WO2019149010A1 - 一种复合材料构件的成型方法和复合材料构件 - Google Patents

一种复合材料构件的成型方法和复合材料构件 Download PDF

Info

Publication number
WO2019149010A1
WO2019149010A1 PCT/CN2018/125133 CN2018125133W WO2019149010A1 WO 2019149010 A1 WO2019149010 A1 WO 2019149010A1 CN 2018125133 W CN2018125133 W CN 2018125133W WO 2019149010 A1 WO2019149010 A1 WO 2019149010A1
Authority
WO
WIPO (PCT)
Prior art keywords
pressure
preset
mold
prepreg
male mold
Prior art date
Application number
PCT/CN2018/125133
Other languages
English (en)
French (fr)
Inventor
刘若鹏
赵治亚
冯业恒
左扬
胡紫阳
Original Assignee
深圳光启尖端技术有限责任公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 深圳光启尖端技术有限责任公司 filed Critical 深圳光启尖端技术有限责任公司
Publication of WO2019149010A1 publication Critical patent/WO2019149010A1/zh

Links

Images

Classifications

    • 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
    • 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
    • B29C70/32—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 on a rotating mould, former or core
    • 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
    • B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • 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
    • B29C70/34—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation
    • B29C70/342—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 and shaping or impregnating by compression, i.e. combined with compressing after the lay-up operation using isostatic pressure
    • 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
    • B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/40—Weight reduction

