阅读说明：本技术 复合材料天线碳纤维辐射梁一体成型的方法及成型模具 (Method and mold for integrally molding composite material antenna carbon fiber radiation beam ) 是由 王磊 管稳定 文佳 符伟 刘德礼 于 2021-07-20 设计创作，主要内容包括：本发明提供了一种复合材料天线碳纤维辐射梁一体成型的方法及成型模具,成型模具包括外模和位于外模内的芯模,芯模包括聚苯乙烯泡沫芯轴和包覆于聚苯乙烯泡沫芯轴外表面的乳胶气囊；外模包括下模、上模,乳胶气囊上一体成型的气囊导管上可拆卸连接有连通气嘴；方法包括以下步骤：1)准备上述成型模具；2)在芯模上铺贴碳纤维预浸料,得到碳纤维辐射梁预成型体；3)合模；4)在热压罐内阶梯升温并进行脉冲吹气,固化成型,降温出罐；5)脱模,向乳胶气囊内灌入溶剂,溶解后,抽取出乳胶气囊,再经机加工、打磨、涂装。本发明辐射梁采用碳纤维材料一体成型,制备得到的碳纤维辐射梁中间保持空心、壁厚均匀。(The invention provides a method for integrally forming a composite material antenna carbon fiber radiation beam and a forming die, wherein the forming die comprises an outer die and a core die positioned in the outer die, and the core die comprises a polystyrene foam core shaft and a latex air bag coated on the outer surface of the polystyrene foam core shaft; the outer mold comprises a lower mold and an upper mold, and a communicating air nozzle is detachably connected to an air bag conduit integrally formed on the latex air bag; the method comprises the following steps: 1) preparing the forming die; 2) paving and pasting carbon fiber prepreg on the core mold to obtain a carbon fiber radiation beam preformed body; 3) closing the mold; 4) heating in a hot pressing tank in a stepped manner, performing pulse blowing, curing and forming, cooling and discharging; 5) demoulding, pouring solvent into the latex air bag, dissolving, extracting the latex air bag, machining, polishing and coating. The radiation beam is integrally formed by adopting the carbon fiber material, and the prepared carbon fiber radiation beam keeps hollow in the middle and uniform in wall thickness.)

1. The forming die for integrally forming the composite material antenna carbon fiber radiation beam is characterized by comprising an outer die and a core die (23) positioned in the outer die, wherein the core die (23) comprises a polystyrene foam core shaft (232) and a latex air bag (231) coated on the outer surface of the polystyrene foam core shaft (232); the outer mould includes lower mould (21), goes up mould (22), integrated into one piece has the gasbag pipe on latex gasbag (231), can dismantle on the gasbag pipe and be connected with intercommunication air cock (24).

2. The forming die of claim 1, wherein the lower die (21) and the upper die (22) are connected through a locking screw (25), and the communication air tap (24) is positioned between the connection positions of the upper die (22) and the lower die (21).

3. A method for integrally forming a composite material antenna carbon fiber radiation beam is characterized by comprising the following steps:

1) preparing a molding die according to claim 1 or 2;

2) paving carbon fiber prepreg on the core mold (23) to obtain a carbon fiber radiation beam preformed body;

3) placing the carbon fiber radiation beam preform into the lower die (21), and matching an upper die (22) with the lower die (21) to carry out die assembly;

4) transferring the die after die assembly to an autoclave, connecting a joint of the autoclave with a communicating air nozzle (24) on a latex air bag (231), heating in a step manner in the autoclave, performing pulse blowing, cooling and discharging after a carbon fiber radiation beam is cured and molded;

5) and (3) demolding, pouring a solvent into the latex air bag (231) in the obtained carbon fiber radiation beam, dissolving the polystyrene foam core shaft (232), extracting the latex air bag (231), and then machining, polishing and coating to obtain the carbon fiber radiation beam.

