Metal fiber surface combustion structure thermal test method and device

Abstract

The invention relates to a metal fiber surface combustion structure thermal test method and device, and the method comprises the following steps: a, mixing fuel gas with a gas combustion improver to form a mixed gas, and enabling the mixed gas to be conveyed along at least one gas path; b, igniting mixed gas at the tail end of the gas path, enabling combustion flame to penetrate through an attachment body, wherein all points of at least one surface of the attachment body correspond to all points of the heated surface of the test piece, and therefore fuel gas formed through combustion is sprayed to the heated surface of the test piece to heat the heated surface; and c, measuring thermal load parameters of the heated surface of the test piece corresponding to each gas path in real time, andcontrolling the flow of the mixed gas in the corresponding gas path in real time according to the thermal load parameters. According to the invention, the attachment formed by weaving the metal fibersis used as an attachment of the mixed gas combustion flame, so that the combustion surface can adapt to the complex shape of the test piece, and full-size simulation is 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 metal fiber surface combustion. Background technique [0002] With the development of aerospace technology, hypersonic vehicles have become an important development direction of major aerospace countries. This type of aircraft will be subjected to thermal loads brought 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 used. The leading edge, wing rudder structure, air inlet, nozzle and other key parts of this type of aircraft adopt complex surface design, and the surface thermal load distribution gradient is large during hypersonic flight, and the size is often large. Maneuvering or super-maneuvering orbit changes are often required, and the thermal load h...

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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