A method for forming an integral special-shaped composite material rib

Abstract

The present invention relates to a forming method of an integral special-shaped composite material rib, comprising: S1. making a uniform pressure plate of the rib; S2. laying prepreg blanks of the upper and lower half molds of the rib; S3. making twist strips; S4. filling the twist strips; S5. bagging, canning and curing. The forming method can form an integral special-shaped composite material rib in one step, reducing the existing multiple parts to one part, avoiding the segmentation and docking of parts, on the one hand effectively improving the strength of the rib, on the other hand saving the original assembly process, shortening the production cycle, reducing the manufacturing cost, and making the internal and external web surfaces of the product flat and smooth, with stable and reliable quality.

Description

Technical Field

[0001] The invention belongs to the technical field of aircraft manufacturing, and in particular relates to a method for forming an integral special-shaped composite material rib of a civil manned aircraft. Background Art

[0002] At present, in the production and manufacturing of aviation composite parts, it is difficult to meet the one-time molding requirements of parts with complex structures and high requirements for the internal and external surfaces and assembly accuracy of the products. Most of them are formed separately by segmentation or split molds, and then combined by subsequent gluing, riveting and other process methods, which not only increases a large number of tools and molds, but also affects production efficiency and increases costs. Summary of the invention

[0003] In order to overcome the shortcomings of the prior art, the purpose of the present invention is to provide a method for forming an integral special-shaped composite material rib that can be formed and manufactured in one go, which can improve the strength of the rib and simplify the process, shorten the production cycle, reduce the manufacturing cost, and make the inner and outer web surfaces of the product flat and smooth, with stable and reliable quality.

[0004] To solve the above problems, the technical solution adopted by the present invention is as follows:

[0005] The present invention provides a method for forming an integral special-shaped composite material rib, comprising:

[0006] S1. Production of rib pressure plate: first, a high temperature resistant rubber pad is laid on the pressure plate tooling, and then a high temperature resistant composite material prepreg is laid on the large and small web surfaces of the pressure plate tooling, and the high temperature resistant composite material prepreg is laid to the R corner arc of the web surface, and the R corner arc is not laid with a high temperature resistant composite material prepreg, and then a high temperature resistant rubber pad is laid, and finally, a high temperature resistant rubber pad is laid at the R corner arc, and then the bag is put into the furnace for curing and molding, and demolding is performed to obtain a rib pressure plate;

[0007] S2. Laying the prepreg blanks of the upper and lower molds of the rib: First, lay the prepreg blanks of the upper and lower molds of the rib on the upper and lower molding molds of the rib respectively, and then lay the adhesive peelable cloth and carbon fiber prepreg on the upper and lower molds of the rib respectively, and avoid the prepreg wrinkles, accumulation and other defects at the R corners or curved surfaces of the upper and lower molds of the rib, and finally close the upper and lower molds of the rib;

[0008] S3. Twist strip production: According to the double arc filling area of ​​the ribs in the upper and lower molds after S2 mold closing, a twist strip with a matching shape and size is produced on the twist strip forming mold using carbon fiber unidirectional tape prepreg;

[0009] S4. Filling the twist strips: First, the twist strips are filled one by one into the double arc filling area of ​​the molded ribs of the same shape and size, and then the carbon fiber fabric prepreg and the adhesive strippable cloth are laid on the tooling of the ribs after the mold;

[0010] S5. Bag making, canning and curing: First, bag the ribs obtained by paving in S4, place the uniform pressure plate obtained in S1 and tap it, then put the ribs into the autoclave for curing, and take them out of the can to obtain the integral special-shaped composite material ribs.