4. A method according to claim 3, wherein the polystyrene foam mandrel (232) is manufactured as follows: foaming polystyrene foam in a polystyrene foam forming die at high temperature to manufacture a polystyrene foam mandrel (232);

the method for manufacturing the latex airbag (231) comprises the following steps: polishing and coarsening the surface of a polystyrene foam mandrel (232), cleaning, soaking in a coagulant for 1-3 min, taking out, soaking in latex solution for 1-3 min, taking out, curing and forming at normal temperature to form a latex air bag (231) outside the polystyrene foam mandrel (232), wherein the latex air bag (231) is integrally formed with an air bag guide pipe;

the manufacturing method of the outer die comprises the following steps: and (3) firstly carrying out rough machining on a numerical control machining center, then carrying out finish milling, removing burrs, ensuring that the assembly clearance is less than or equal to 0.1mm, and manufacturing to obtain the external mold.

5. The method according to claim 3, wherein in the step 2), the carbon fiber prepreg comprises a carbon fiber/epoxy resin fabric prepreg, a multilayer carbon fiber/epoxy resin unidirectional prepreg and a carbon fiber/epoxy resin fabric prepreg from inside to outside, wherein the carbon fiber is one or more of T300, T700 and T800-grade carbon fiber, and the epoxy resin is one of medium-temperature curing epoxy resin and high-temperature curing epoxy resin.

6. The method according to claim 5, wherein the step 2) comprises in particular the steps of: wrapping a layer of high-temperature preservative film on the core mold (23), and then sequentially paving a layer of carbon fiber/epoxy resin fabric prepreg, a plurality of layers of carbon fiber/epoxy resin unidirectional prepreg and a layer of carbon fiber/epoxy resin fabric prepreg on the core mold (23) to obtain a carbon fiber radiation beam preformed body;

after the first layer of prepreg is laid and pasted, vacuumizing and pre-compacting every time after 3-5 layers of prepreg are laid and pasted, wherein the vacuum degree is not lower than-0.085 MPa, and the vacuumizing time is not lower than 5 min;

and (3) starting to lay the prepreg to the 4 th layer from last, laying one layer of prepreg every time, and measuring the outer diameter of the carbon fiber radiation beam preform within +/-2 mm of the tolerance of a theoretical value.

7. The method according to claim 3, wherein in the step 2), a plurality of latex bladder extraction ports for extracting the latex bladders (231) are reserved on the carbon fiber radiation beam preform.

8. The method according to any one of claims 3 to 7, wherein in the step 4), the step-heating and pulse-blowing in the autoclave specifically comprises the steps of:

A. the communicating air nozzle (24) provides 2-4 kg/cm²Heating to 75-95 deg.C at a temperature not higher than 3 deg.C/min under low pressure, and connecting the air nozzle (24) to provide 10-12 kg/cm²High pressure and reduced to 2-4 kg/cm within 1min²Low pressure;

B. the autoclave is heated at a heating rate of not higher than 3 ℃/min, and when the temperature reaches the gel point temperature of the epoxy resin in the prepreg, the communicating air nozzle (24) provides 10-12 kg/cm²High pressure, and when the temperature reaches the curing temperature of the epoxy resin in the prepreg, keeping the temperature and the pressure for 20-60 min;

C. the autoclave is cooled to below 60 ℃ at the cooling rate of not higher than 3 ℃/min, the air pressure of the communicating air nozzle (24) is closed, and the autoclave is taken out.

9. The method according to any one of claims 3 to 7, wherein the step 2) further comprises embedding an aluminum alloy embedded part (13) at the connecting position of the carbon fiber radiation beam, the antenna and the central cylinder.