Definitions

  • the present invention relates to a molding method in the field of material technology, and in particular to a molding method of a composite member and a composite member.
  • Composite materials are used in aerospace, petroleum, chemical, metallurgical, electric power and other fields due to their good resistance to high temperature creep, corrosion resistance, high yield strength and fracture toughness.
  • the existing composite member has many molding methods, but all have certain defects.
  • the prior art discloses a prepreg compression molding method, which utilizes the thermal expansion property of the silica gel sheet to form a silica gel in the heating molding.
  • the internal pressure generated by the heat of the sheet causes the prepreg to obtain uniform pressure in all directions, thereby solving the technical problem that the side of the molded member is insufficiently subjected to the positive pressure and the internal tensile force, but in this method, when the shape of the member is complicated, The shape and thickness of the silica gel sheets at different positions are different, resulting in different coefficients of thermal expansion.
  • the present invention provides a method for forming a composite member and a composite member, which solves the problem of delamination, pores, pores, etc. which are prone to occur at the corners of the member in the existing vacuum bag compression molding method.
  • a practical problem in addition, compared to the prior art of a prepreg compression molding method, it can make the member more uniformly stressed when pressed on the male mold and the flexible foam material, and, compared to The prior art of a "C"-shaped rubber core molding method, a molding method for a "work” member, and a molding device for a "work” member, a structure that can be made due to excellent plasticity of the flexible foam material More complex composite products.
  • a method of forming a composite member is provided.
  • the method for molding the composite member comprises: step S1, preparing a male mold, a foam material and a prepreg according to actual requirements; and step S2, laying a prepreg on the male mold according to the designed layup order and the number of layers; Step S3, the male mold and the foam material are compacted to obtain a mold clamping structure, and then the prepreg is solidified and formed under the designed temperature, pressure and time conditions; in step S4, after the curing is completed, the mold release is taken out and solidified.
  • Composite component preparing a male mold, a foam material and a prepreg according to actual requirements; and step S2, laying a prepreg on the male mold according to the designed layup order and the number of layers; Step S3, the male mold and the foam material are compacted to obtain a mold clamping structure, and then the prepreg is solidified and formed under the designed temperature, pressure and time conditions; in step S4, after the curing is completed, the mold release is taken out and solidified.
  • Composite component preparing a
  • step S3 includes: step S31, pressing the mold clamping structure to the first preset pressure according to the preset first preset pressure; and step S32, according to the preset first temperature gradient, The mold clamping structure is heated to a first preset temperature, and the pressure is maintained during the first time period; and in step S33, the mold clamping structure is pressurized to the second preset pressure according to the preset first pressure gradient.
  • the step S32 and the step S33 further comprise: heating the mold clamping structure to the second preset temperature according to the preset second temperature gradient, and maintaining the pressure holding during the second time period.
  • the step S33 further comprises: pressurizing the clamping structure to the third preset pressure according to the preset second pressure gradient.
  • the step S1 further comprises: applying a release agent on the inner surface of the male mold.
  • step S1 further comprises: fixedly connecting the male mold and the pressure plate.
  • step S31 the vacuuming process is performed on the mold clamping structure during the third time period.
  • the step S3 comprises: placing the mold clamping structure into the vacuum bag, and connecting the vacuum bag and the vacuum pump to perform vacuuming treatment by the vacuum pump.
  • the release agent comprises at least one of the following: oleic acid, paraffin, stearic acid, silicone grease release agent, silicone oil release agent, zinc stearate, silicone grease or silicone rubber.
  • a composite member is provided.
  • the composite member includes a composite member that is formed by a molding method of any of the above composite members.
  • the invention prepares the male mold, the foam material and the prepreg according to actual requirements, and then lays the prepreg on the male mold according to the designed layup order and the number of layers, and then compactly connects the male mold and the foam material.
  • the prepreg is then solidified under the designed temperature, pressure and time conditions, and finally, after the curing is completed, the cured composite member is demolded, thereby using the male mold and the foam material as compaction.
  • the auxiliary means of prepreg because the foam material is very plastic when pressed, and can ensure that the force of the member is uniformly adjustable in all directions, and then the pressure and temperature processing curves are set by the process, so that the member is fully and evenly compacted, thereby achieving Improve delamination, pores and air gaps, etc.
  • FIG. 1 is a flow chart of a method of forming a composite member in accordance with an embodiment of the present invention
