KR19980051721A - Manufacturing method of fiber reinforced composite and carbon-carbon composite lattice structure - Google Patents

Abstract

A method of manufacturing a fiber reinforced composite material and a carbon-carbon composite grid structure for preparing an ultralight structure or an ultra high temperature heat resistant structure in a lattice form, the method comprising: impregnating a bundle of fiber reinforcing material into a thermosetting resin; Winding the bundle of fiber reinforcing materials impregnated with the thermosetting resin in a predetermined pattern along a guide pin installed in the jig and molding at room temperature or high temperature; Wrapping the fiber reinforcement bundle wound around the jig with heat shrink tape through the guide pin; Providing a fiber-reinforced composite material comprising separating a guide pin installed in the jig from the jig and removing a grid structure formed through the jig from the jig; Other modifications include impregnating a carbon fiber bundle into a polymer resin having a high carbonization rate; Winding the polymer fiber-impregnated carbon fiber bundles in a predetermined pattern along a guide pin installed in the jig to be molded at room temperature or high temperature; Wrapping the bundle of carbon fibers wound around the jig through the guide pins with a heat shrink tape; Heat-treating the lattice structure formed into a preform as described above in a carbonization heat treatment oven in an oxygen-free atmosphere at 1000 ° C. or more in a state of being wound around a jig; The method of manufacturing a carbon-carbon composite grid structure comprising the step of separating the guide pin installed in the jig from the jig to remove the grid structure formed through the jig from the jig.

Description

Manufacturing Method of Fiber Reinforced Composites and Carbon-Carbon Composites

The present invention relates to a fiber-reinforced composite material and a carbon-carbon composite lattice structure manufacturing method for producing a super lightweight structure or ultra-high temperature heat-resistant structure in the form of a lattice.

The grid structure manufactured using the fiber reinforced composite material of the present invention can be used as a variety of truss structures for aerospace, and can be widely used as a substitute for steel nets applied to general construction, electricity-related pedestal structures or concrete structures. Carbon-carbon composites are carbon fiber reinforced carbon matrix composites, which have excellent heat resistance, high strength, and high elasticity. They are used as ultra-high temperature and light weight structural materials in the aerospace field. Is only 1/5, and the strength increases with increasing temperature and can be used up to about 3000 ℃ in an oxygen-free atmosphere, so it can be applied to various aviation heat resistant structures as a super lightweight heat resistant structure. It can be used as a cartridge for heat treatment of heat-resistant alloys and various ceramics required.

Figure 1 illustrates a grating structure made of a conventional composite, cutting the structural elements of the pre-formed composite 110, for example, tubular composite, channel-shaped composite, bar-shaped composite to a predetermined length as shown After that, the lattice structure 100 is manufactured by assembling and connecting the composites 110 to each other using a metal fitting 120.

In the case of the grid structure 100 manufactured by connecting (jointing) the composite material 110 through the metal fitting 120 as described above, since it is lighter than the existing metal grid structure, it is easy to carry and install, In particular, it has excellent resistance to corrosion and has excellent economic efficiency for maintenance.

However, in order to manufacture the lattice structure 100 as described above, the composite material 110 having a predetermined cross section is formed in advance, and after cutting to a predetermined length, a multi-step process using the metal fitting 110 is required.

In addition, the manufacturing of the composite member 110 is usually subjected to a process of pultrusion or filament winding by impregnating a polymer resin in glass fiber, according to the manufacturing equipment and molding jig (pultrusion die or winding mandrel) The cost of investment for the product is not small, which is the main cause of the price increase of the final product.

In addition, in order to avoid problems such as a decrease in strength of the composite 110 due to the connection (joint) of the metal fitting 120 and the composite 110 member, the bonding joint (bonding joint) mainly by the adhesive rather than the mechanical coupling as shown in FIG. In this case, special surface treatment of the adhesive surface is required to increase the strength and reliability of the joint, and in the case where the carbon composite material and the aluminum fitting are combined, the galvanic corrosion treatment is required separately. . Therefore, although the conventional grating structure 100 has many advantages in terms of performance compared to the existing metal grating structure, it takes a lot of time from facility investment and composite member to assembly, and is a major driver of the price increase due to the addition of a special process. There is a limitation in expanding the application.