10. The method according to any one of claims 3 to 7, wherein in the step 3), before the carbon fiber radiation beam preform is placed in the lower die (21), a layer of carbon fiber/epoxy resin fabric prepreg is laid at the R-angle positions of the upper die (22) and the lower die (21) of the outer die, and then a rolled twisted carbon fiber/epoxy resin unidirectional prepreg ribbon is placed;

in the step 5), the machining specifically comprises the following steps: taking a reference hole of a machining tool as a machining reference, installing the assembly surface and the assembly hole of the reflection surface and the central cylinder on the machined carbon fiber radiation beam, and installing a steel wire thread sleeve (14) in the assembly hole; the polishing specifically comprises the following steps: the carbon fiber radiation beam is polished once along one direction by using 100-150 # abrasive paper, and then the carbon fiber radiation beam is polished once along the direction vertical to the first polishing direction.

Technical Field

The invention belongs to the technical field of radiation beams, and particularly relates to a method and a mold for integrally molding a composite material antenna carbon fiber radiation beam.

Background

The radiation beam is the main supporting component of the antenna reflection surface, is mainly applied to various antenna structures and mainly plays a role in reflecting electromagnetic waves. At present, the traditional radiation beam is mainly formed by welding and gluing T-shaped steel, angle steel, steel pipes and other profiles, and is of an all-steel structure, heavy in monomer weight and poor in corrosion resistance. The traditional radiation beam is assembled on an antenna reflector, so that the whole weight of the antenna is increased, the antenna is not convenient to carry and accurately drive, the welding strength is not high, the size precision is not high, and therefore the weight of the radiation beam is reduced, which is the central weight of the whole antenna product.

The patent with the application number of 201310525888.6 discloses a carbon fiber antenna radiation beam and a manufacturing method thereof, wherein a carbon fiber circular tube is adopted to replace the traditional section steel as a beam frame, and the butt joint of the carbon fiber circular tube is connected by a steel joint in an adhesive mode. This carbon fiber antenna radiation beam has changed traditional antenna radiation beam steel structure, adopts carbon fiber material as the main material to make with sticky technique, alleviate radiation beam weight greatly, intensity is big, and the rigidity is good, and simple process has moreover overcome a great deal of not enough of traditional antenna radiation beam. However, the carbon fiber round tube of the carbon fiber antenna radiation beam needs to be butted by steel joints, and the stability of a product can be affected if the joints are loosened or damaged in the using process.

Disclosure of Invention

The invention aims to solve the technical problem of overcoming the defects and shortcomings in the background technology and provides a method and a mold for integrally molding a composite material antenna carbon fiber radiation beam.

In order to solve the technical problems, the technical scheme provided by the invention is as follows:

a forming die for integrally forming a composite material antenna carbon fiber radiation beam comprises an outer die and a core die positioned in the outer die, wherein the core die comprises a polystyrene foam core shaft and a latex air bag coated on the outer surface of the polystyrene foam core shaft; the outer die comprises a lower die and an upper die, the latex air bag is integrally formed with an air bag conduit, and the air bag conduit is detachably connected with a communicating air nozzle.

Preferably, the lower die and the upper die are connected through a locking screw, and the communicating air nozzle is located between the connecting position of the upper die and the lower die.

As a general inventive concept, the present invention provides a method for integrally forming a carbon fiber radiation beam of a composite material antenna, comprising the steps of:

1) preparing the forming die;

2) paving and pasting carbon fiber prepreg on the core mold to obtain a carbon fiber radiation beam preformed body;

3) placing the carbon fiber radiation beam preformed body into the lower die, and matching the upper die with the lower die to carry out die assembly;

4) transferring the die after die assembly to a hot-pressing tank, connecting a joint of the hot-pressing tank with a communicating air tap on the latex air bag, heating in the hot-pressing tank in a stepped manner, performing pulse blowing, and cooling and discharging the carbon fiber radiation beam after curing and forming;

5) and (3) demolding, namely filling a solvent (acetone, butanone and the like) into the latex air bag in the obtained carbon fiber radiation beam, dissolving the polystyrene foam core shaft, extracting the latex air bag, and then machining, polishing and coating the latex air bag to obtain the carbon fiber radiation beam.

