Parallel/crossed stagger arrangement type corrugation and sandwich integrated thermal protection panel

Abstract

A parallel/crossed stagger arrangement type corrugation and sandwich integrated thermal protection panel which comprises a top layer panel body, a middle panel body, a bottom layer panel body, an upper layer web and a lower layer web. The top layer panel body is connected with the middle panel body through the upper layer web. The middle panel body is connected with the bottom layer panel body through the lower layer web. The gaps between all the panel bodies and webs are filled with heat insulation materials. The three panel bodies are parallel. The upper layer web and the lower layer web adopt parallel stagger arrangement type distributed structures or crossed stagger arrangement type distributed structures. The upper layer web and the lower layer web are perpendicular to the three panel bodies or inclination angles are formed between the upper layer web and the three panel bodies as well as between the lower layer web and the three panel bodies. The top layer panel body is connected with the upper layer web in a riveted and inserted mode, and riveting points and inserting points are distributed in a staggered mode. The riveting points are connected through L-shaped connecting pieces. The inserting points are connected with trapezoidal inserting rails through dovetail inserting grooves. The dovetail grooves and the trapezoidal inserting rails are subjected to chamfering treatment, and deformation compensation gaps are reserved between the dovetail grooves and the trapezoidal inserting rails. By adoption of the thermal protection panel, the thermal short-circuiting effect can be effectively improved, and the deformation mismatching effect can be effectively relieved.

Description

technical field [0001] The invention belongs to the technical field of thermal protection for the surface of hypersonic aircraft, and in particular relates to a parallel / cross-staggered corrugated sandwich integrated thermal protection panel. Background technique [0002] The surface of a hypersonic vehicle usually requires thermal protection treatment to protect the fuselage structure and other internal subsystems in an extreme thermal environment and prevent them from being damaged due to overheating. [0003] The traditional heat protection method is mainly to apply heat-insulating materials such as ceramic heat-proof tiles and heat-insulating blankets on the surface of the aircraft. This heat-protection method can only play a role in preventing heat insulation. The mechanical properties of thermal insulation materials are weak, and it is also accompanied by the disadvantage of poor maintainability of the adhesive connection. When it is used as the surface thermal protect...

AI Technical Summary

Problems solved by technology

[0006] Although the above-mentioned thermal protection panels can have good mechanical properties in high temperature environments, the alloy materials used for the webs and panels of the thermal protection panels usually have high thermal conductivity, and the heat of the upper panel will flow along the web Transfer to the lower panel, and the heat transfer speed is significantly faster than the heat transfer speed in the insulation material, which will produce a very obvious thermal short circuit effect and cause the temperature of the lower panel to rise too fast

In addition, due to the large temperature difference between the upper panel and the lower panel, the thermal expansion deformation of

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