CN109263160B

CN109263160B - Method for forming heterogeneous multilayer heat-insulation-preventing composite material prefabricated body structure

Info

Publication number: CN109263160B
Application number: CN201810817890.3A
Authority: CN
Inventors: 单忠德; 孙正; 刘丰; 张群; 胡培利
Original assignee: China Academy Of Machinery Science And Technology Group Co ltd; Beijing Jike Guochuang Lightweight Science Research Institute Co Ltd
Current assignee: China Academy Of Machinery Science And Technology Group Co ltd; Beijing Jike Guochuang Lightweight Science Research Institute Co Ltd
Priority date: 2018-07-23
Filing date: 2018-07-23
Publication date: 2021-05-04
Anticipated expiration: 2038-07-23
Also published as: CN109263160A

Abstract

The invention discloses a heterogeneous multilayer heat-insulation-preventing composite material prefabricated body structure and a forming process thereof. The structure comprises a heat-proof structural layer, a heat-insulating transition layer and a bearing structural layer. The forming process includes presetting guide rods, controlling the sequence of fiber winding, changing the center distance of guide sleeves, replacing guide sleeves with fibers and preparing prefabricated bodies with multiple materials, multiple layers and gradient density. The heat-proof structural layer is formed by winding and laying fibers with excellent heat-proof performance along the guide sleeve. The heat insulation transition layer is made by winding fibers with excellent heat insulation performance along the guide sleeve. The bearing structure layer is made by winding and laying continuous fibers along the guide sleeve. The density gradient structure is realized by controlling the center distance of the guide sleeve and a fiber laying and winding combination mode. The composite material prepared by impregnating the prefabricated body structure and the matrix can realize the functions of heat prevention, heat insulation and bearing integration.

Description

Method for forming heterogeneous multilayer heat-insulation-preventing composite material prefabricated body structure

Technical Field

The invention relates to a method for forming a heat-proof/heat-insulation/load-bearing composite material prefabricated body structure, in particular to a method for forming a heterogeneous multilayer heat-proof/heat-insulation composite material prefabricated body structure, which is used for the field of heat-proof/heat-insulation/load-bearing integrated heat protection of composite materials.

Background

The hypersonic flight vehicle has the characteristics of hypersonic cruise, quick response, high strategic value and the like, and becomes important strategic equipment for competitive development of all the countries. In the process of hypersonic flight and reentry of the hypersonic flight vehicle in the near space, the surface temperature of the vehicle is very high, and the fuselage cabin body bears ultrahigh dynamic load. The thermal protection system is positioned outside the fuselage of the hypersonic aircraft and protects the fuselage and the internal structure of the hypersonic aircraft from exceeding the temperature limit which can be borne. With the continuous improvement of the structural efficiency requirement of the aircraft, the thermal protection system is promoted to meet the heat insulation requirement and can bear certain load, so that the thermal protection system of the hypersonic aircraft continuously tends to develop towards the heat insulation/bearing integration direction.

The traditional thermal protection structure mainly comprises a corrugated sandwich integrated thermal protection structure, a rigid heat insulation sandwich integrated structure, a multi-level structure integrated thermal protection structure and the like, has good specific rigidity, specific strength, heat prevention/heat insulation/bearing performance and also has wide application prospect. However, whether the sandwich structure or the multi-layer structure is limited by the preparation process and the structure thereof, the thermal protection system has heavy weight and poor stability of the thermal protection performance, and the reliability of the thermal protection system of the hypersonic aircraft is further influenced.

Aiming at the heat prevention/heat insulation/bearing integration requirement provided by the heat protection system of the hypersonic aircraft, the development of the composite material heat prevention/heat insulation/bearing integration heat protection system becomes a problem to be solved urgently for the hypersonic aircraft, and the preform forming is the key for researching the heat prevention/heat insulation/bearing integration composite material.

Disclosure of Invention

The invention provides a forming method of a heterogeneous multilayer heat-insulation-preventing composite material prefabricated body structure, which aims to solve the problems, realize the integration of heat prevention, heat insulation and bearing of a hypersonic aircraft heat protection system and further improve the performance of the heat protection system.

The invention adopts the following technical scheme:

a heterogeneous multilayer heat-insulation-preventing composite material prefabricated body structure forming method comprises a heat-insulation structural layer (1), a heat-insulation transition layer (2) and a bearing structural layer (3), and the prefabricated body forming process comprises the following steps:

(1) preparing a positioning plate and a guide rod, punching the positioning plate, fixing the guide rod on the positioning plate, wherein the hole distance between the heat-proof structural layer (1) and the bearing structural layer (3) is smaller, and the hole distance between the heat-insulation transition layer (2) is larger;

(2) weaving a heat-proof structural layer (1), firstly, carrying out cross winding on fibers along guide rods, connecting the guide rods in each row in the heat-proof structural layer (1), and then laying the fibers in the horizontal direction;

