阅读说明：本技术 一种适用于h型梁复合材料成型工装及其共固化成型方法 (Forming tool suitable for H-shaped beam composite material and co-curing forming method thereof ) 是由 陈超 唐中华 张帅 刘秀 倪敏轩 郭长龙 嵇培军 于 2020-12-30 设计创作，主要内容包括：本发明公开了一种适用于H型梁复合材料成型工装及其共固化成型方法,包括：第一模块,所述第一模块呈长方体状,所述第一模块的两端上分别设有一个第一通孔,所述第一模块上设有两个第一圆角,两个所述第一圆角设置在两个相邻的棱边上,两个所述第一圆角之间的面为第一工作面；第二模块,所述第二模块呈长方体状,所述第二模块的两端上分别设有一个第二通孔,所述第二模块上设有两个第二圆角,两个所述第二圆角设置在两个相邻的棱边上,两个所述第二圆角之间的面为第二工作面,所述第二工作面上设有凹槽,所述凹槽内设有柔性模块,定位销,所述定位销用于穿设在所述第一通孔和所述第二通孔内。其能够保障H型梁复合材料结构的共固化成型质量。(The invention discloses a forming tool and a co-curing forming method suitable for H-shaped beam composite materials, wherein the forming tool comprises the following steps: the first module is in a cuboid shape, two ends of the first module are respectively provided with a first through hole, the first module is provided with two first round corners, the two first round corners are arranged on two adjacent edges, and the surface between the two first round corners is a first working surface; the second module, the second module is the cuboid form, be equipped with a second through-hole on the both ends of second module respectively, be equipped with two second fillets on the second module, two the second fillet sets up on two adjacent edges, two the face between the second fillet is the second working face, be equipped with the recess on the second working face, be equipped with flexible module in the recess, the locating pin is used for wearing to establish first through-hole with in the second through-hole. The co-curing forming quality of the H-shaped beam composite material structure can be guaranteed.)

1. The utility model provides a be applicable to H type roof beam combined material shaping frock which characterized in that includes:

the first module is in a cuboid shape, two ends of the first module are respectively provided with a first through hole, the first module is provided with two first round corners, the two first round corners are arranged on two adjacent edges, and the surface between the two first round corners is a first working surface;

the second module is in a cuboid shape, two ends of the second module are respectively provided with a second through hole, the second module is provided with two second round corners which are arranged on two adjacent edges, the surface between the two second round corners is a second working surface, the second working surface is provided with a groove, and a flexible module is arranged in the groove,

and the positioning pin is used for penetrating in the first through hole and the second through hole.

2. The H-beam composite molding tool and the co-curing molding method thereof according to claim 1, wherein the flexible module can be natural rubber, synthetic rubber, silicone rubber, or thermoplastic elastomer.

3. The H-beam composite material forming tool and the co-curing forming method thereof according to claim 1, wherein the parameters of the first module are alloy steel, aluminum alloy, titanium alloy, glass fiber reinforced plastic and carbon fiber reinforced resin matrix composite material.

4. The H-shaped beam composite material forming tool and the co-curing forming method thereof according to claim 1, wherein the parameter of the first fillet is 2-10 mm in radius.

5. The H-beam composite material forming tool and the co-curing forming method thereof according to claim 1, wherein the parameters of the second module are alloy steel, aluminum alloy, titanium alloy, glass fiber reinforced plastic and carbon fiber reinforced resin matrix composite material.

6. The H-shaped beam composite material forming tool and the co-curing forming method thereof according to claim 1, wherein the parameter of the second fillet is 2-10 mm in radius.

7. The H-shaped beam composite material forming tool and the co-curing forming method thereof according to claim 1, wherein the depth of the groove is 0.5-5 mm.

8. The forming method for the H-shaped beam composite material forming tool according to any one of claims 1 to 7 is characterized by comprising the following steps of:

s1: coating a release agent on the first working surface, the second working surface and the flexible module;

s2: paving a prepreg on the first working surface, wherein the prepreg is attached to the first working surface, and the prepreg, the side surfaces attached to two sides of the first working surface and the first fillet are arranged to form a first C-shaped preformed body;

s3: paving a prepreg on the second working surface, wherein the prepreg is attached to the second working surface, and the prepreg, the side surfaces attached to two sides of the second working surface and the second fillet are arranged to form a second C-shaped preformed body;