Preferably, the polystyrene foam core shaft is manufactured by the following method: foaming polystyrene foam in a polystyrene foam forming die at high temperature to manufacture a polystyrene foam mandrel;

the manufacturing method of the latex air bag comprises the following steps: polishing and coarsening the surface of the polystyrene foam mandrel, cleaning, soaking the polystyrene foam mandrel in a coagulant for 1-3 min, taking out, soaking the polystyrene foam mandrel in latex solution for 1-3 min, taking out, and curing and forming at normal temperature to form an emulsion air bag outside the polystyrene foam mandrel, wherein the emulsion air bag is integrally formed with an air bag guide pipe;

the manufacturing method of the outer die comprises the following steps: and (3) firstly carrying out rough machining on a numerical control machining center, then carrying out finish milling, removing burrs, ensuring that the assembly clearance is less than or equal to 0.1mm, and manufacturing to obtain the external mold.

Preferably, in the step 2), the carbon fiber prepreg comprises, from inside to outside, a carbon fiber/epoxy resin fabric prepreg, a multilayer carbon fiber/epoxy resin unidirectional prepreg, and a carbon fiber/epoxy resin fabric prepreg, wherein the carbon fiber is one or more of T300, T700, and T800-grade carbon fibers, and the epoxy resin is one of medium-temperature curing epoxy resin and high-temperature curing epoxy resin.

Preferably, the step 2) specifically comprises the following steps: wrapping a layer of high-temperature preservative film on the core mold, and then sequentially paving a layer of carbon fiber/epoxy resin fabric prepreg, a plurality of layers of carbon fiber/epoxy resin unidirectional prepreg and a layer of carbon fiber/epoxy resin fabric prepreg on the core mold to obtain a carbon fiber radiation beam preformed body; the laying angle, the laying sequence and the number of the laying layers of the carbon fiber/epoxy resin prepreg are better results obtained according to mechanical simulation;

after the first layer of prepreg is laid and pasted, vacuumizing and pre-compacting every time after 3-5 layers of prepreg are laid and pasted, wherein the vacuum degree is not lower than-0.085 MPa, and the vacuumizing time is not lower than 5 min;

and (3) starting to lay the prepreg to the 4 th layer from last, laying one layer of prepreg every time, and measuring the outer diameter of the carbon fiber radiation beam preform within +/-2 mm of the tolerance of a theoretical value.

Preferably, in the step 2), a plurality of latex airbag extraction ports for extracting the latex airbags are reserved on the carbon fiber radiation beam pre-forming body.

Preferably, in the step 4), the step-heating and pulse-blowing in the autoclave specifically includes the following steps:

A. the communicating nozzle provides 2-4 kg/cm²Heating to 75-95 deg.C at a temperature not higher than 3 deg.C/min under low pressure, and connecting with gas nozzle to provide 10-12 kg/cm²High pressure and reduced to 2-4 kg/cm within 1min²Low pressure;

B. the autoclave is heated at a heating rate of not higher than 3 ℃/min, and when the temperature reaches the gel point temperature of the epoxy resin in the prepreg, a communicating air nozzle provides 10-12 kg/cm²High pressure, and when the temperature reaches the curing temperature of the epoxy resin in the prepreg, keeping the temperature and the pressure for 20-60 min;

C. cooling the autoclave to below 60 ℃ at a cooling rate of not higher than 3 ℃/min, closing the air pressure of the communicating air nozzle, and discharging.

The invention adopts the processes of step heating and pulse blowing, and can effectively improve the quality of the inside and the outside of the carbon fiber radiation beam.

Preferably, the step 2) further comprises pre-embedding an aluminum alloy embedded part at the connecting position of the carbon fiber radiation beam, the antenna and the central cylinder.