[0011] The above-mentioned method for forming an integral special-shaped composite material rib, step S3 is specifically as follows: according to the circumference of the rib shape, the carbon fiber unidirectional tape prepreg is first cut into a long strip with a width of about 40 mm, and then the long strip is cut into filaments with a width of about 2 to 3 mm, and then the carbon fiber unidirectional tape prepreg filaments are sequentially filled into the twist strip forming tooling. During filling, a pressure rod is required to compact the carbon fiber unidirectional tape prepreg filaments, and the filled carbon fiber unidirectional tape prepreg filaments are 0.5 to 1 mm higher than the mold plane. Then, a pressure plate is installed on the twist strip forming tooling filled with the carbon fiber unidirectional tape prepreg filaments and tightened with screws to compact it. Finally, the twist strip forming tooling is placed in a drying room at 55° to 65° for heating and pre-compacting for 2 hours. After heating and compacting, a twist strip with a shape and size consistent with the double arc filling area of ​​the rib after mold closing is obtained.

[0012] The carbon fiber unidirectional tape prepreg used in making the twist strips in step S3 and the carbon fiber prepreg used in laying the ribs in step S2 are both carbon fiber fabric materials.

[0013] The above-mentioned method for forming an integral special-shaped composite rib, step S1 is specifically as follows: first, a whole layer of high-temperature resistant rubber pad is laid on the uniform pressure plate tooling, and then two layers of high-temperature resistant composite prepreg are laid on the two large web surfaces, and the two layers of high-temperature resistant composite prepreg are laid to the R-angle arc of the web surface, and the high-temperature resistant composite prepreg is not laid at the R-angle arc, and the laid second layer of high-temperature resistant composite prepreg is smaller than the first layer of high-temperature resistant composite prepreg, and the surrounding edges of the first layer of high-temperature resistant composite prepreg and the surrounding edges of the second layer of high-temperature resistant composite prepreg are 2 mm apart; then A total of four layers of high-temperature resistant composite material prepreg are laid on the small web surface, and the four layers of high-temperature resistant composite material prepreg are laid to the R-corner arc of the web surface. No high-temperature resistant composite material prepreg is laid at the R-corner arc, and the size of the laid four layers of high-temperature resistant composite material prepreg increases layer by layer from bottom to top, and the four edges of two adjacent layers of high-temperature resistant composite material prepreg are 1 mm apart; then a whole layer of high-temperature resistant rubber pad is laid to cover all surfaces, and two layers of high-temperature resistant rubber pads are laid in the R-corner area, and the two layers of high-temperature resistant rubber pads exceed the R-corner arc; finally, the bags are made and put into the furnace for curing and forming, and the rib uniform pressure plate can be obtained after demoulding.

[0014] The above-mentioned forming method of the integral special-shaped composite material rib, step S4 is specifically as follows: first, after taking the prepared twist strip out from the twist strip tooling, fill it into the double arc filling area of ​​the molded rib according to the shape and size of the twist strip, and hammer the twist strip with a rubber hammer to make the twist strip fill the filling area more fully; then, three layers of carbon fiber fabric prepreg are laid in sequence on the molded rib tooling, and after each whole layer of carbon fiber fabric prepreg is laid, vacuum cold compaction is performed once. During compaction, the vacuum degree is greater than or equal to 0.08Mpa, and the time is at least 15min; finally, a layer of peelable cloth with glue is laid to complete all the laying work of the rib. The above entire laying process needs to be operated in a controllable environment with a temperature of 18℃~26℃ and a humidity of less than 65%.

[0015] The above-mentioned forming method of the integral special-shaped composite material rib, step S2 is specifically as follows: first, the prepreg blanks of the upper and lower half molds of the rib are laid on the upper and lower molding molds of the rib respectively, and then a layer of peelable cloth with glue is laid on the upper and lower molding molds of the rib respectively, so as to facilitate the co-curing and gluing of the formed parts; then, eight layers of carbon fiber prepreg are laid on the upper and lower molding molds of the rib respectively, and after each whole layer of carbon fiber prepreg is laid, vacuum cold compaction is performed once. During compaction, the vacuum degree is greater than or equal to 0.08Mpa, and the time is at least 15min. During the laying process, the carbon fiber prepreg should be prevented from having defects such as wrinkles and accumulation at the R corners or curved surfaces of the mold; finally, the upper and lower molding molds of the rib are closed, and positioned through positioning holes and positioning pins and bolted.