s3: assembling a first module and a second module, oppositely attaching the first working surface and the second working surface, correspondingly arranging a first through hole and a second through hole, and penetrating a positioning pin into the first through hole and the second through hole to ensure accurate positioning of the first module and the second module so as to attach the first C-shaped preformed body and the second C-shaped preformed body;

s4: respectively placing twill strips in the depressions at two sides of the first C-shaped pre-forming body and the second C-shaped pre-forming body;

s5: respectively placing a flange strip pre-forming body on two sides of the first C-shaped pre-forming body and the second C-shaped pre-forming body, wherein the flange strip pre-forming body is in a long strip shape and is attached to the first C-shaped pre-forming body, the second C-shaped pre-forming body and the twill strip;

s6: sequentially coating an isolation film, an air felt and a vacuum bag on the tool and the materials on the tool, completing vacuum degree detection of a vacuum bag packaging system, and then putting the vacuum bag packaging system into a tank for curing;

s7: and after the tank is taken out and the mold is released, nondestructive detection and size detection are carried out, and the H-shaped beam composite material structure with the molding quality and the size precision meeting the requirements is obtained.

9. The H-beam composite material forming tool and the co-curing forming method thereof according to claim 8, wherein the prepreg laid in S2 and S3 can be formed by manually laying, automatically laying silk or automatically laying tape to lay flat laminated layers of the prepreg and then adopting a thermal diaphragm preforming process or a mechanical laminated slip forming mode; the twill strip can be prefabricated by performing methods such as manual twisting, pultrusion and mould pressing.

Technical Field

The invention relates to the field of composite materials, in particular to a forming tool suitable for an H-shaped beam composite material and a co-curing forming method thereof.

Background

In composite load bearing structures, H-beams are widely used due to their outstanding structural stiffness and strength. The H-shaped beam structure composite material can be formed by adopting co-curing, co-bonding, secondary bonding and other modes, wherein the secondary bonding is formed by bonding the completely cured components, the molding quality of each part is easy to ensure by independently curing the components, but the structural integrity is insufficient; the co-bonding is that after part of components in the structure are cured, the components and the uncured part are subjected to primary heating curing molding, so that the molding quality can be effectively ensured, but the molding process flow is more complex; the co-curing molding is to mold all components in the structure after being assembled by using an uncured pre-forming body and then being cured by heating and pressurizing once, and the structural integrity is high but the molding risk is increased synchronously. As the H-shaped beam is mainly used in a large-load working condition, the structure with integrity formed by co-curing is the preferred forming method of the H-shaped beam composite material structure.

Traditionally, H type roof beam co-curing shaping adopts metal rigidity frock mostly to ensure profile tolerance and size precision, nevertheless to large size H type roof beam structure web face, adopt metal rigidity frock often can bring the unstable problem of web face shaping pressure because the rigidity is to the mould involution mode of rigidity, and then produce the shaping quality risk. In recent years, the core mold or soft mold assisted forming through rubber or air bags is also developed, but the profile and the size of the formed profile are difficult to ensure without the support of a metal rigid tool.

Disclosure of Invention

In order to overcome the defects in the prior art, the embodiment of the invention provides a forming tool suitable for an H-shaped beam composite material and a co-curing forming method thereof, which can ensure the co-curing forming quality of an H-shaped beam composite material structure.

In order to realize the above-mentioned purpose, the embodiment of the application discloses a composite material shaping frock suitable for H type roof beam, includes:

the first module is in a cuboid shape, two ends of the first module are respectively provided with a first through hole, the first module is provided with two first round corners, the two first round corners are arranged on two adjacent edges, and the surface between the two first round corners is a first working surface;

the second module is in a cuboid shape, two ends of the second module are respectively provided with a second through hole, the second module is provided with two second round corners which are arranged on two adjacent edges, the surface between the two second round corners is a second working surface, the second working surface is provided with a groove, and a flexible module is arranged in the groove,

and the positioning pin is used for penetrating in the first through hole and the second through hole.

Preferably, the flexible module can be natural rubber, synthetic rubber, silicone rubber, thermoplastic elastomer.

Preferably, the parameters of the first module are alloy steel, aluminum alloy, titanium alloy, glass fiber reinforced plastic and carbon fiber reinforced resin matrix composite.

Preferably, the parameter of the first round angle is 2-10 mm of radius.

Preferably, the parameters of the second module are alloy steel, aluminum alloy, titanium alloy, glass fiber reinforced plastic and carbon fiber reinforced resin matrix composite.

