Preparation method of titanium-based composite material thermal protection skin structure

Abstract

The invention provides a preparation method of a titanium-based composite material thermal protection skin structure. SiC fiber cloth, a titanium alloy foil and a titanium alloy plate are laid to prepare a prefabricated blank including alternately arranged siC fiber cloth and titanium alloy foils, a titanium alloy core plate and a titanium alloy lower plate coated with soldering flux that are arranged in sequence from top to bottom; the prefabricated blank is placed in a vacuum hot pressing furnace to be subjected to high-temperature and high-pressure treatment, argon is introduced, superplastic forming is conducted under the conditions that the forming temperature is 870-940 DEG C, the maximum atmospheric pressure is 3.6 MPa, and the time is 80-120 min, finally, the titanium alloy sandwich structure is filled with the thermal insulation material, and a finished product is obtained. The titanium-based composite material thermal protection skin structure prepared by the method is high in tolerable temperature, the sandwich structure is beneficial to weight reduction of the skin structure and subsequent filling of a thermal insulation material, and aerogel filling is beneficial to improvement of the thermal insulation effect of the skin structure.

Description

technical field [0001] The invention relates to the field of thermal protection structures and preparation methods, in particular to a preparation method of a titanium-based composite material thermal protection skin structure. Background technique [0002] The main function of the thermal protection system of a hypersonic vehicle is to ensure that the temperature of the internal structure of the vehicle is maintained within a certain range in a hypersonic aerodynamic thermal environment to ensure the safety of the structure. [0003] According to the classification of heat protection methods, thermal protection systems can be divided into three categories: passive thermal protection systems, semi-active thermal protection systems and active thermal protection systems. The active thermal protection system is a heat protection method in which most of the heat is taken away by the working fluid or the cooling flow. It can be cooled in three ways, namely film cooling, sweat coo...

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Problems solved by technology

Although the metal heat protection system has potential advantages, there are still some problems in several mature metal heat protection systems. The weight price paid by the skin is unbearable for aircraft development; it can be applied to the titanium alloy multi-layer wall panel in the lower temperature area (leeward side), which can withstand lower temperature; the current metal thermal protection structure such as superalloy honeycomb structure and other preparation processes It is relatively complex; the technology maturity of intermetallic compounds is low, and its key performance indicators such as strength, elongation at break and fracture toughness cannot meet the use requirements of skins

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