[0016] The above-mentioned method for forming an integral special-shaped composite material rib, step S5 is specifically as follows: first, the rib obtained by paving in S4 is bagged, and when the equalizing plate obtained in S1 is placed, it is knocked with a rubber hammer to make each side of the equalizing plate fit closely with each side of the rib prepreg blank, so as to ensure that the rib prepreg blank is evenly stressed during curing, and to ensure the product quality after the rib is formed; then after the bag making is completed, a vacuum leakage inspection is carried out, and when the vacuum is drawn, the vacuum degree of the solid laminate is not less than 0.08Mpa, and the vacuum gauge reading should not drop by more than 6.77Kpa within 5 minutes; then the rib is placed in an autoclave for curing, and after curing, the temperature is lowered and the rib is taken out of the autoclave to obtain the cured molding of the integral special-shaped composite material rib.

[0017] The preferred solution is to further ensure the quality of the integral special-shaped composite material rib obtained by curing, and the rib product needs to be tested for vacuum again before curing. The vacuum degree shall not be lower than 0.08Mpa, and the drop in the vacuum gauge reading shall not exceed 6.77kpa / 5min.

[0018] Compared with the prior art, the present invention has the following beneficial effects:

[0019] By adopting the molding method of the integral special-shaped composite material rib of the present invention, the integral special-shaped composite material rib can be molded and manufactured at one time, reducing the existing multiple parts to one part, avoiding the segmentation and docking of the parts, on the one hand effectively improving the strength of the rib, on the other hand also saving the original assembly process, shortening the production cycle, reducing the manufacturing cost, and can also make the inner and outer web surfaces of the product flat and smooth, with stable and reliable quality. BRIEF DESCRIPTION OF THE DRAWINGS

[0020] Figure 1 It is a schematic diagram of the process of forming the integral special-shaped composite material rib of the present invention;

[0021] Figure 2 is a diagram of a rib shim plate obtained in an embodiment of a method for forming an integral special-shaped composite material rib according to the present invention;

[0022] Figure 3 It is a diagram showing the rib splitting and laying in the embodiment of the molding method of the integral special-shaped composite material rib of the present invention;

[0023] Figure 4 This is a diagram showing the ribs after being laid and molded in an embodiment of the molding method of the integral special-shaped composite material rib of the present invention;

[0024] Figure 5 5a is a schematic diagram of the production of rib twist strips in an embodiment of the molding method of the integral special-shaped composite material rib of the present invention, wherein 5a is a schematic diagram of the rib twist strip molding tooling, and 5b is a schematic diagram after the unidirectional tape prepreg filaments are filled into the twist strip molding tooling;

[0025] Figure 6 It is a diagram showing the filling of twist strips to the mold seam after the ribs are molded in an embodiment of the molding method of the integral special-shaped composite material rib of the present invention;

[0026] Figure 7 Another diagram of the method for forming an integral special-shaped composite material rib according to the present invention, after the rib is molded and filled with twist strips to the mold seam;

[0027] Figure 8 is a diagram of an integral special-shaped composite material rib produced in an embodiment of the method for forming an integral special-shaped composite material rib according to the present invention;

[0028] Fig. 9 1 is another diagram of an integral special-shaped composite material rib produced in an embodiment of the method for forming an integral special-shaped composite material rib according to the present invention. DETAILED DESCRIPTION

[0029] In order to make the purpose, technical solution and advantages of the present invention more clearly understood, the present invention is further described in detail below in conjunction with the accompanying drawings and embodiments. It should be understood that the specific embodiments described herein are only used to explain the present invention and are not used to limit the present invention.