  • FIG. 2 is a schematic view of a forming mold according to an embodiment of the present invention.
  • FIG. 3 is a flow chart of a method of forming a composite member in accordance with an embodiment of the present invention.
  • a method of forming a composite member is provided.
  • a molding method of a composite member includes: step S101, preparing a male mold, a foam material, and a prepreg according to actual requirements; and step S103, on the male mold, according to the design of the paving
  • the layer sequence and the number of layers are pasted with the prepreg; in step S105, the male mold and the foam material are compacted to obtain a mold clamping structure, and then the prepreg is solidified under the designed temperature, pressure and time conditions; step S107 After the curing is completed, the cured composite member is taken out by demolding.
  • the male mold, the foam material and the prepreg are prepared according to actual requirements, and then the prepreg is laid on the male mold according to the designed layup order and the number of layers, followed by the male mold and the foam material.
  • Compacting the joint to obtain a mold clamping structure then solidifying the prepreg under the designed temperature, pressure and time conditions, and finally, after the curing is completed, demolding and removing the solidified composite member, thereby utilizing the male mold and the foam
  • the material is plastically good under pressure and can ensure uniform adjustment of force in all directions of the member. Then, the pressure and temperature processing curves are set by the process, so that the member is fully and uniformly pressed. In order to achieve improved delamination, pores and air gaps and other uncompressed images.
  • the molding die comprises a male mold (or a hard mold) 1, a foam material (or flexible foam material) 2, and a pressure-bonding plate 3, wherein the male mold 1 and the foam material 2 form a closed space, and The prepreg is laid on the inner surface of the male mold 1 according to the layup design.
  • the male mold 1 and the pressure plate 3 are fixedly connected, so that the male mold 1 can be pressed by the pressure plate 3, and further, the mold 1 is placed thereon.
  • An opening for evacuating is provided.
  • the manufacturing cost of the mold will increase a lot, so the mold we manufacture is most suitable for components with small shapes and complex structures.
  • the specific process of the molding method of the composite member includes:
  • Step 31 according to the shape of the product, manufacturing a hard mold (or hard male mold) 1, and through the blanking machine to cut the foam material 2 matched with the male mold 1, from the outside, according to actual needs, through the cutting machine Prepreg
  • Step 32 on the inner surface of the male mold 1 shown in FIG. 2, the prepreg is laid according to the designed layup order and the number of layers;
  • Step S33 the male mold 1 and the flexible foam material 2 are compacted to form a sealed space, and the flexible foam material 2 is further wrapped with a separator, so that the flexible foam material 2 is used as a mold half, thereby the male mold 1 Forming a mold clamping structure with the flexible foam material 2, and then vacuuming the mold clamping structure to remove air between the male mold 1 and the prepreg. Further, it is understood that the vacuum processing process is in progress.
  • the parameter (such as the third time period) can be set according to actual needs.
  • the clamping structure is evacuated for at least 15 minutes under a pressure of -0.95 Bar. This is not limited;
  • Step S34 the mold clamping structure is placed into the curing tank, and the pressure in the tank is pressurized to the first preset pressure according to the preset first preset pressure.
  • the first preset The specific value of the pressure can be set according to actual needs.
  • the tank can be pressurized to a first preset pressure of 100 to 115 psi by using a pressurized fluid having a pressure of 60 to 80 psi.
  • the invention is not limited thereto;
  • Step S35 heating the mold clamping structure to a first preset temperature according to a preset first temperature gradient, and maintaining the pressure during the first time period.
  • the first temperature gradient and the first The specific value of the temperature can be set according to actual needs.
  • the mold clamping structure is heated to a preset temperature of 65 ° C at 1 ° C / min, and the holding pressure is maintained for 15 min, so that the prepreg is Fully compacted;
  • Step S36 pressurizing the clamping structure to the second preset pressure according to the preset first pressure gradient.
  • the specific values of the second temperature gradient and the second preset temperature can be performed according to actual needs. Providing, for example, according to an embodiment of the present invention, continuing to increase the pressure on the pressure plate 3 to a second preset pressure of 120 to 180 psi;
  • step S37 the mold is heated according to the curing curve, the resin is solidified, and the mold is removed.
  • a release agent may be applied to the inner surface of the male mold 1 in advance to facilitate demolding, and at the same time, the release agent includes, but is not limited to, oleic acid, paraffin, stearic acid, and silicone grease. Release agent, silicone oil release agent, zinc stearate, silicone grease or silicone rubber.
  • step S35 further includes: heating the clamping structure to the first according to the preset second temperature gradient.
  • step S36 further comprises: pressurizing the pressure in the tank to the third pre- according to the preset second pressure gradient Set pressure.