(3) after the heat-proof structural layer (1) is woven, the fiber type is changed to weave the heat-insulating transition layer (2), the fibers are firstly crossly wound along the last row of guide rods of the heat-proof structural layer (1), the heat-proof structural layer (1) and the heat-insulating transition layer (2) are connected, then crossly wound along the first row of guide rods of the bearing structural layer (3), and the heat-insulating transition layer (2) and the bearing structural layer (3) are connected;

(4) replacing the fiber type to weave the bearing structure layer (3), firstly, the fiber is wound along the first row of guide rods of the bearing structure layer (3) in a crossed manner, the guide rods in each row in the bearing structure layer (3) are connected, and then, the fiber is laid in the vertical direction and the horizontal direction;

(5) compacting the prefabricated bodies obtained in the steps 2, 3 and 4 to eliminate gaps in the fibers;

(6) selecting the same kind of fibers as the heat-proof structural layer (1), the heat-insulating transition layer (2) and the bearing structural layer (3), and replacing the guide rods with the fibers according to the requirement to prepare the prefabricated body with a multi-material, multi-layer and density gradient structure.

The heat-proof structure layer (1) is a high-density structure layer, the hole pitch on the positioning plate is small, the material is one or a combination of carbon fiber, SiC fiber, quartz fiber, aramid fiber, basalt fiber and metal wire, the fiber is firstly wound along the guide rods in a cross mode, the guide rods in each row in the heat-proof structure layer (1) are connected, and then the fiber is laid along the horizontal direction of the guide sleeve.

The heat insulation transition layer (2) is a low-density layer, the hole distance on the positioning plate is large, the material is one or more of carbon fiber, SiC fiber, quartz fiber, aramid fiber, basalt fiber and metal wire, the fiber takes the last row of guide rods of the heat-proof structure layer (1) as a starting point, the first row of guide rods of the bearing structure layer (3) as a terminal point, the guide rods are wound in a crossed mode, and the heat-proof structure layer (1) is connected with the bearing structure layer (3).

The bearing structure layer (3) is a high-density layer, the hole pitch on the positioning plate is small, the material is one or a combination of a plurality of carbon fibers, SiC fibers, quartz fibers, aramid fibers, basalt fibers and metal wires, the fibers are firstly wound in a cross mode along the guide rods, the guide rods in each row in the bearing structure layer (3) are connected, and then the fibers are laid in the vertical direction and the horizontal direction.

And in the compaction treatment, the compaction pore plate compacts the preform along the guide rod, so that gaps among fibers in the preform are eliminated.

The guide rod is replaced by the fiber, so that the continuous fiber in the same layer is ensured, and the fiber replacing the guide rod is the same as the fiber in the layer in type.

The density gradient is realized by adjusting the hole pitch on the positioning plate and different fiber laying and winding modes.

The layer thickness and the position distribution of the heat-proof structure layer (1), the heat-insulating transition layer (2) and the bearing structure (3) can be adjusted according to the requirements of the use environment.

The invention has the following advantages:

1. the invention divides the heat protection structure into three layers of heat prevention, heat insulation and bearing, different layers obtain the required optimal performance by selecting different materials, and the layer thickness and the position distribution can be adjusted according to the use environment.

2. According to the invention, different fiber winding and laying modes are adopted for each layer of the prefabricated body, different layers can have different surface densities, interlayer fusion can be realized, and integrated forming is realized.

3. The prefabricated body can realize a density gradient structure by adjusting the hole distance on the positioning plate and adopting a fiber laying and winding mode.

Based on the above description, the heterogeneous multilayer heat-insulation-preventing composite material prefabricated body structure and the forming process can be used as a scheme of a heat protection system of a hypersonic aircraft.

Drawings

FIG. 1 is a schematic structural view of a heterogeneous multi-layer insulation-proof composite preform according to the present invention.

Fig. 2 is a side view of the guide sleeve arrangement in an embodiment of the present invention.

Fig. 3 is a top view of the guide sleeve arrangement according to an embodiment of the present invention.

FIG. 4 is a schematic view of a process for forming a thermal protection structure layer according to an embodiment of the present invention.

FIG. 5 is a schematic diagram of a thermal barrier transition layer forming process according to an embodiment of the present invention.

FIG. 6 is a schematic view of a process for forming a carrier structure layer according to an embodiment of the present invention.

FIG. 7 is a schematic view of an exemplary compaction process according to the present invention.

Detailed Description

Preparing a positioning plate 5 and a guide rod 4, wherein the diameter of the guide rod is 1.2mm, punching a hole with the aperture of 1.2mm on the positioning plate 5, and fixing the guide rod 4 on the positioning plate 5 as shown in fig. 2.

FIG. 3 is a top view of the distribution of the guide rods 4, the center distance of the guide sleeves in the y direction is 2mm, the center distance of the guide sleeves in the first, second, fourth and fifth rows is 2mm, and the center distance of the guide sleeves in the third row is 4 mm.