[0030] like Figure 1 As shown, the present invention provides a method for forming an integral special-shaped composite material rib, comprising the following steps:

[0031] Step S1. Production of the rib pressure plate: firstly, a high temperature resistant rubber pad is laid on the pressure plate tooling, and then a high temperature resistant composite material prepreg is laid on the large and small web surfaces of the pressure plate tooling, and the high temperature resistant composite material prepreg is laid to the R corner arc of the web surface, and the R corner arc is not laid with the high temperature resistant composite material prepreg, then the high temperature resistant rubber pad is laid, and finally, the high temperature resistant rubber pad is laid at the R corner arc, and then the bag is made and put into the furnace for curing and molding, and demoulding is performed to obtain the rib pressure plate;

[0032] Step S2. Laying the prepreg blanks of the upper and lower molds of the rib: firstly, laying the prepreg blanks of the upper and lower molds of the rib respectively on the upper and lower molding molds of the rib, and then laying the adhesive peelable cloth and carbon fiber prepreg on the upper and lower molds of the rib respectively in sequence, and avoiding the occurrence of prepreg wrinkles, accumulation and other defects at the R corners or curved surfaces of the upper and lower molds of the rib, and finally closing the upper and lower molds of the rib;

[0033] Step S3. Twist strip production: according to the double arc filling area of ​​the ribs in the upper and lower molds after the mold is closed in S2, a twist strip with a shape and size matching is produced on the twist strip forming mold using carbon fiber unidirectional tape prepreg;

[0034] Step S4. Filling the twist strips: first, fill the twist strips one by one into the double arc filling area of ​​the molded ribs with matching shapes and sizes, and then lay the carbon fiber fabric prepreg and the adhesive peelable cloth on the molded rib tooling;

[0035] Step S5. Bag making, canning and curing: first make bags for the ribs obtained by paving in S4, place the uniform pressure plate obtained in S1 and tap it, then put the ribs into an autoclave for curing, and take them out of the can to obtain an integral special-shaped composite material rib.

[0036] By means of the molding method of the integral special-shaped composite material rib of the present invention, the integral special-shaped composite material rib can be molded and manufactured at one time, reducing the existing multiple parts to one part, avoiding the segmentation and docking of the parts, on the one hand effectively improving the strength of the rib, on the other hand saving the original assembly process, shortening the production cycle, reducing the manufacturing cost, and making the inner and outer web surfaces of the product flat and smooth, with stable and reliable quality.

[0037] The forming method of the integral special-shaped composite material rib of the present invention is further described below by way of examples.

[0038] Example:

[0039] This embodiment is a molding method of the integral special-shaped composite material ribs of the present invention to manufacture ribs used in the all-composite spoilers of AG300 and AG600 aircraft. The molds required for this molding method include upper and lower molding molds for the ribs, a twist strip molding mold, and a uniform pressure plate molding mold. The specific molding method is:

[0040] The first step is to make the equalizing plate. First, lay a whole layer of high-temperature resistant rubber pads on the equalizing plate tooling, and then lay two layers of high-temperature resistant composite material prepregs on the two large web surfaces. The two layers of high-temperature resistant composite material prepregs are laid to the R-corner arc, and the second layer of high-temperature resistant composite material prepreg needs to be 2 mm smaller than the four sides of the first layer of high-temperature resistant composite material prepreg. A total of four layers of high-temperature resistant composite material prepregs are laid on the small web surface. The four layers of high-temperature resistant composite material prepregs are laid to the R-corner arc, and the next layer of high-temperature resistant composite material prepreg needs to be 1 mm smaller than each side of the previous layer of high-temperature resistant composite material prepreg, decreasing layer by layer, and no high-temperature resistant composite material prepreg is laid in the R-corner area on both sides (R-corner arc); then lay a whole layer of rubber pads to cover all surfaces, and lay two more layers of high-temperature resistant rubber pads in the two R-corner areas, and the two layers of high-temperature resistant rubber pads exceed the R-corner arc; finally, make bags and put them into the furnace for curing and molding. After demolding, you can get a ribbed equalizing plate (such as Figure 2 ), this pressure plate can be reused many times and only needs to be manufactured before the first forming of the rib parts, and does not need to be manufactured again in subsequent production.

