Non-linear evolution calculating method of zirconium diboride-silicon carbide composite material oxide

Abstract

The invention relates to a non-linear evolution calculating method of zirconium diboride-silicon carbide composite material oxide. The non-linear evolution calculating method of zirconium diboride-silicon carbide composite material oxide includes the steps: 1) performing isothermal oxidation tests for no less than 3 insulation time quantums on a zirconium diboride-silicon carbide composite material test sample; 2) cooling the sample to be tested to an indoor temperature and processing the sample to be tested to obtain a profile or cross section structure, drying and saving, and preventing the oxide shedding; 3) determining the oxide layered structure of the profile or cross section of the test sample; 4) measuring the thickness of each oxide layer; 5) according to difference of the oxide structures, respectively establishing differential equations that the thickness of the oxide evolves following the time; 6) solving the differential equations to obtain theoretical calculating values of the thickness of oxides; 7) by changing characteristic parameter values, performing iterative computations until the deviation absolute values between the thickness of all the test oxides and the thickness of the calculated oxides are all smaller than a specified accuracy, and determining the characteristic parameters of the equations, satisfying the accuracy requirement, according to the results of iterative computations; and 8) fixing the characteristic parameters of the differential equations, and solving the oxide thickness quantitative evolution rules in different temperatures and any oxidation time.

Description

technical field [0001] The invention belongs to the field of high-temperature heat-resistant materials and aircraft thermal protection design, and in particular relates to a method for calculating the nonlinear evolution of an oxide layer of a zirconium diboride-silicon carbide ultra-high temperature ceramic composite material. Background technique [0002] Zirconium diboride-silicon carbide ultra-high temperature ceramic composite materials are mainly used for thermal protection of high-temperature parts such as the nose cone of hypersonic aircraft, the leading edge of wing rudder, and the support plate of scramjet combustion chamber. Because it is related to the flight safety of high-temperature heat-resistant materials and aircraft thermal protection systems, the oxide layer thickness evolution and performance prediction and evaluation methods of zirconium diboride-silicon carbide composite materials in high-temperature aerobic environments are key technologies for enginee...

AI Technical Summary

Problems solved by technology

There are two problems with this calculation method when predicting the oxide layer structure and its thickness evolution. Parabolic and linear laws; second, the calculation method cannot reflect the phenomenon of multi-layer oxide layer structure observed in the experiment, and the calculation model deviates from the physical reality

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