Modeling simulation method for ablation behavior of C/C composite material nozzle of solid rocket engine

Abstract

The invention discloses a modeling simulation method for an ablation behavior of a C / C composite material nozzle of a solid rocket engine, which comprises the following steps of: establishing a multi-scale ablation model of the C / C composite material nozzle, comprehensively considering the processes of gas flow, heat transfer, mass transfer, mechanical erosion of particles, chemical reaction of gas and the like, and obtaining the temperature field, flow field and pressure distribution conditions of the nozzle; analyzing and judging the mechanical erosion degree of each part of the nozzle according to a particle trajectory result, stimulating the retreat and morphology of the microscopic surface of the C / C composite material by utilizing a level set method, and revealing the thermochemical ablation rule of fibers and a matrix. According to the method, the ablation condition of the C / C composite nozzle is comprehensively analyzed from the macroscopic angle and the microscopic angle, and the method has important value for thermal performance research and fine design of the nozzle.

Description

technical field [0001] The invention relates to the technical field of solid rocket motors, in particular to a method for modeling and simulating the ablation behavior of a C / C composite material nozzle of a solid rocket motor on a macro or micro scale. Background technique [0002] C / C composite material is a carbon fiber reinforced carbon matrix composite material with high strength (especially high temperature stability), good thermal shock resistance, good ablation resistance, resistance to gas erosion containing solid particles, and small thermal expansion coefficient It has a series of excellent properties such as low thermal conductivity, and is currently the only high-temperature thermal protection material that can be used above 3000 ° C. It has been widely used in rocket engines, especially solid rocket engine nozzle throat linings, but it has weak oxidation resistance. Limit its high temperature service life. [0003] In recent years, Hf, Ta, Si and other refract...

AI Technical Summary

Problems solved by technology

[0013] This technology does not take multiphase flow into consideration, and simply simplifies the experiment to pure gas phase flow, which is not consistent with the reality, because in reality, alumina particles have a great impact on the denudation of the material surface

In addition, the flow field calculation of this technology does not consider the nozzle material ablation, but in the actual rocket working process, the nozzle wall retreat caused by ablation will change the aerodynamic geometry and surface state of the nozzle, and then affect the flow field parameters near the wall and heat, mass transfer process

Subsequently, the change of gas parameters will strongly react on the material of the nozzle and affect the ablation

Therefore, although the calculation results of this technique provide a certain basis for the analysis of the ablation mechanism, they cannot represent the actual situation.

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