Figure 2 illustrates a conventional grating structure made of a metal material, the grating structure 200 is a cartridge used for high temperature heat treatment.

In the case of the cartridge-type lattice structure 200 provided as described above, a metal cartridge is used at a temperature of 1000 ° C. or less, which is a relatively low temperature region, and a graphite cartridge of high purity and high density is used at a high temperature of 1500 ° C. or more. In the case of metal cartridges, the thermal mass of the jig itself is large during heat treatment, so the loss is large in terms of thermal efficiency. In the case of graphite materials, not only is it weak in thermal shock, but also general mechanical strength (for example, tensile strength and impact strength) is a problem. It becomes thicker than necessary, and in actual use, a problem occurs that often breaks down even in a weak impact.

In the present invention, in order to solve the problem of the joint region in the conventional manufacturing method of the composite grid structure, the fiber reinforcement bundle impregnated in the polymer resin is wound directly to the jig of the grid structure and molded to separate the molding from the jig to integrate the joint site It is an object of the present invention to provide a method for manufacturing a low cost fiber reinforced composite lattice structure.

Another object of the present invention is to provide a method for producing a carbon-carbon composite lattice structure in which the joint structure is integrally made using a carbon-carbon composite material instead of a metal or graphite-based jig used in the conventional high temperature heat treatment.

In order to achieve the above object, the present invention comprises the steps of impregnating a bundle of fiber reinforcing material in the thermosetting resin;

Winding the bundle of fiber reinforcing materials impregnated with the thermosetting resin in a predetermined pattern along a guide pin installed in the jig and molding at room temperature or high temperature;

Wrapping the fiber reinforcement bundle wound around the jig with heat shrink tape through the guide pin;

Separating the guide pin installed in the jig from the jig to remove the grid structure formed through the jig from the jig.

Another modified example of the present invention, the carbon fiber bundle impregnated with a high carbonization polymer resin;

Winding the polymer fiber-impregnated carbon fiber bundles in a predetermined pattern along a guide pin installed in the jig to be molded at room temperature or high temperature;

Wrapping the bundle of carbon fibers wound around the jig through the guide pins with a heat shrink tape;

Heat-treating the lattice structure formed into a preform as described above in a carbonization heat treatment oven in an oxygen-free atmosphere at 1000 ° C. or more in a state of being wound around a jig;

Separating the guide pin installed in the jig from the jig to remove the grid structure formed through the jig from the jig.

1 is a perspective view of a lattice structure made of a conventional composite material.

Figure 2 is a perspective view of a lattice structure made of a conventional metal material.

Figure 3 is a manufacturing process of the integrally molded fiber composite grid structure of the present invention.

4 is a configuration diagram of the fiber reinforcement bundle of FIG.

5 is a cross-sectional view taken along the line A-A of FIG.

6 is an exemplary view for forming a joint portion of the fiber composite lattice structure of the present invention.

7 is an illustration of a method of compacting the fiber reinforcement bundle of FIG. 4 using a heat shrink tape.

8 is a cross-sectional view taken along the line B-B in FIG.

9A and 9B are illustrations of a state in which the grid structure formed by FIG. 3 is separated from the jig.

10 is a different embodiment of the present invention, the manufacturing degree of the carbon-carbon composite lattice structure.

Explanation of symbols for the main parts of the drawings

10, 50: lattice structure 18, 58: jig

20, 60: guide pin 22: heat shrink tape

62: Carbonization Heat Treatment Oven

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the accompanying drawings.

Figure 3 illustrates a manufacturing process diagram of the integrally molded fiber composite grating structure of the present invention.

