CN113246339A - Laminated carbon fiber reinforced prepreg material and method for forming coated missile wing by using same - Google Patents
Laminated carbon fiber reinforced prepreg material and method for forming coated missile wing by using same Download PDFInfo
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- CN113246339A CN113246339A CN202110800222.1A CN202110800222A CN113246339A CN 113246339 A CN113246339 A CN 113246339A CN 202110800222 A CN202110800222 A CN 202110800222A CN 113246339 A CN113246339 A CN 113246339A
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- carbon fiber
- fiber reinforced
- reinforced prepreg
- missile wing
- main beam
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
- B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
- B29B15/122—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex
- B29B15/125—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex by dipping
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—Shaping by lay-up, i.e. applying fibres, tape or broadsheet on a mould, former or core; Shaping by spray-up, i.e. spraying of fibres on a mould, former or core
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
- B29C70/386—Automated tape laying [ATL]
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/777—Weapons
- B29L2031/7772—Cartridges
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Robotics (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Reinforced Plastic Materials (AREA)
- Laminated Bodies (AREA)
Abstract
The application relates to a laminated carbon fiber reinforced prepreg material and a method for forming a missile wing by utilizing the laminated carbon fiber reinforced prepreg material. And carrying out normal-temperature plasma modification by adopting a dielectric barrier discharge reactor to obtain a modified carbon fiber fabric, conveying the modified carbon fiber fabric to a roller at room temperature, immersing the roller into PPS resin glue solution to obtain carbon fiber reinforced prepreg cloth, and laminating the prepreg cloth to obtain the missile wing. The sulfur-containing atmosphere is added in the plasma source gas, so that the bonding property with the sulfur-containing resin is improved conveniently, the coarsening effect can be realized through the plasma treatment, and finally, the elastic modulus and the breaking strength can be improved.
Description
Technical Field
The application belongs to the technical field of preparation and application of composite materials, and particularly relates to a preparation method of a carbon fiber reinforced prepreg material and a forming method for obtaining a missile wing after the material is laminated.
Background
The missile wing is a main wing surface connected to the missile body, and has the main functions of generating air lift force, lifting the missile body and playing a role in stable control. With the higher requirement of modern weapons on the aerodynamic performance of flight, the wing profiles of the missile wings are thinner and thinner, the bending rigidity is smaller and smaller, and the problem of aeroelasticity is more and more serious. The conventional missile wing is made of light alloy or composite material, and the carbon fiber reinforced prepreg is used as the missile wing at present and has the excellent characteristics of low specific weight and the like. The carbon fiber reinforced prepreg composite material has good designability, so that the carbon fiber reinforced prepreg composite material is greatly applied to the weight reduction of an aircraft structure. However, as the missile wing generates deformation, vibration, divergence, flutter and other phenomena in the flying process, if the vibration deformation is large, large alternating stress is easy to generate, fatigue cracks are easy to cause, and higher requirements are provided for the structural strength of the carbon fiber reinforced prepreg composite material.
Disclosure of Invention
The carbon fiber fabric is pretreated, normal-temperature plasma modification is carried out in a dielectric barrier discharge reactor, mixed gas of high-purity hydrogen sulfide and oxygen is introduced between electrodes of a reaction chamber, the flow rate of the introduced gas is 20-25mL/min, the volume ratio of the hydrogen sulfide to the oxygen is (0.2-0.4): 1, an alternating current power supply with the voltage of 10kHz and 20-25kV is applied to the dielectric barrier discharge reactor to generate normal-temperature sulfur-containing plasma, and a sample is subjected to treatment for 1-2 min.
Immersing the modified carbon fiber fabric into PPS resin glue solution at room temperature through a conveying roller, uniformly coating the carbon fiber fabric on two sides of a sample, standing for a period of time, and immersing the resin glue solution again to enable the resin to soak the carbon fiber fabric; removing redundant resin through rolling to reach a preset thickness to obtain carbon fiber reinforced prepreg cloth, placing the carbon fiber cloth immersed with glue solution on a double-roller open mill, adjusting the distance between two rollers, starting the machine, repeatedly rolling to remove redundant resin, enabling the resin content to reach a standard, heating the double-roller open mill to 55-65 ℃, facilitating the volatilization of low-boiling-point solvents in the resin glue solution, simultaneously improving the prepreg degree until the resin is uniformly impregnated in the carbon fiber, and taking down the prepreg cloth.
The missile wing main beam comprises a missile wing end part and a profile part, the end part is a windward side in the flying process, the missile wing main beam is of a high-strength steel frame structure, the surface of the missile wing main beam is provided with a hollow structure to reduce weight, the missile wing main beam end part comprises an upper cambered surface and a lower cambered surface, the profile part is divided into an upper profile and a lower profile, carbon fiber reinforced prepreg cloth is laid in each region of the surface of the missile wing, and then the carbon fiber reinforced prepreg cloth is heated and cured to obtain the carbon fiber composite missile wing.
