operation and low in cost, can overcome extremely bad experiment conditions of the electric arc wind tunnel and can obtain surface morphology change course and ablation of the thermal protection structure of the high supersonic velocity aircraft in real-time.

Description

technical field [0001] The invention relates to an ablation test method for testing the ablation of a thermal protection structure of a hypersonic vehicle, belonging to an aerospace experiment method. Background technique [0002] The shape of the future hypersonic vehicle is complex. Due to the interaction between the shock wave and the shock wave, and between the shock wave and the boundary layer, the heat flow distribution on the surface of the model is also relatively complicated due to the surrounding flow field, which also brings extremely complicated thermal deformation. An important goal of thermal protection structure design is to control the thermal deformation of the structure within a reasonable range, and the basis for the control is to test and study the ablation performance of the thermal structure model during the test. [0003] The ablation test of the thermal protection structure commonly used at present mainly includes the measurement of the temperature, p...

AI Technical Summary

Problems solved by technology

These methods all need to lay components in the test piece, so it brings great inconvenience to the measurement.

Cauty et al. used the ultrasonic method to measure dynamic ablation. The principle is to measure the dynamic change of the model surface during the ablation process according to the time and speed of ultrasonic propagation in the object under test. However, due to the close relationship between ultrasonic speed and temperature, the propagation The relationship between time and ablation thickness is difficult to determine

Wang Xiliang et al. developed a real-time measurement method for heat-resistant layer ablation based on X-ray real-time diagnostic technology, and measured the instantaneous ablation rate of the heat-resistant layer under the erosion of high-concentration particle flow. very high

[0005] It is extremely difficult to measure the shape and ablation amount of the thermal protection structure model in the arc wind tunnel ablation experiment. Due to the extremely harsh experimental conditions such as high temperature and arc interference, the previous measurement methods are basically unable to achieve this problem.

Some of the other limited measurement methods need to process the measured object itself, pre-embed the ablation potentiometer device, etc., or require expensive equipment, and these methods cannot realize the ablation morphology and ablation of the thermal protection structure model. Quantitative global information extraction

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