The fiber reinforcement of this invention consists of carbon, glass, aramid fiber, etc. And the fiber reinforcement is provided in the form of a bundle. The fiber reinforcement bundle 12 is impregnated into the thermosetting resin 16 in the impregnation tank 14 through the guide roller 13, and then wound in a predetermined pattern along the guide pin 20 installed in the jig 18. Or molded at high temperatures. In this case, the cross-sectional area of the fiber reinforcement bundle 12 may be obtained by repeatedly passing the fiber reinforcement bundle 12 through the guide pin 20 installed in the jig 18 as illustrated in FIGS. 4 and 5. have. As a result, desired cross-sectional area of the fiber reinforcement bundle 12 can be obtained.

In addition, the fiber reinforcement bundle 12 is continuously wound in the direction of rotation 360 ° to the guide pin 20 as illustrated in FIG. 6 so that the joint 10a of the grid structure 10 is integrally formed as shown in FIG. 9B. ) Is formed. In this way, since the fiber reinforcement bundle 12 is formed after winding 360 ° continuously rotating along the guide pin 20, not only the strength of the joint 10a can be improved, but also metal fittings as in the related art are unnecessary.

As described above, the fiber reinforcement bundles 12 wound around the jig 18 through the guide pin 20 are wrapped with the heat shrink tape 22 as shown in FIGS. 7 and 8. As such, when the fiber reinforcement bundles 12 impregnated with the thermosetting resin 16 are wrapped with the heat shrink tape 22, bubbles generated between the resins during molding are removed, and at the same time, the fiber arrangement is compacted, thereby mechanically The physical properties will be improved and the appearance will be beautiful.

The grid structure 10 formed through the jig 18 as shown in FIG. 9A separates the plurality of guide pins 20 installed in the jig 18 from the jig 18, thereby displacing the grid structure 10 as shown in FIG. 9B. It is to be removed by (18) to obtain a fiber-reinforced composite lattice structure (10) formed integrally.

The guide pin 20 provided in the jig 18 is detachably installed from the jig 18 and is processed with a release-treated metal or Teflon. Accordingly, the guide pin 20 is slipped from the fiber reinforcement bundle 12 which is wound around the guide pin 20 to form the joint 10a, and thus can be separated.

The jig 18 is for obtaining a grating structure 10 of a predetermined fiber reinforced composite material. Therefore, the shape of the jig 18 may be changed to match the shape of the grid structure 10, of course. In addition, the jig 10 may be rotatable so that the fiber reinforcement bundle 12 may be easily wound on the guide pin 20, and the fiber reinforcement bundle 12 may be fixed to the guide pin 20 in a predetermined pattern. Winding can be done manually or automatically, depending on the yield.

FIG. 10 illustrates a manufacturing process diagram of a carbon-carbon composite lattice structure as another modified example of the present invention.

As shown, the carbon-carbon composite material is provided in a bundle form as a composite of carbon fibers reinforced carbon matrix. The carbon fiber bundle 52 is impregnated in the polymer resin 56 having a high carbonization rate such as phenol and pitch in the impregnation tank 54 through the guide roller 53, and then the graphite guide installed in the jig 58 in the form of a cartridge. Winding in a predetermined pattern along the pin 60 is molded at room temperature or high temperature. At this time, the cross-sectional area of the carbon fiber bundle 52 can be obtained by repeatedly passing the carbon fiber bundle 52 through the guide pin 60 installed in the jig 58 as illustrated in FIGS. 4 and 5. . As a result, the desired strength can be obtained by increasing or decreasing the cross-sectional area of the carbon fiber bundle 52.

In addition, as shown in FIG. 6, the carbon fiber bundle 52 is continuously wound in a 360 ° rotational direction to the guide pin 60 to integrally connect the joint 50a of the grid structure 50 as shown in FIG. 10. ) Is formed. In this way, since the carbon fiber bundle 52 is formed by winding 360 ° continuously rotating along the guide pin 60, the joint 50a can be improved in strength.