The specific carbon fiber composite material missile wing laying, coating and winding forming method mainly comprises the following steps:
1) laying 14 layers of carbon fiber reinforced prepreg cloth on the upper molded surface of the main missile wing beam by adopting a transitional positioning tool;
2) laying 38 layers of carbon fiber reinforced prepreg cloth on the lower molded surface of the main beam of the missile wing by adopting a transitional positioning tool;
3) 4 layers of carbon fiber reinforced prepreg cloth are respectively paved in the unfolding direction of the upper cambered surface and the lower cambered surface of the missile wing main beam;
4) 4 layers of carbon fiber reinforced prepreg cloth are wound on the side surface of the main beam of the missile wing;
5) and heating and curing the laid missile wing main beam, and removing the forming tool after heating and curing for 2 hours at 120 ℃ in the forming tool.
The sulfur-containing atmosphere is added in the plasma source gas, so that the bonding property with the sulfur-containing resin is improved conveniently, and the plasma treatment can also realize the coarsening effect. The carbon fiber is easy to brittle fracture, the specific surface area of the carbon fiber is increased through the coarsening effect of the plasma, the bonding area with the resin in the immersion process is increased, in addition, the sulfur-containing active groups are formed on the surface of the carbon fiber through the plasma of oxygen and hydrogen sulfide gas, the bonding property with the PPS resin is improved, and the strength of the laminated structure is integrally improved. The PPS resin has high thermal stability, chemical corrosion resistance and flame retardance, and can improve the flame retardance and the stability of the missile wing. The missile wing prepared from the carbon fiber reinforced prepreg cloth has the characteristics of high elastic modulus and breaking strength, is more suitable for real environment, and improves the use stability.
Drawings
FIG. 1 is a schematic structural view of a main beam of the missile wing.
In the figure: 1. an upper arc surface; 2. a lower arc surface; 3. a lower profile; 4. an upper profile.
Detailed Description
Example 1:
the carbon fiber fabric is pretreated, normal-temperature plasma modification is carried out in a dielectric barrier discharge reactor, mixed gas of high-purity hydrogen sulfide and oxygen is introduced between electrodes of a reaction chamber, the flow rate of the introduced gas is 25mL/min, the volume ratio of the hydrogen sulfide to the oxygen is 0.3:1, a 10kHz and 23kV alternating current power supply is applied to the dielectric barrier discharge reactor to generate normal-temperature sulfur-containing plasma, and a sample is subjected to treatment for 1-2 min.
Immersing the modified carbon fiber fabric into PPS resin glue solution at room temperature through a conveying roller, uniformly coating the carbon fiber fabric on two sides of a sample, standing for a period of time, and immersing the resin glue solution again to enable the resin to soak the carbon fiber fabric; removing redundant resin through rolling to reach a preset thickness to obtain carbon fiber reinforced prepreg cloth, placing the carbon fiber cloth immersed with glue solution on a double-roller open mill, adjusting the distance between two rollers, starting the machine, repeatedly rolling to remove the redundant resin, enabling the resin content to reach a standard, heating the double-roller open mill to 55-65 ℃, facilitating the volatilization of low-boiling-point solvents in the resin glue solution, simultaneously improving the prepreg degree until the resin is uniformly impregnated in the carbon fiber, taking down the prepreg cloth, stacking the prepreg cloth for multiple layers, and heating and curing for 2 hours at 120 ℃ in a forming tool to obtain a laminated structure.
And stretching the prepared sample on an INSTRON5569 testing machine, and processing the obtained force and displacement data to obtain the tensile modulus and breaking strength data of the sample.
Examples 2 to 4 and comparative examples 1 to 5
Examples 2 to 4 and comparative examples 1 to 4 were prepared to obtain a laminate structure by the same process as in example 1, specific process parameters were adjusted, and tensile modulus and breaking strength were measured for each type of sample. Comparative example 5 carbon fibers were not modified and PPS immersion and laminate preparation were carried out in the manner described in example 1.
The tensile modulus and the breaking strength of the laminated structure obtained by preparing the carbon fiber reinforced prepreg cloth without surface modification are lower than those of the laminated structure after surface modification, the missile wing can be influenced by complex airflow in the flying process to generate the phenomena of deformation, vibration and the like, if the vibration deformation is large, large alternating stress is easily generated, fatigue cracks are easily caused, the high elastic modulus can resist the stress, the large deformation is avoided, and the breaking strength is high, so that the reliability of the missile wing can be improved. The comparative examples 1 to 4 change the volume ratio of hydrogen sulfide to oxygen, the proportional relation of the hydrogen sulfide and the oxygen can influence the types and the number of active functional groups generated after plasma ionization, and the proper proportion can enable the modified carbon fiber and the dangling bond of the PPS resin to form bonding, improve the bonding performance and finally improve the mechanical property of the laminated structure.
TABLE 1 preparation parameters and Properties
Comparative examples 6 to 8
Comparative examples 6 to 8 a laminate structure was prepared by the same procedure as in example 1, the specific resin species were adjusted, and the tensile modulus and the breaking strength were measured for each type. Tests show that different resins and the laminated structure prepared from the modified carbon fiber fabric have different performances, the sulfur-containing resin is selected, and a sulfur-containing active group is formed on the surface of the carbon fiber in the modification process, so that the bonding performance between the carbon fiber and the resin can be better improved, and the specific resin types and performances are shown in table 2.