  • the method of forming the composite member includes the following steps:
  • Step A manufacturing the male mold 1 of the mold according to the shape of the product, and discharging the foam material 2 and the prepreg;
  • Step B cutting the prepreg according to the requirements of the layering process, and laying it on the male mold 1 with the release cloth;
  • Step C compactly connecting the male mold 1 and the flexible foam material 2 to form a sealed space, and the flexible foam material 2 is wrapped with a separator to close the mold;
  • Step E vacuuming the sealing mold with a vacuum pump, at least -15 minutes below -0.95 Bar, removing air between the mold and the prepreg;
  • Step F pressurizing the tank to a first preset pressure of 100 to 115 psi using a pressurized fluid having a pressure of 60 to 80 psi;
  • Step G heating the mold to a preset temperature of 65 ° C at 1 ° C / min, holding the pressure for 15 min, so that the prepreg is fully compacted;
  • Step H continue to increase the pressure on the pressure plate 3 to a second preset pressure of 120 to 180 psi, heat the mold according to the curing curve, cure the resin, and release the mold.
  • the flow in this embodiment is basically the same as that in the first embodiment, and the difference is that the temperature gradient is increased in the step G, and the pressure is maintained according to the temperature gradient.
  • the degree of infiltration of the resin is further increased, and the product can be made closer and the complex structure product can be manufactured.
  • the method of forming the composite member includes the following steps:
  • Step A manufacturing the male mold 1 of the mold according to the shape of the product, and discharging the foam material 2 and the prepreg;
  • Step B cutting the prepreg according to the requirements of the layering process, and laying it on the male mold 1 with the release cloth;
  • Step C compactly connecting the male mold 1 and the flexible foam material 2 to form a sealed space, and the flexible foam material 2 is wrapped with a separator to close the mold;
  • Step E vacuuming the sealing mold with a vacuum pump, at least -15 minutes below -0.95 Bar, removing air between the mold and the prepreg;
  • Step F using a pressurized fluid having a pressure of 60 to 80 psi to pressurize the bladder to a first preset pressure of 100 to 115 psi;
  • Step G heating the mold to a preset temperature of 30 ° C at 1 ° C / min, holding the pressure for 10 min; then heating to a preset temperature of 65 ° C at 1 ° C / min, holding and holding for 30 min; the resin is fully wet;
  • Step H continue to increase the pressure on the pressure plate 3 to a second preset pressure of 120 to 180 psi, heat the mold according to the curing curve, cure the resin, and release the mold.
  • the flow in this embodiment is basically the same as that in the first embodiment, and the difference is that the pressure gradient is increased in the step H, and the pressure is maintained by the pressure gradient.
  • the degree of infiltration of the resin is further increased, and the product can be made closer and the complex structure product can be manufactured.
  • the method of forming the composite member includes the following steps:
  • Step A manufacturing the male mold 1 of the mold according to the shape of the product, and discharging the foam material 2 and the prepreg;
  • Step B cutting the prepreg according to the requirements of the layering process, and laying it on the male mold 1 with the release cloth;
  • Step C compactly connecting the male mold 1 and the flexible foam material 2 to form a sealed space, and the flexible foam material 2 is wrapped with a separator to close the mold;
  • Step E vacuuming the sealing mold with a vacuum pump, at least -15 minutes below -0.95 Bar, removing air between the mold and the prepreg;
  • Step F pressurizing the tank to a first preset pressure of 100 to 115 psi using a pressurized fluid having a pressure of 60 to 80 psi;
  • Step G heating the mold to a preset temperature of 30 ° C at 1 ° C / min, holding the pressure for 10 min; then heating to a preset temperature of 65 ° C at 1 ° C / min, holding and holding for 30 min; the resin is fully wet;
  • Step H continue to increase the pressure on the pressure plate 3 to a second preset pressure of 120-150 psi, continue to increase the pressure of the pressure plate 3 to a third preset pressure of 150 psi to 180 psi; heat the mold according to the curing curve, the resin is solidified, and the mold release treatment is performed. .
  • a composite member is also provided.
  • the composite member includes a composite member that is formed by a molding method of any of the above composite members.
  • the male mold, the foam material and the prepreg are prepared according to actual requirements, and then the prepreg is laid on the male mold according to the designed layup order and the number of layers. Then, the male mold and the foam material are compacted and joined to obtain a mold clamping structure, and then the prepreg is solidified under the designed temperature, pressure and time conditions, and finally, after the curing is completed, the solidified composite material member is demolded and taken out.
  • the male mold and the foam material as an auxiliary means for compacting the prepreg, since the foam material is plastically good under pressure and can ensure uniform adjustment of the force in all directions of the member, the pressure and temperature are processed through the process. The curve is such that the member is sufficiently uniformly compacted to achieve an improved uncompressed image such as delamination, porosity and air gap.