Preferably, in the step 3), before the carbon fiber radiation beam pre-forming body is placed in the lower die, a layer of carbon fiber/epoxy resin fabric prepreg is laid at the R-angle positions of the upper die and the lower die of the outer die, and then the rolled carbon fiber/epoxy resin unidirectional prepreg twisted strips are placed;

in the step 5), the machining specifically comprises the following steps: taking a reference hole of a machining tool as a machining reference, installing a steel wire thread sleeve in an assembling surface and an assembling hole of the reflection surface and the central cylinder on the machining carbon fiber radiation beam; the polishing specifically comprises the following steps: the carbon fiber radiation beam is polished once along one direction by using 100-150 # abrasive paper, and then the carbon fiber radiation beam is polished once along the direction vertical to the first polishing direction.

Compared with the prior art, the invention has the beneficial effects that:

1. the invention adopts a core mould comprising a polystyrene foam (EPS) core shaft and a latex air bag, carbon fiber/epoxy resin prepreg is laid on the core mould, the mould is closed again, the temperature is raised in a step manner, and the carbon fiber radiation beam is cured and formed by pulse blowing. The invention utilizes a blowing process method, the radiation beam is integrally formed by adopting carbon fiber materials, and the prepared carbon fiber radiation beam keeps hollow in the middle and uniform in wall thickness. The surface quality refers to HB7224-1995, general technical conditions of composite material member, the film-sticking surface is smooth and flat, and has no obvious wrinkle, concave pit and projection, and an ultrasonic detector is used for making nondestructive detection according to GJB1038.1A-2004, nondestructive detection method of fibre-reinforced composite material so as to attain the requirements of grade B and above.

2. The invention changes the traditional steel structure of the radiant beam, and even the carbon fiber structure in the traditional process can not be integrally formed, and the invention has the advantages of replacing the steel structure, simultaneously not needing the pipe-to-pipe connection through the joint glue joint, and having the advantages of light weight, high strength, good rigidity, corrosion resistance, simple process and the like.

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 introduced below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and for those skilled in the art, other drawings can be obtained according to these drawings without creative efforts.

Fig. 1 is an exploded view of a mold for integrally molding a composite material antenna carbon fiber radiation beam according to the present invention;

fig. 2 is a cross-sectional view of a mandrel of the present invention;

FIG. 3 is a schematic structural diagram of a carbon fiber radiation beam produced by the present invention;

illustration of the drawings:

11. a carbon fiber radiant beam body; 12. a carbon fiber radiant beam cover plate; 13. aluminum alloy embedded parts; 14. a steel wire thread insert; 21. a lower die; 22. an upper die; 23. a core mold; 231. a latex air bag; 232. a polystyrene foam mandrel; 24. communicating the air tap; 25. locking the screw; 26. a lower die guide post; 27. a lifting eye screw; 28. an upper die bushing; 29. and (6) ejecting the block.

Detailed Description

In order to facilitate understanding of the invention, the invention will be described more fully and in detail with reference to the accompanying drawings and preferred embodiments, but the scope of the invention is not limited to the specific embodiments below.

Unless otherwise defined, all terms of art used hereinafter have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used herein is for the purpose of describing particular embodiments only and is not intended to limit the scope of the present invention.

Unless otherwise specifically stated, various raw materials, reagents, instruments, equipment and the like used in the present invention are commercially available or can be prepared by existing methods.

Example 1:

a forming mold for integrally forming a composite material antenna carbon fiber radiation beam, as shown in fig. 1 and fig. 2, the forming mold comprises an outer mold and a core mold 23 positioned in the outer mold, the core mold 23 comprises a polystyrene foam core shaft 232 and a latex air bag 231 coated on the outer surface of the polystyrene foam core shaft 232; the outer mold comprises a lower mold 21 and an upper mold 22, an air bag conduit is integrally formed on the latex air bag 231, a communicating air tap 24 (which is separately arranged in figure 1 and is connected during use) is detachably connected onto the air bag conduit, specifically, the air bag conduit and the communicating air tap 24 can be sleeved and then locked through a nut.