[0041] The second step is to lay the prepreg blanks of the upper and lower half molds of the rib. First, lay the prepreg blanks of the upper and lower half molds of the rib on the upper and lower molding molds of the rib respectively. According to the requirements of relevant documents, first, a layer of peelable cloth with adhesive should be laid on the upper and lower molds of the rib respectively, so as to facilitate the co-curing and bonding of the formed parts; then, according to the relevant process documents, 8 layers of carbon fiber prepreg should be laid on the upper and lower molding molds of the rib respectively, and each time a whole layer of prepreg is laid, it is necessary to vacuum cold compact once. When compacting, the vacuum degree should not be less than 0.08Mpa, and the time should be at least 15min. During the laying process, it should be avoided that the prepreg will appear wrinkles, accumulation and other defects at the R corners or curved surfaces of the mold. At the same time, it can ensure that the prepreg is tightly compacted at the R corners and between layers, and the gas mixed in the prepreg layers is completely discharged to ensure product quality; finally, after 8 layers of carbon fiber prepreg are laid on the upper and lower molding molds of the rib, the upper and lower molding molds can be closed, and the upper and lower molding molds are positioned by positioning holes and positioning pins, and the bolts are locked (such as Figure 3 and 4 shown).

[0042] The third step is to make the twist strips. The twist strips are made on the corresponding twist strip forming mold using carbon fiber unidirectional tape prepreg. The material properties of the carbon fiber unidirectional tape prepreg used are consistent with the carbon fiber fabric material properties used for laying the ribs. When making the twist strip, according to the outer circumference of the rib, the unidirectional tape prepreg is first cut into strips with a width of about 40mm, and then the unidirectional tape prepreg strips are cut into filaments with a width of about 2-3mm, and the unidirectional tape prepreg filaments are filled into the twist strip forming tooling in turn. When filling, it is necessary to use a pressure rod to compact the unidirectional tape prepreg filaments, and the unidirectional tape prepreg filaments after filling need to be 0.5-1mm higher than the mold plane; then after filling, the upper pressure plate is installed and tightened with screws to compact, and then the tooling is placed in a 55°-65° drying room for heating and pre-compacting for 2 hours. After heating and compacting, the outer shape (shape and size) of the twist strip can be consistent with the outer shape of the double arc filling area of ​​the rib after mold closing, and the twist strip can be formed more compactly, thereby improving the quality of the twist strip (such as Figure 5 shown).

[0043] The fourth step is to fill the twist strips. First, take out the prepared twist strips from the twist strip tooling, and fill them into the double arc filling area of ​​the molded rib according to the shape of the twist strips; then hammer the twist strips with a rubber hammer to make the twist strips fill the filling area more fully; then, lay 3 layers of carbon fiber fabric prepreg in sequence on the molded rib tooling. After laying each layer of carbon fiber fabric prepreg, vacuum cold compaction is required. When compacting, the vacuum degree should not be less than 0.08Mpa, and the time should be at least 15min; finally, lay a layer of peelable cloth with adhesive to complete all the laying work of the rib (such as Figure 6 and 7 The above whole paving process needs to be operated in a controllable environment with a temperature of 18℃~26℃ and a humidity of less than 65%, which can effectively prevent the material from absorbing too much moisture in the air and ensure the product quality and mechanical properties. Moreover, controlling the temperature within the aforementioned range can ensure that the material is in the most favorable state for operation to the greatest extent, which is conducive to improving product quality and work efficiency.

[0044] The fifth step is bag making and canning for curing and forming. After the ribs are laid, first make bags according to the bag making process and place a uniform pressure plate. At this time, you can use a rubber hammer to knock the uniform pressure plate to make each side of the uniform pressure plate fit closely with each side of the rib prepreg blank to ensure that the rib prepreg blank is evenly stressed during curing and the product quality after the rib is formed; then after the bag making is completed, a vacuum leakage check is carried out: when vacuuming, the vacuum degree of the solid laminate shall not be less than 0.08Mpa, and the vacuum gauge reading shall not drop by more than 6.77Kpa within 5min; then the ribs are placed in the autoclave for curing, and the composite material ribs are cured according to the relevant curing process data. Before curing, the rib parts need to be tested for vacuum again, and the vacuum degree shall not be less than 0.08Mpa, and the vacuum gauge reading shall not drop by more than 6.77kpa / 5min; finally, after curing, when the rib tooling cools down to room temperature, it can be taken out of the can, completing the curing and forming of the integral special-shaped composite material ribs (attached Figure 8 and 9 ).