TABLE 2 resin types and Properties
Example 5
The end part of the main beam of the missile wing comprises an upper cambered surface 1 and a lower cambered surface 2, the section surface is divided into an upper section surface 4 and a lower section surface 3, carbon fiber reinforced prepreg cloth is laid in each area of the surface of the missile wing, and then the carbon fiber reinforced prepreg cloth is heated and cured to obtain the carbon fiber composite missile wing. The specific carbon fiber composite material missile wing laying, coating and winding forming method mainly comprises the following steps: 1) laying 14 layers of carbon fiber reinforced prepreg cloth on the upper molded surface 4 of the missile wing main beam by adopting a transitional positioning tool; 2) laying 38 layers of carbon fiber reinforced prepreg cloth on the lower molded surface 3 of the main beam of the missile wing by adopting a transitional positioning tool; 3) 4 layers of carbon fiber reinforced prepreg cloth are respectively paved in the spanwise direction of the upper cambered surface 1 and the lower cambered surface 2 of the main beam of the missile wing; 4) 4 layers of carbon fiber reinforced prepreg cloth are wound on the side surface of the main beam of the missile wing; 5) and heating and curing the laid missile wing main beam, and removing the forming tool after heating and curing for 2 hours at 120 ℃ in the forming tool.
Claims (2)
1. A laminated carbon fiber reinforced prepreg material is characterized in that a dielectric barrier discharge reactor is adopted to carry out normal temperature plasma modification to obtain a modified carbon fiber fabric, the modified carbon fiber fabric is immersed into PPS resin glue solution at room temperature through a transfer roller and is uniformly coated on two sides of a sample, excess resin is removed through rolling to reach a preset thickness to obtain carbon fiber reinforced prepreg, the carbon fiber fabric immersed with the glue solution is placed on a double-roller open mill to be repeatedly rolled, the carbon fiber fabric modification method comprises the steps of introducing high-purity hydrogen sulfide and oxygen mixed gas between electrodes of a reaction chamber, introducing the flow rate of aeration is 20-25mL/min, the volume ratio of hydrogen sulfide to oxygen is (0.2-0.4): 1, applying an alternating current power supply of 10kHz and 20-25kV to the dielectric barrier discharge reactor to generate normal temperature sulfur-containing plasma, the sample was subjected to treatment for 1-2 min.
2. A missile wing molding method which utilizes the laminated carbon fiber reinforced prepreg material as the structural component, which is characterized in that the molding method mainly comprises the following steps:
1) laying 14 layers of carbon fiber reinforced prepreg cloth on the upper molded surface of the main missile wing beam by adopting a transitional positioning tool;
2) laying 38 layers of carbon fiber reinforced prepreg cloth on the lower molded surface of the main beam of the missile wing by adopting a transitional positioning tool;
3) 4 layers of carbon fiber reinforced prepreg cloth are respectively paved in the unfolding direction of the upper cambered surface and the lower cambered surface of the missile wing main beam;
4) 4 layers of carbon fiber reinforced prepreg cloth are wound on the side surface of the main beam of the missile wing;
5) and heating and curing the laid missile wing main beam, and removing the forming tool after heating and curing for 2 hours at 120 ℃ in the forming tool.
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| CN202110800222.1A CN113246339B (en) | 2021-07-15 | 2021-07-15 | Carbon fiber reinforced prepreg material and method for forming coated missile wing by using same |
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| CN202110800222.1A CN113246339B (en) | 2021-07-15 | 2021-07-15 | Carbon fiber reinforced prepreg material and method for forming coated missile wing by using same |
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Denomination of invention: Carbon fiber reinforced prepreg material and its coating wing forming method Effective date of registration: 20211215 Granted publication date: 20210921 Pledgee: Tianjin Kerong Financing Guarantee Co.,Ltd. Pledgor: BEIJING AEROSPACE TIANMEI TECHNOLOGY Co.,Ltd.|BEIJING HANGTIAN HEXING TECHNOLOGY Co.,Ltd. Registration number: Y2021120000068 |
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Address after: Area B, No.1 Factory building, No.26 Siwei Road, development zone, Dongli District, Tianjin Patentee after: BEIJING AEROSPACE TIANMEI TECHNOLOGY Co.,Ltd. Patentee after: Beijing Aerospace Hexing Technology Co.,Ltd. Address before: Area B, No.1 Factory building, No.26 Siwei Road, development zone, Dongli District, Tianjin Patentee before: BEIJING AEROSPACE TIANMEI TECHNOLOGY Co.,Ltd. Patentee before: BEIJING HANGTIAN HEXING TECHNOLOGY Co.,Ltd. |
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Date of cancellation: 20230303 Granted publication date: 20210921 Pledgee: Tianjin Kerong Financing Guarantee Co.,Ltd. Pledgor: BEIJING HANGTIAN HEXING TECHNOLOGY Co.,Ltd.|BEIJING AEROSPACE TIANMEI TECHNOLOGY Co.,Ltd. Registration number: Y2021120000068 |