In this embodiment, the lower mold 21 and the upper mold 22 are connected by a locking screw 25, the communication air nozzle 24 is located at the joint of the upper mold 22 and the lower mold 21 and is locked with the upper mold 22 and the lower mold 21, that is, the joint of the upper mold 22, the lower mold 21 and the communication air nozzle 24 is provided with a matching opening, and the communication air nozzle 24 is clamped after the upper mold 22 and the lower mold 21 are closed.

In this embodiment, the parting surface of the outer mold is the middle cross section of the radiation beam; the external dimension of the emulsion air bag 231 is obtained by subtracting the wall thickness of the carbon fiber radiation beam from 4/3-5/4 of the external dimension of the carbon fiber radiation beam, and the external dimension of the polystyrene foam core shaft 232 is obtained by subtracting the wall thickness of the emulsion air bag 231 from the external dimension of the emulsion air bag 231.

In the forming die of the embodiment, the upper die 22 and the lower die 21 are both provided with an ejection block 29 and a lifting bolt 27, the lower die 21 is provided with a lower die guide post 26, a glue overflow groove and an exhaust groove, and the upper die 22 is provided with an upper die bushing 28 matched with the lower die guide post 24 (in fig. 1, the upper die bushing 28 and the upper die 22 are in a detachable state).

Example 2:

a method for integrally forming a composite material antenna carbon fiber radiation beam specifically comprises the following steps:

(1) designing and manufacturing a die: respectively designing and manufacturing an external mold and a core mold 23 for forming the carbon fiber radiation beam, wherein the external mold is manufactured in a machining mode, and the core mold 23 is manufactured through mold forming, and the method specifically comprises the following specific steps:

A. designing an external mold: designing an external mold for molding the carbon fiber radiation beam according to the drawing and technical requirements of the radiation beam, wherein the parting surface is the middle cross section of the radiation beam;

B. designing a core mold: the core die 23 comprises a latex air bag 231 and a polystyrene foam core shaft 232 positioned in the latex air bag 231, the external dimension of the latex air bag 231 is the size obtained by subtracting the wall thickness of the carbon fiber radiation beam 4/3 from the external dimension of the carbon fiber radiation beam on one side, and the external dimension of the polystyrene foam core shaft 232 is the size obtained by subtracting the wall thickness (0.8-1.2 mm) of the latex air bag 231 from the external dimension of the latex air bag 231;

C. manufacturing a polystyrene foam mandrel: EPS foaming is carried out in an EPS forming die at high temperature to manufacture a polystyrene foam mandrel 232;

D. manufacturing of the latex airbag: polishing and coarsening the surface of the polystyrene foam mandrel 232, cleaning, soaking in a coagulant (B liquid) for 1-3 min, taking out, soaking in an emulsion (A liquid) for 1-3 min, taking out, and curing and forming at normal temperature to form an emulsion air bag 231 outside the polystyrene foam mandrel 232; the latex balloon 231 is integrally formed with a balloon catheter, and the latex balloon 231 is connected to the communicating air nipple 24 through the balloon catheter.

E. Manufacturing of the outer die: rough machining is firstly carried out on a numerical control machining center, then fine milling is carried out, burrs are removed, and the assembly clearance is guaranteed to be less than or equal to 0.1 mm.

(2) Manufacturing and analyzing a layer, blanking: the CPD module through CATIA spreads the layer to the three-dimensional digifax of carbon fiber radiation roof beam and makes the analysis, opens the laying-out at CATIA's CPD module to optimize the row material in AutoCAD, use automatic blanking machine to carry out the unloading to carbon fiber/epoxy preimpregnation material, and carry out the serial number and divide into groups.