[0045] The forming method of the integral special-shaped composite material rib adopts a more optimal layering process method, a uniform pressure plate forming method (uniform pressure plate production) and a curing forming process method, so that the forming manufacturing production cycle of the integral special-shaped composite material rib is short, the manufacturing cost is low, the product quality is stable and reliable, and it has good economic benefits. At the same time, it also provides corresponding technical reserves for the production and manufacturing of related special-shaped composite material parts in China. The forming method of the present invention can reduce the structural weight, reduce the production cost and the production cycle, and at the same time improve and stabilize the quality of related parts.

[0046] The above-mentioned embodiments are only preferred embodiments of the present invention and cannot be used to limit the scope of protection of the present invention. Any non-substantial changes and substitutions made by technicians in this field on the basis of the present invention shall fall within the scope of protection required by the present invention.

Claims

1. A method for forming an integral special-shaped composite material rib, characterized in that: include: S1. Rib balancing plate production: First, lay high temperature resistant rubber pads on the balancing plate tooling, then lay high temperature resistant composite material prepregs on the large and small web surfaces of the balancing plate tooling, and lay the high temperature resistant composite material prepregs to the R corner arc of the web surface, and do not lay high temperature resistant composite material prepregs on the R corner arc, then lay the high temperature resistant rubber pads, and finally lay the R corner arc. After laying the high temperature resistant rubber pad at the corner arc, the bag is made and put into the furnace for curing and forming, and then demolding is performed to obtain the rib uniform pressure plate; specifically, firstly, a whole layer of high temperature resistant rubber pad is laid on the uniform pressure plate tooling, and then two layers of high temperature resistant composite material prepreg are laid on the two large web surfaces, and the two layers of high temperature resistant composite material prepreg are laid to the R corner arc of the web surface, and the high temperature resistant composite material prepreg is not laid at the R corner arc, and the laid second layer of high temperature resistant composite material prepreg is smaller than the first layer of high temperature resistant composite material prepreg, and the surrounding edges of the first layer of high temperature resistant composite material prepreg and the surrounding edges of the second layer of high temperature resistant composite material prepreg are 2 mm; then four layers of high-temperature resistant composite material prepreg are laid on the small web surface, and the four layers of high-temperature resistant composite material prepreg are laid to the R-angle arc of the web surface, and the high-temperature resistant composite material prepreg is not laid at the R-angle arc, and the size of the laid four layers of high-temperature resistant composite material prepreg increases layer by layer from bottom to top, and the surrounding edges of two adjacent layers of high-temperature resistant composite material prepreg are 1mm apart; then a whole layer of high-temperature resistant rubber pad is laid to cover all surfaces, and two layers of high-temperature resistant rubber pads are laid in the R-angle area, and the two layers of high-temperature resistant rubber pads exceed the R-angle arc; finally, the bag is made and put into the furnace for curing and forming, and the rib uniform pressure plate can be obtained after demoulding; S2. Laying the prepreg blanks of the upper and lower molds of the rib: First, lay the prepreg blanks of the upper and lower molds of the rib respectively on the upper and lower molding molds of the rib, and then lay the adhesive peelable cloth and carbon fiber prepreg on the upper and lower molds of the rib in turn, and avoid wrinkles and accumulation defects of the prepreg at the R corners or curved surfaces of the upper and lower molds of the rib, and finally close the upper and lower molds of the rib; specifically: first, lay the prepreg blanks of the upper and lower molds of the rib respectively on the upper and lower molding molds of the rib, and then lay a layer of adhesive peelable cloth on the upper and lower