Preferably, the parameter of the second round angle is 2-10 mm of radius.

Preferably, the depth of the groove is 0.5-5 mm.

The application discloses a molding method, which comprises the following steps:

s1: coating a release agent on the first working surface, the second working surface and the flexible module;

s2: paving a prepreg on the first working surface, wherein the prepreg is attached to the first working surface, and the prepreg, the side surfaces attached to two sides of the first working surface and the first fillet are arranged to form a first C-shaped preformed body;

s3: paving a prepreg on the second working surface, wherein the prepreg is attached to the second working surface, and the prepreg, the side surfaces attached to two sides of the second working surface and the second fillet are arranged to form a second C-shaped preformed body;

s3: assembling a first module and a second module, oppositely attaching the first working surface and the second working surface, correspondingly arranging a first through hole and a second through hole, and penetrating a positioning pin into the first through hole and the second through hole to ensure accurate positioning of the first module and the second module so as to attach the first C-shaped preformed body and the second C-shaped preformed body;

s4: respectively placing twill strips in the depressions at two sides of the first C-shaped pre-forming body and the second C-shaped pre-forming body;

s5: respectively placing a flange strip pre-forming body on two sides of the first C-shaped pre-forming body and the second C-shaped pre-forming body, wherein the flange strip pre-forming body is in a long strip shape and is attached to the first C-shaped pre-forming body, the second C-shaped pre-forming body and the twill strip;

s6: sequentially coating an isolation film, an air felt and a vacuum bag on the tool and the materials on the tool, completing vacuum degree detection of a vacuum bag packaging system, and then putting the vacuum bag packaging system into a tank for curing;

s7: and after the tank is taken out and the mold is released, nondestructive detection and size detection are carried out, and the H-shaped beam composite material structure with the molding quality and the size precision meeting the requirements is obtained.

Preferably, the prepreg laid and pasted in the S2 and S3 can be formed by adopting a thermal diaphragm pre-forming process or a mechanical lamination slip forming mode after being manually laid, automatically laid or automatically laid with tapes to lay flat laminated prepregs; the twill strip can be prefabricated by performing methods such as manual twisting, pultrusion and mould pressing.

The invention has the following beneficial effects:

1. the unique adaptive forming tool of the rigid tool (a first module) and the flexible tool (a second module) is obtained through the combination of the flexible modules, so that the uniform transmission of pressure in the forming process of the web surface of the H-shaped beam is ensured while the forming size precision of the web surface is ensured, and the co-curing forming quality of the composite material structure of the H-shaped beam is ensured;

2. through setting up first through-hole and second through-hole, the cooperation locating pin effectively prevents first module and second module location inaccurate.

In order to make the aforementioned and other objects, features and advantages of the invention comprehensible, preferred embodiments accompanied with figures are described in detail below.

Drawings

In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, it is obvious that the drawings in the following description are only some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to the drawings without creative efforts.

Fig. 1 is a schematic structural diagram of a tool suitable for forming an H-shaped beam composite material according to an embodiment of the present invention;

FIG. 2 is an exploded view of a tooling for forming a composite material for an H-beam according to an embodiment of the present invention;

reference numerals of the above figures:

1. a first module; 11. a first rounded corner; 12. a first through hole; 13. a first working surface;

2. a second module; 21. a second rounded corner; 22. a second through hole; 23. a second working surface; 24. a flexible module;

3. a first C-shaped preform;

4. a second C-shaped preform;

5. twisting the strips;

6. a bead preform.

Detailed Description

The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

In the description of the present invention, it should be noted that the terms "upper", "lower", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience of description and simplicity of description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature.

To achieve the above object, referring to fig. 1 and fig. 2, the present invention provides a tool for forming H-beam composite material, including a first module 1 and a second module 2.

The first module 1 is a cuboid, two first through holes 12 are respectively arranged at two ends of the first module 1, two first round corners 11 are arranged on the first module 1, the two first round corners 11 are arranged on two adjacent edges, and the surface between the two first round corners 11 is a first working surface 13.

The second module 2 is a cuboid, two second through holes 22 are respectively formed in two ends of the second module 2, two second round corners 21 are arranged on the second module 2, the two second round corners 21 are arranged on two adjacent edges, the two surfaces between the second round corners 21 are second working surfaces 23, grooves are formed in the second working surfaces 23, and flexible modules 24 are arranged in the grooves.