(3) Laying a prepreg: wrapping a layer of high-temperature preservative film on a core mold, then sequentially paving and pasting a layer of T300 carbon fiber/medium-temperature curing epoxy resin fabric prepreg, a plurality of layers of T700 carbon fiber/medium-temperature curing epoxy resin unidirectional prepregs and a layer of T300 carbon fiber/medium-temperature curing epoxy resin fabric prepreg, paving and pasting a first layer of prepreg and then vacuumizing and pre-compacting after paving and pasting 3-5 layers of prepreg, wherein the vacuum degree is not lower than-0.085 MPa, the vacuumizing time is not lower than 5min, starting from the paving and pasting of the prepreg to the 4 th layer from last, paving and pasting a layer of prepreg, measuring the outer diameter of a carbon fiber radiation beam preform, and obtaining the carbon fiber radiation beam preform within the tolerance of a theoretical value of +/-2 mm.

When laying a layer, pre-burying an aluminum alloy embedded part 13 at the connecting position of the carbon fiber carbon radiation beam, the antenna and the central cylinder, and reserving a plurality of latex air bag extraction ports on the carbon fiber carbon radiation beam pre-forming body so as to extract the latex air bags 231 subsequently.

(4) Die assembly: firstly, paving a layer of carbon fiber/epoxy resin fabric prepreg at the R-angle positions of an upper die 22 and a lower die 21 of an outer die, then placing a rolled carbon fiber/epoxy resin unidirectional prepreg twisted strip, then placing a carbon fiber radiation beam preformed body on the lower die 21, matching the upper die 22 with the lower die 21, closing the dies, locking a locking screw 25 between the upper die 22 and the lower die 21, and locking a communicating air nozzle 24.

(5) High-temperature high-pressure curing molding: the mould after the compound die is transferred to the autoclave, the autoclave joint is connected with the communicating air tap 24 of the radiation beam forming mould, the ladder in the autoclave is heated up and the pulse is blown (the pulse is blown to the latex air bag 231 through the communicating air tap 24 and the air bag guide pipe in sequence), and the method specifically comprises the following steps:

A. the communicating air nozzle 24 provides 2-4 kg/cm²Low pressure, when the temperature in the autoclave is raised to 80 + -5 ℃ at a temperature rise rate of not higher than 3 ℃/min, the gas nozzle 24 is connected to provide 10-12 kg/cm²High pressure and reduced to 2-4 kg/cm within 1min²Low voltage (pulsed);

B. the autoclave is heated to 130 plus or minus 5 ℃ at a heating rate of not more than 3 ℃/min, and when the temperature reaches 105 plus or minus 5 ℃ (the gel point temperature of the medium-temperature cured epoxy resin), the communicating air nozzle 24 provides 10-12 kg/cm²High pressure, when the temperature reaches 130 +/-5 ℃ (the curing temperature of the medium-temperature curing epoxy resin), keeping the temperature and the pressure for 30-60 min;

C. cooling the autoclave to below 60 ℃ at a cooling rate of not higher than 3 ℃/min, closing air tap and air pressure, and discharging.

(6) Demolding and taking out the core mold: dismantle locking screw 25 in proper order, open and go up mould 22, ejecting solidified carbon fiber radiation beam through ejecting block 29, will communicate air cock 24 and dismantle from the gasbag pipe, solvent acetone is poured into to latex gasbag 231 in the rethread gasbag pipe, acetone dissolves polystyrene foam dabber 232 back, a plurality of latex gasbag extraction openings that rethread carbon fiber radiation beam reserved extract latex gasbag 231, extract from a latex gasbag extraction opening earlier during specific extraction, extract from other latex gasbag extraction openings after the latex gasbag fracture again.

(7) Machining: and taking the reference hole of the machining tool as a machining reference, installing the assembly surface and the assembly hole of the reflection surface and the central cylinder on the machining carbon fiber radiation beam, and installing a steel wire thread sleeve in the assembly hole.