Landscapes

  • Chemical & Material Sciences (AREA)
  • Engineering & Computer Science (AREA)
  • Composite Materials (AREA)
  • Mechanical Engineering (AREA)
  • Casting Or Compression Moulding Of Plastics Or The Like (AREA)

Abstract

一种复合材料构件的成型方法，该成型方法包括：步骤S1，按照实际要求，准备阳模(1)、泡沫材料(2)和预浸料；步骤S2，在阳模(1)上，按照设计的铺层顺序及层数铺贴预浸料；步骤S3，将阳模(1)和泡沫材料(2)压实连接，以得到合模结构，然后使预浸料在设计的温度、压力和时间条件下固化成型；步骤S4，在固化结束后，脱模取出固化的复合材料构件。该方法通过利用阳模(1)和泡沫材料(2)作为压实预浸料的辅助手段，由于泡沫材料(2)在受压时可塑性很好且能保证构件各方向受力均匀可调，再则通过工艺设置压力和温度加工曲线，使得构件被充分均匀压实，从而达到改善分层，气孔和气隙等未压实现象。

Description

一种复合材料构件的成型方法和复合材料构件 技术领域
本发明涉及材料技术领域的成型方法，具体来说，涉及一种复合材料构件的成型方法和复合材料构件。
背景技术
复合材料构件由于具有良好的抗高温蠕变、耐蚀性、高屈服强度和断裂韧性，用于航空航天、石油、化工、冶金、电力等领域。
此外，现有的复合材料构件的成型方法较多，但都存在一定缺陷，例如，现有技术公开了一种预浸料模压成型方法，其通过利用硅胶片的热膨胀性能，在加热成型中硅胶片受热产生内压使预浸料在各个方向上获得均匀压力，从而解决了成型构件侧面所受正压力不足和遭受的内拉力影响的技术问题，然而在此方法中，当构件形状复杂时，不同位置的硅胶片的外形和厚度都不相同，从而导致其热膨胀系数不同，当热压罐加热时难以控制其膨胀压力，甚至会由于压力不同而使得制件变形；另外一个现有技术公开了一种“C”形橡胶芯模成型方法、用于“工”形构件的成型方法和用于“工”形构件的成型装置，其通过利用未硫化橡胶铺设在橡胶芯模成型模具的凹部内并与所述凹部紧密贴合，然而在此方法中，由于硫化橡胶自身具有一定的形状，各方向的膨胀系数不同，所以硫化橡胶在受热时膨胀不均匀，从而导致预浸料在一定程度上受力不均匀，对于构件曲面容易产生内侧拉力。
针对相关技术中的问题，目前尚未提出有效的解决方案。
发明内容
针对相关技术中的问题，本发明提出一种复合材料构件的成型方法和复合材料构件，其解决了现有的真空袋压成型方法中构件拐角处易出现的 分层、孔隙、气孔等未压实的问题，此外，其相比于一种预浸料模压成型方法的现有技术，其在阳模和柔性泡沫材料上加压时可使得构件受力更加均匀，以及，其相比于一种“C”形橡胶芯模成型方法、用于“工”形构件的成型方法和用于“工”形构件的成型装置的现有技术，由于柔性泡沫材料的可塑性极好，可以制的结构更加复杂的复合材料制品。
本发明的技术方案是这样实现的：
根据本发明的一个方面，提供了一种复合材料构件的成型方法。
该复合材料构件的成型方法包括：步骤S1，按照实际要求，准备阳模、泡沫材料和预浸料；步骤S2，在阳模上，按照设计的铺层顺序及层数铺贴预浸料；步骤S3，将阳模和泡沫材料压实连接，以得到合模结构，然后使预浸料在设计的温度、压力和时间条件下固化成型；步骤S4，在固化结束后，脱模取出固化的复合材料构件。
根据本发明的一个实施例，步骤S3包括：步骤S31，根据预设的第一预设压力，将合模结构加压至第一预设压力；步骤S32，根据预设的第一温度梯度，将合模结构加热至第一预设温度，并在第一时间段内保温保压；步骤S33，根据预设的第一压力梯度，将合模结构加压至第二预设压力。
根据本发明的一个实施例，步骤S32和步骤S33之间还包括：根据预设的第二温度梯度，将合模结构加热至第二预设温度，并在第二时间段内保温保压。
根据本发明的一个实施例，步骤S33还包括：根据预设的第二压力梯度，将合模结构加压至第三预设压力。
根据本发明的一个实施例，步骤S1还包括：在阳模的内表面上涂抹脱模剂。
根据本发明的一个实施例，步骤S1还包括：将阳模和压合板固定连接。
根据本发明的一个实施例，步骤S31之前包括：在第三时间段内，对合模结构进行抽真空处理。
根据本发明的一个实施例，步骤S3包括：将合模结构放置到真空袋内，并将真空袋和真空泵连接，从而通过真空泵进行抽真空处理。
根据本发明的一个实施例，脱模剂包括以下至少之一：油酸、石蜡、 硬脂酸、硅脂脱模剂、有机硅油脱模剂、硬脂酸锌、硅脂或硅橡胶。
根据本发明的另一方面，提供了一种复合材料构件。
该复合材料构件包括：复合材料构件通过上述任一项复合材料构件的成型方法制得。
本发明的有益技术效果在于：