As described above, the carbon fiber reinforcement 52 wound around the jig 58 through the guide pin 60 is wrapped with the heat shrink tape 22 as shown in FIGS. 7 and 8. As such, when the carbon fiber bundles 52 impregnated with the polymer resin 56 are wrapped with the heat shrink tape 22, bubbles generated between the resins during the molding are removed, and at the same time, the fiber array is compacted, thereby mechanically The physical properties will be improved and the appearance will be beautiful.

As described above, the grid structure 50 formed through the jig 58 separates the guide pin 60 installed in the jig 58 from the jig 58 to form the grid structure 50 having an integral preform structure. You can get it.

However, it is preferable to perform a high temperature heat treatment before separation from the jig 58 in order to prevent the shrinkage and crushing expected during the carbonization and graphitization heat treatment at a high temperature (˜2000 ° C.). The lattice structure 50 may be heat-treated in an oxygen-free atmosphere by placing the lattice structure 50 together with the jig 58 in the carbonization heat treatment oven 62 as illustrated in FIG. 10.

After the first carbonization, the lattice structure 50 is separated from the jig 58, and the porous fiber bundles are impregnated and cured again with a polymer resin, and then recarbonized, or pyrolytic carbon is deposited by chemical vapor deposition to increase the density. Therefore, mechanical strength can be obtained.

Using the jig 58 and the guide pin 60 as the graphite material in order to prevent thermal deformation during carbonization.

The jig 58 is to obtain a grating structure 50 of a predetermined carbon-carbon composite as described above. Therefore, the shape of the jig 58 may be different depending on the shape of the grid structure 50, of course. And the jig 58 is preferably rotatable so as to easily wind the carbon fiber bundle 52 to the guide pin 60, the carbon fiber bundle 52 in a predetermined pattern on the guide pin 60 Winding can be done manually or automatically, depending on the yield.

As described above, the lattice structure made of the fiber-reinforced composite material and the carbon-carbon composite material of the present invention is made of an integral preform, which greatly shortens the manufacturing process and has an effect of providing a low-cost lattice structure with improved mechanical strength. will be.

Claims (5)

(a) impregnating the fiber reinforcement bundle 12 into the thermosetting resin 16; (b) winding the fiber reinforcement bundle 12 impregnated with the thermosetting resin 16 in a predetermined pattern along a guide pin 20 installed in the jig 18 and molding at room temperature or high temperature; (c) wrapping the fiber reinforcement bundle 12 wound around the jig 18 through the guide pin 20 with a heat shrink tape 22; (d) manufacturing a fiber reinforced composite material lattice structure comprising the step of separating the guide pin 20 installed in the jig 18 from the jig to remove the grid structure 10 formed through the jig Way. The fiber reinforcement bundle 12 impregnated with the thermosetting resin 16 has a cross-sectional area formed by winding a predetermined pattern along the guide pin 20 to obtain a required strength of the grid structure 10. Method for producing a fiber-reinforced composite grating structure, characterized in that. The method according to claim 1, characterized in that the fiber reinforcement bundle 12 is integrally formed in the joint (10a) of the lattice structure (10) by winding continuously in the direction of rotation 360 ° to the guide pin (20). Method of manufacturing a fiber reinforced composite lattice structure. The method of claim 1, wherein the guide pin (20) installed in the jig (18) is detachable from the jig (18), characterized in that the process of manufacturing a fiber reinforced composite material grating structure, characterized in that the processed metal or Teflon. (a) impregnating the carbon fiber bundle 52 into the high carbonization polymer resin 56; (b) winding the carbon fiber bundle 52 impregnated with the polymer resin 56 in a predetermined pattern along a guide pin 60 installed in the jig 58 and molding at room temperature or high temperature; (c) wrapping the carbon fiber bundle 52 wound around the jig 58 through the guide pin 60 with a heat shrink tape 22; (d) heat-treating the lattice structure 50 formed into the preform in an anoxic atmosphere at 1000 ° C. or higher in a carbonization heat treatment oven 62 while being wound around the jig 58; (e) removing the guide pin 60 installed in the jig 58 from the jig to remove the grid structure 50 formed through the jig from the jig; Manufacturing method.