molding molds of the rib respectively, so as to facilitate the co-curing bonding of the formed parts; then, respectively Eight layers of carbon fiber prepreg are laid on the upper and lower forming molds of the rib in sequence, and vacuum cold compaction is performed after each layer of carbon fiber prepreg is laid. During compaction, the vacuum degree is greater than or equal to 0.08Mpa, and the time is at least 15 minutes. During the laying process, wrinkles and accumulation defects of the carbon fiber prepreg should be avoided at the R corner or curved surface of the mold; finally, the upper and lower forming molds of the rib are closed, and the positioning holes and positioning pins are used for positioning and bolt locking; the carbon fiber prepreg is a carbon fiber fabric material; S3. Twist strip production: According to the double arc filling area of ​​the ribs in the upper and lower molds after S2 mold closing, carbon fiber unidirectional tape prepreg is used to produce twist strips of suitable shape and size on the twist strip forming mold. ， Specifically, according to the rib circumference, the carbon fiber unidirectional tape prepreg is first cut into a strip with a width of about 40 mm, and then the strip is cut into filaments with a width of 2 to 3 mm. Then, the carbon fiber unidirectional tape prepreg filaments are sequentially filled into the twist strip forming tooling. During filling, a pressure rod is required to compact the carbon fiber unidirectional tape prepreg filaments, and the filled carbon fiber unidirectional tape prepreg filaments are 0.5 to 1 mm higher than the mold plane. Then, a pressure plate is installed on the twist strip forming tooling filled with the carbon fiber unidirectional tape prepreg filaments and tightened and compacted with screws. Finally, the twist strip forming tooling is placed in a drying room at 55° to 65° for heating and pre-compacting for 2 hours. After heating and compacting, a twist strip with a shape and size consistent with the double arc filling area of ​​the rib after mold closing is obtained; the carbon fiber unidirectional tape prepreg is a carbon fiber fabric material; S4. Filling the twist strips: First, fill the twist strips one by one into the double arc filling area of ​​the molded ribs with matching shapes and sizes, and then lay the carbon fiber fabric prepreg and adhesive peelable fabric on the molded rib tooling. ， Specifically, first, after taking out the prepared twist strip from the twist strip tooling, fill it into the double arc filling area of ​​the molded rib according to the shape and size of the twist strip, and hammer the twist strip with a rubber hammer to make the twist strip fill the filling area more fully; then, three layers of carbon fiber fabric prepreg are laid on the molded rib tooling in sequence, and after each layer of carbon fiber fabric prepreg is laid, vacuum cold compaction is performed. During compaction, the vacuum degree is greater than or equal to 0.08Mpa, and the time is at least 15min; finally, a layer of peelable cloth with adhesive is laid to complete all the laying work of the rib. The above entire laying process needs to be carried out at a temperature of 18℃~26℃ and a humidity of less than 65% operated in a controlled environment; S5. Bag making, canning and curing: First, bag the ribs obtained by paving in S4, place the uniform pressure plate obtained in S1 and tap it, then put the ribs into the autoclave for curing, and take them out of the can to obtain the integral special-shaped composite material ribs.

2. The method for forming an integral special-shaped composite material rib according to claim 1, characterized in that: Step S5 is specifically as follows: first, the ribs obtained by paving in S4 are bagged, and when the equalizing plate obtained in S1 is placed, it is knocked with a rubber hammer to make each side of the equalizing plate fit closely with each side of the rib prepreg blank, so as to ensure that the rib prepreg blank is evenly stressed during curing, and the product quality after the rib is formed is ensured; then, after the bagging is completed, a vacuum leakage check is performed, and when the vacuum is drawn, the vacuum degree of the solid laminate is not less than 0.08Mpa, and the vacuum gauge reading should not drop by more than 6.77Kpa within 5 minutes; then, the rib is placed in an autoclave for curing, and after curing, the temperature is lowered and the rib is taken out of the autoclave to obtain the cured molding of the integral special-shaped composite material rib.

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