An anti-insulation integrated thermal protection structure suitable for negative curvature shapes

Abstract

The invention discloses an anti-heat insulation integrated heat protection structure suitable for a negative curvature shape, and belongs to the technical field of heat protection for hypersonic near-space vehicles. It includes: a load-bearing shell; a heat protection layer, the heat protection layer includes a heat insulation layer and a heat protection layer, the inner wall of the heat protection layer is provided with grid-shaped heat protection layer reinforcement ribs, and the heat insulation layer is arranged on the heat protection layer to strengthen In the grid of the ribs, the surface of the heat insulation layer is provided with a heat insulation layer covering skin; the heat protection layer, the heat insulation layer covering skin, and the reinforcement rib of the heat protection layer pass through the seam line with the heat insulation layer in the state of prepreg It is stitched into one body, and then cured at high temperature to form an integrated heat-insulating structure; the adhesive layer is located between the load-bearing shell and the heat protection layer, and the adhesive layer is an adhesive with high temperature resistance and thermal matching properties. The invention adopts an integrated heat protection layer for preventing heat insulation and is bonded on the load-bearing shell with a high-temperature-resistant adhesive, which can avoid interface separation at negative curvature parts of the heat protection structure of the aircraft.

Description

technical field [0001] The invention relates to the technical field of thermal protection of hypersonic near-space vehicles, in particular to an anti-heat insulation integrated thermal protection structure suitable for negative curvature shapes. Background technique [0002] Hypersonic near-space vehicles (generally referring to aircraft with a flight speed exceeding Mach 5 and flying in the atmosphere all the way) have great military value and potential economic value due to their high flight speed and strong defense penetration capabilities. The main direction of the development of foreign weapons and spacecraft. When the aircraft flies at hypersonic speed in the atmosphere, the aerodynamic heating is very serious. The thermal protection of the outer surface of the aircraft has always been a key problem to be solved in the design of hypersonic near space vehicles. [0003] The thermal protection structure of the outer surface of a common hypersonic vehicle is generally a ...

AI Technical Summary

Problems solved by technology

After the interface separation occurs at the negative curvature part, under the action of high-speed aerodynamic load, the stress of the heat shield layer at the part where the interface separation occurs will increase rapidly, and damage will easily occur, which will lead to the destruction of the entire heat shield layer and the damage of the aircraft structure

[0006] (2) During the forming process of the heat-proof layer, the fiber cloth or prepreg needs to be laid on the load-bearing shell or tooling. For the heat protection structure with a negative curvature shape, due to the deformation of the fiber cloth or prepreg in the plane The ability is poor. During the draping process, the negative curvature is prone to wrinkles, and the formed heat-resistant layer will have defects such as local bulges or local holes, which will affect the thermal protection performance of the heat-resistant layer.

[0007] (3) For the heat-proof layer formed by winding or laying pre-fixed on the load-bearing layer with prepreg cloth, and then solidified and formed together with the load-bearing layer, in addition to the above problems, there are also negative curvature parts due to winding, laying The tension force is difficult to control, which makes it difficult to guarantee the material performance of the heat-proof layer at the negative curvature part; at the same time, because the thermal expansion of the load-bearing shell is larger than that of the heat-proof layer, the load-bearing shell shrinks more after curing, and the heat-proof layer at the negative curvature Interfacial separation between the layer and the load-bearing shell will be the first to occur

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