And the positioning pins are used for penetrating in the first through holes 12 and the second through holes 22.

Further, the flexible module 24 can be natural rubber, synthetic rubber, silicone rubber, thermoplastic elastomer.

Further, the parameters of the first module 1 are alloy steel, aluminum alloy, titanium alloy, glass fiber reinforced plastic and carbon fiber reinforced resin matrix composite.

Further, the parameter of the first round angle 11 is a radius of 2-10 mm.

Further, the parameters of the second module 2 are alloy steel, aluminum alloy, titanium alloy, glass fiber reinforced plastic and carbon fiber reinforced resin matrix composite material.

Furthermore, the parameter of the second round angle 21 is the radius of 2-10 mm.

Furthermore, the depth of the groove is 0.5-5 mm.

Further, the first through hole 12 penetrates through the first module 1, and the second through hole 22 is arranged regardless of the second module 2, so that the positioning pin is effectively prevented from being disengaged from the second through hole 22.

It can be understood that the unique adaptive forming tool of the rigid tool (the first module 1) and the flexible tool (the second module 2) is obtained by combining the flexible modules 24, so that the uniform pressure transmission in the forming process of the web surface of the H-shaped beam is ensured while the forming size precision of the web surface is ensured, and the co-curing forming quality of the composite material structure of the H-shaped beam is ensured;

through setting up first through-hole 12 and second through-hole 22, cooperation locating pin effectively prevents first module 1 and second module 2 location inaccurate.

The application discloses a molding method, which comprises the following steps:

s1: applying a release agent on the first working surface 13, the second working surface 23 and the flexible module 24;

s2: paving and pasting prepreg on the first working surface 13, wherein the prepreg is pasted on the first working surface 13, and the prepreg, the side surfaces pasted on two sides of the first working surface 13 and the first fillet 11 are arranged to form a first C-shaped preforming body 3;

s3: paving a prepreg on the second working surface 23, wherein the prepreg is adhered to the second working surface 23, and the prepreg, the side surfaces adhered to two sides of the second working surface 23 and the second fillet 21 are arranged to form a second C-shaped pre-forming body 4;

s3: assembling a first module 1 and a second module 2, oppositely attaching the first working surface 13 and the second working surface 23, correspondingly attaching the first through hole 12 and the second through hole 22, and penetrating the positioning pin into the first through hole 12 and the second through hole 22 to ensure accurate positioning of the first module 1 and the second module 2 so as to attach the first C-shaped preformed body 3 and the second C-shaped preformed body 4;

s4: placing twill strips 5 in the depressions at both sides of the first C-shaped pre-form 3 and the second C-shaped pre-form 4 respectively;

s5: respectively placing a flange strip pre-forming body 6 on two sides of the first C-shaped pre-forming body 3 and the second C-shaped pre-forming body 4, wherein the flange strip pre-forming body 6 is in a long strip shape, and the flange strip pre-forming body 6 is attached to the first C-shaped pre-forming body 3, the second C-shaped pre-forming body 4 and the twister strip 5;

s6: sequentially coating an isolation film, an air felt and a vacuum bag on the tool and the materials on the tool, completing vacuum degree detection of a vacuum bag packaging system, and then putting the vacuum bag packaging system into a tank for curing;

s7: and after the tank is taken out and the mold is released, nondestructive detection and size detection are carried out, and the H-shaped beam composite material structure with the molding quality and the size precision meeting the requirements is obtained.

Furthermore, the prepreg laid and pasted in the S2 and S3 can be formed by adopting a thermal diaphragm pre-forming process or a mechanical lamination slip forming mode after being manually laid, automatically laid or automatically laid with tapes to lay flat laminates of the prepreg; the twister strip 5 can be prefabricated by performing methods such as manual twisting, pultrusion and mould pressing.

In the present embodiment, the prepreg sheet may be a unidirectional prepreg or a fabric prepreg using carbon fibers, the fibers in the prepreg may be, but are not limited to, carbon fibers, glass fibers, aramid fibers, etc., and the resin may be, but is not limited to, epoxy resin, bismaleimide resin, phenolic resin, polyimide resin, etc.

The principle and the implementation mode of the invention are explained by applying specific embodiments in the invention, and the description of the embodiments is only used for helping to understand the method and the core idea of the invention; meanwhile, for a person skilled in the art, according to the idea of the present invention, there may be variations in the specific embodiments and the application scope, and in summary, the content of the present specification should not be construed as a limitation to the present invention.