The material of the heat-proof structure layer (1) is 3K SiC fiber with the surface density of 1.79g/cm³The center distances of the guide sleeves in the x direction and the y direction are both 2mm, fibers are wound along the guide sleeves in a cross mode according to the mode 6 in the figure 4, then the fibers are laid along the horizontal direction of the guide sleeves, the heat-proof structural layer (1) with the thickness of 8mm is prepared, and the layer density is 5 layers/10 mm.

The material of the heat insulation transition layer (2) is quartz fiber with the density of 2.2g/cm³The center distance of the guide sleeve in the x direction is 4mm, the quartz fiber is crossly wound along the last row of guide rods of the heat-proof structural layer (1) according to the mode of 7 in figure 5, the heat-proof structural layer (1) and the heat-insulating transition layer (2) are connected, then the crossly wound along the first row of guide rods of the bearing structural layer (3) are connected, the heat-insulating transition layer (2) with the thickness of 5mm and the bearing structural layer (2) are prepared, and the layer density is 4 layers/10 mm.

The bearing structure layer (3) is 12K carbon fiber with the density of 1.8g/cm³The center distances of the guide sleeves in the x direction and the y direction are both 2mm, the carbon fibers are firstly crossly wound along a first row of guide rods of the bearing structure layer (3) according to the mode of 8 in a figure 6, the guide rods in each row in the bearing structure layer (3) are connected, and then the fibers are laid in the vertical direction and the horizontal direction, so that the bearing structure layer with the thickness of 6mm is prepared, and the layer density is 5 layers/10 mm.

The resulting preform is compacted and the compaction orifice 9 compacts the preform 10 along the guide sleeve 4, as shown in fig. 7, eliminating fiber gaps in the preform.

3K SiC fibers are adopted to replace the guide rod in the heat-proof structural layer (1), quartz fibers are adopted to replace the guide rod in the heat-insulating transition layer (2), and 12K carbon fibers are adopted to replace the guide rod in the bearing structural layer (3), so that the preparation of the heterogeneous multilayer heat-proof composite prefabricated body is completed.

The invention is not to be considered as limited to the specific embodiments thereof, and all changes, equivalents and improvements that can be made by those skilled in the art are intended to be included within the scope of the invention, all within the spirit and principle of the inventive concept.

Claims

1. A heterogeneous multilayer heat-insulation-preventing composite material preform structure forming method is characterized by comprising the following steps:

(6) selecting fibers of the same kind as the heat-proof structural layer (1), the heat-insulating transition layer (2) and the bearing structural layer (3), and replacing the guide rods with the fibers according to requirements to prepare a prefabricated body with a multi-material, multi-layer and density gradient structure;

the heat-proof structure layer (1) is a high-density structure layer, the hole pitch on the positioning plate is small, the material is one or more of carbon fiber, SiC fiber, quartz fiber, aramid fiber, basalt fiber and metal wire, the fiber is firstly wound along the guide rods in a cross mode, each row of guide rods in the heat-proof structure layer (1) are connected, and then the fiber is laid along the horizontal direction of the guide sleeve;

the heat insulation transition layer (2) is a low-density layer, the hole pitch on the positioning plate is large, the material is one or more of carbon fiber, SiC fiber, quartz fiber, aramid fiber, basalt fiber and metal wire, the fiber takes the last row of guide rods of the heat-proof structural layer (1) as a starting point, takes the first row of guide rods of the bearing structural layer (3) as an end point, and is wound along the guide rods in a cross mode to connect the heat-proof structural layer (1) with the bearing structural layer (3);

the bearing structure layer (3) is a high-density layer, the hole pitch on the positioning plate is small, the material is one or a combination of a plurality of carbon fibers, SiC fibers, quartz fibers, aramid fibers, basalt fibers and metal wires, the fibers are firstly wound in a cross mode along guide rods, the guide rods in each row in the bearing structure layer (3) are connected, and then the fibers are laid in the vertical direction and the horizontal direction.

2. A heterogeneous multi-layer insulation composite preform structure forming method as claimed in claim 1, wherein the compacting process is performed by compacting the preform by a compacting orifice plate along a guide rod to eliminate the gaps between fibers in the preform.

3. A method for forming a heterogeneous multi-layer insulation composite preform structure according to claim 1, wherein the guide rods are replaced by fibers to ensure that the fibers in the same layer are continuous, and the fibers of the replacement guide rods are the same as the fibers in the layer.

4. A method for forming a heterogeneous multi-layer insulation composite preform structure according to claim 1, wherein the density gradient is achieved by adjusting the pitch of holes on the positioning plate and by different ways of fiber placement and winding.

5. The method for forming the heterogeneous multi-layer heat-proof and insulation composite material preform structure according to claim 1, wherein the layer thicknesses and the position distribution of the heat-proof structure layer (1), the heat-insulation transition layer (2) and the bearing structure layer (3) can be adjusted according to the requirements of the use environment.