Method for obtaining transient temperature field of gradient composite heat insulation structure

Abstract

The invention discloses a method for obtaining a transient temperature field of a gradient composite heat insulation structure, and belongs to the technical field of thermal protection of hypersonic aircraft engines. The method comprises the following steps: providing a plurality of material layers used for a gradient composite heat insulation structure, and arranging all material layers in sequence from high temperature to low temperature; establishing a one-dimensional transient temperature field calculation model for the gradient composite heat insulation structure; giving a control equation for describing the heat transfer process of the gradient composite heat insulation structure, wherein the control equation is described through a plurality of partial differential equations; discretizing the partial differential equations by adopting an implicit difference calculation format to obtain a discrete linear equation set; solving the discrete linear equation set; the method can be used for rapidly predicting the transient temperature field of the gradient composite heat insulation structure of the wall surface of a high-heat-flux combustion chamber of a hypersonic aircraft, can analyze the influence of different material combination schemes and thermophysical parameters of different materials on wall surface heat insulation, and provides effective technical support for thermal protection design of an engine.

Description

technical field [0001] The invention relates to the calculation of the temperature field of the heat insulation structure on the wall of the combustion chamber of a rocket engine, a ramjet engine, a detonation engine, etc., and specifically relates to a method for obtaining the transient temperature field of a gradient composite heat insulation structure, which belongs to a hypersonic aircraft engine Thermal protection technical field. Background technique [0002] With its advantages of high maneuverability, fast flight speed and long-range precision strike, hypersonic vehicles have become the main development direction of aerospace in various countries in the world. When a hypersonic vehicle is flying, the engine works under the extreme thermophysical conditions of high speed, high temperature and high intensity combustion, especially the gas temperature in the combustion chamber can be as high as 2500-3000K, and the high temperature gas has strong oxidation and denudation...

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Problems solved by technology

[0005] Purpose of the invention: The present invention discloses a method for obtaining the transient temperature field of a gradient composite heat insulation structure. By establishing a physical and mathematical model of the heat insulation structure and using the finite difference method to numerically simulate the transient temperature field, it can be conveniently and quickly Predict the temperature change of the heat insulation structure, so as to realize the evaluation of the heat insulation performance of the heat insulation structure, and solve the technical problem in the prior art that the passive heat protection simulation needs to be obtained through high-cost experimental methods

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