Thermal test method and device for burning structure on metal fiber surface

Abstract

The invention relates to a method and device for thermal testing of metal fiber surface combustion structures. The method comprises the following steps: a. mixing fuel gas with a gas oxidant to form a mixed gas, so that the mixed gas is transported along at least one gas path; b. at the end of the gas path The mixed gas is ignited, and the combustion flame passes through the attachment, and each point on at least one surface of the attachment corresponds to each point on the heated surface of the test piece, so that the gas formed by combustion is injected onto the heated surface of the test piece, and the heating surface is affected. Perform heating; c. Measure the thermal load parameters of the heated surface of the specimen corresponding to each gas path in real time, and control the flow rate of the mixed gas in the corresponding gas path in real time according to the thermal load parameters. In the invention, the attachment body woven by metal fibers is used as the attachment of the mixed gas combustion flame, so that the combustion surface can be adapted to the complex shape of the test piece, and full-scale simulation can be realized.

Description

technical field [0001] The invention relates to the technical field of thermal testing, in particular to a structural thermal testing method and device based on surface combustion of metal fibers. Background technique [0002] With the development of aerospace technology, hypersonic vehicles have become an important development direction of various aerospace powers. Such aircraft will be subjected to the thermal load caused by hypersonic airflow during flight. In order to ensure the safety of the aircraft and keep the interior of the aircraft within the allowable temperature and pressure range, a thermal protection structure must be adopted. The leading edge, rudder structure, air intake, nozzle and other key parts of this type of aircraft are designed with complex surfaces. During the hypersonic flight, the surface thermal load distribution gradient is large, and the size is often large. It is often necessary to perform maneuvering or super maneuvering orbit change, and th...

AI Technical Summary

Problems solved by technology

However, in response to the new requirements of the aerothermal simulation of the above-mentioned complex structures, the traditional thermal test method has many deficiencies

For example, the current test system is difficult to simulate the large gradient heat flow distribution on the surface and the high impact rate nonlinear time-varying heat flow simulation ability

From the perspective of traditional test methods, high-temperature wind tunnels mostly use step-type thermal power up and down methods to realize unsteady thermal environment simulations, so it is difficult to accurately simulate rapidly changing complex nonlinear thermal environment history; while radiation heating equipment such as quartz lamps, although Excellent electrical control performance, which can realize nonlinear time-varying heat flow simulation with high impact rate, but it is difficult to accurately simulate the large gradient heat flow distribution on the surface of the structure

Moreover, limited by the installation form of the test system, it is difficult for the current system to adapt to the heat flow loading on the surface of large-scale complex structures.

The size of traditional high-temperature wind tunnel specimens is limited, and it is difficult to realize full-scale simulation of components; while radiation heating equipment such as quartz lamps are installed in partitions, it is difficult to adapt to complex aerodynamic shapes

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