Heat preventing and insulating integrated thermal protection structure suitable for negative curvature shape

Abstract

The invention discloses a heat preventing and insulating integrated thermal protection structure suitable for a negative curvature shape, and belongs to the technical field of thermal protection of hypersonic-speed near space aircrafts. The thermal protection structure includes a force bearing shell and a thermal protection layer; the thermal protection layer includes a heat insulating layer and aheat preventing layer, the inner wall of the heat preventing layer is provided with grid-like heat-preventing layer reinforcement ribs, the heat insulating layer is arranged in the grids of the heat-preventing layer reinforcement ribs, and the surface of the heat insulating layer is provided with a heat insulating layer covering skin; the heat preventing layer, the heat insulating layer coveringskin, and the heat-preventing layer reinforcing ribs are sewed together with the heat insulating layer through a sewing line in a prepreg state, and the whole is subjected to high-temperature curing to form the heat preventing and insulating integrated structure; and an adhesive layer is located between the force bearing shell and the thermal protection layer, and the adhesive layer is an adhesivewith high-temperature resistance and heat matching performance. The thermal protection structure provided by the invention adopts the heat preventing and insulating integrated thermal protection layer, and the thermal protection layer is bonded to the force bearing shell by using the high-temperature-resistant adhesive, so that interface separation at the negative curvature part of the thermal protection structure of an aircraft can be avoided.

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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