(8) Polishing and coating: the carbon fiber radiation beam is polished once along one direction by using 100-150 # abrasive paper, then the carbon fiber radiation beam is polished once along the direction vertical to the first polishing direction, the outer surface of the carbon fiber radiation beam is polished to be dull and lusterless, if pinholes or poor glue exist on the surface of the carbon fiber radiation beam, transparent atomic ash is needed to be used for hole sealing treatment, and finally paint specified by technical requirements is sprayed.

Example 3:

the method for integrally forming the composite material antenna carbon fiber radiation beam is different from the embodiment 2 in that the step (3) and the step (5) are specifically as follows:

(3) laying a carbon fiber prepreg: wrapping a layer of high-temperature preservative film on a core mould 23, then sequentially paving and pasting a layer of T300 carbon fiber/high-temperature curing epoxy resin fabric prepreg, a plurality of layers of T700 carbon fiber/high-temperature curing epoxy resin unidirectional prepreg and a layer of T300 carbon fiber/high-temperature curing epoxy resin fabric prepreg, embedding an aluminum alloy embedded part 13 at the connecting position of a carbon fiber radiation beam and an antenna and a central cylinder, paving and pre-compacting the first layer of prepreg and the later 3-5 layers of prepreg after paving and pre-compacting by vacuumizing, wherein the vacuum degree is not lower than-0.085 MPa, the vacuumizing time is not lower than 5min, starting when the prepreg is paved to the last 4 layers, paving and each layer of prepreg, measuring the outer diameter of a carbon fiber radiation beam preform, and obtaining the carbon fiber radiation beam preform within +/-2 mm of the tolerance of a theoretical value;

(5) high-temperature high-pressure curing molding: transferring the die after die assembly to an autoclave, connecting an autoclave joint with a communicating air tap 24 of a radiation beam forming die, and performing step heating and pulse blowing in the autoclave, wherein the method specifically comprises the following steps:

A. the communicating air nozzle 24 provides 2-4 kg/cm²Low pressure, when the temperature in the autoclave is raised to 90 plus or minus 5 ℃ at a temperature rise rate of not more than 3 ℃/min, the communicating air nozzle 24 provides 10 to 12kg/cm²High pressure and reduced to 2-4 kg/cm within 1min²Low voltage (pulsed);

B. the autoclave is heated to 150 +/-5 ℃ at a heating rate of not more than 3 ℃/min, and when the temperature reaches 120 +/-5 ℃ (the gel point temperature of the high-temperature cured epoxy resin), 10-12 kg/cm is provided by the communicating air nozzle 24²High pressure, when the temperature reaches 150 +/-5 ℃ (the curing temperature of the high-temperature curing epoxy resin), keeping the temperature and the pressure for 20-30 min;

C. cooling the autoclave to below 60 ℃ at a cooling rate of not higher than 3 ℃/min, closing air tap and air pressure, and discharging;

the remaining steps (1), (2), (4), (6), (7) and (8) are the same as in example 2.

The carbon fiber radiation beam finally prepared in embodiments 2 and 3 of the present invention is shown in fig. 3, and includes a carbon fiber radiation beam main body 11, a carbon fiber radiation beam cover plate 12, an aluminum alloy embedded part 13, and a steel wire thread sleeve 14 installed on the aluminum alloy embedded part 13, wherein the carbon fiber radiation beam cover plate 12 is used for sealing a latex air bag extraction opening reserved in the carbon fiber radiation beam, and the carbon fiber radiation beam main body 11 and the carbon fiber radiation beam cover plate 12 are connected by gluing.

The surface quality of the carbon fiber radiation beam finally prepared in the embodiments 2 and 3 of the invention refers to HB7224-1995, general technical conditions of composite material members, the film surface is smooth and flat, no obvious wrinkles, pits and bulges exist, and an ultrasonic detector is used for nondestructive detection according to GJB1038.1A-2004, nondestructive detection method of fiber reinforced composite materials, so that the requirements of B level and above are met.