本发明通过按照实际要求，准备阳模、泡沫材料和预浸料，随后在阳模上，按照设计的铺层顺序及层数铺贴预浸料，随后将阳模和泡沫材料压实连接，以得到合模结构，然后使预浸料在设计的温度、压力和时间条件下固化成型，最后在固化结束后，脱模取出固化的复合材料构件，从而通过利用阳模和泡沫材料作为压实预浸料的辅助手段，由于泡沫材料在受压时可塑性很好且能保证构件各方向受力均匀可调，再则通过工艺设置压力和温度加工曲线，使得构件被充分均匀压实，从而达到改善分层，气孔和气隙等未压实现象。
附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1是根据本发明实施例的复合材料构件的成型方法的流程图；
图2是根据本发明实施例的成形模具的示意图；
图3是根据本发明具体实施例的复合材料构件的成型方法的流程图。
具体实施方式
下面将结合本发明实施例中的附图，对本发明实施例中的技术方案进行清楚、完整地描述，显然，所描述的实施例仅仅是本发明一部分实施例，而不是全部的实施例。基于本发明中的实施例，本领域普通技术人员所获 得的所有其他实施例，都属于本发明保护的范围。
根据本发明的实施例，提供了一种复合材料构件的成型方法。
如图1所示，根据本发明实施例的复合材料构件的成型方法包括：步骤S101，按照实际要求，准备阳模、泡沫材料和预浸料；步骤S103，在阳模上，按照设计的铺层顺序及层数铺贴预浸料；步骤S105，将阳模和泡沫材料压实连接，以得到合模结构，然后使预浸料在设计的温度、压力和时间条件下固化成型；步骤S107，在固化结束后，脱模取出固化的复合材料构件。
借助于上述技术方案，通过按照实际要求，准备阳模、泡沫材料和预浸料，随后在阳模上，按照设计的铺层顺序及层数铺贴预浸料，随后将阳模和泡沫材料压实连接，以得到合模结构，然后使预浸料在设计的温度、压力和时间条件下固化成型，最后在固化结束后，脱模取出固化的复合材料构件，从而通过利用阳模和泡沫材料作为压实预浸料的辅助手段，由于泡沫材料在受压时可塑性很好且能保证构件各方向受力均匀可调，再则通过工艺设置压力和温度加工曲线，使得构件被充分均匀压实，从而达到改善分层，气孔和气隙等未压实现象。
为了更好的描述本发明的技术方案，下面通过具体的实施例进行详细的描述。
如图2所示，该成型模具包括阳模(或硬模)1、泡沫材料(或柔性泡沫材料)2和压合板3，其中，阳模1与泡沫材料2形成一个密闭的空间，同时，预浸料按铺层设计方案铺覆于阳模1的内表面上，另外，将阳模1和压合板3固定连接，从而可通过压合板3对阳模1施加压力，此外，模具1上设置有用于抽真空的开口。另外，当制备的复合材料构件的深度很深时，对于压力的控制难度会大幅增加，当温度要求较高时，会受到泡沫材料2的温度限制，此时生产成本会大幅提高，同时，考虑到泡沫使用寿命的问题，模具的制造成本会增加很多，因此我们所制造的模具，最适合用于形体较小且结构复杂的构件。
此外，如图3所示，该复合材料构件的成型方法的具体流程包括：
步骤31，根据产品的形状，制造硬模(或硬性阳模具)1，并通过下 料机下料和阳模1相匹配的泡沫材料2，从外，还根据实际需求，通过下料机下料预浸料；
步骤32，在如图2所示的阳模1的内表面上，按照设计的铺层顺序及层数铺贴预浸料；
步骤S33，将阳模1与柔性泡沫材料2压实连接，形成一个密封的空间，且柔性泡沫材料2上还包裹隔离膜，从而将柔性泡沫材料2用作一个半模，从而将阳模1与柔性泡沫材料2合模，得到合模结构，然后对该合模结构进行抽真空处理，从而除去阳模1和预浸料之间的空气，此外，当然可以理解，该抽真空处理过程中的参数(如第三时间段)可根据实际需求进行设置，例如，根据本发明的一个实施例，在-0.95Bar的压力条件下，对该合模结构进行抽真空至少15分钟，本发明对此不作限定；
步骤S34，将合模结构放入至固化罐内，并根据预设的第一预设压力，将罐内的压力加压至第一预设压力，此外，当然可以理解，该第一预设的压力的具体数值可根据实际需求进行设置，例如，根据本发明的一个实施例，可通过利用压力为60～80psi的有压流体将罐内的加压至第一预设压力100～115psi，本发明对此不作限定；
步骤S35，根据预设的第一温度梯度，将合模结构加热至第一预设温度，并在第一时间段内保温保压，此外，当然可以理解，该第一温度梯度和第一预设温度的具体数值可根据实际需求进行设置，例如，根据本发明的一个实施例，将合模结构以1℃/min加热至预设温度65℃，保温保压15min，从而使预浸料被充分压实成型；
步骤S36，根据预设的第一压力梯度，将合模结构加压至第二预设压力，此外，当然可以理解，该第二温度梯度和第二预设温度的具体数值可根据实际需求进行设置，例如，根据本发明的一个实施例，继续增加压合板3上压力至第二预设压力120～180psi；
步骤S37，按固化曲线加热模具，树脂固化，脱模处理。
另外，还可在步骤31中，预先在阳模1的内表面上涂抹脱模剂，从而便于脱模，同时，该脱模剂包括但不限于：油酸、石蜡、硬脂酸、硅脂脱模剂、有机硅油脱模剂、硬脂酸锌、硅脂或硅橡胶。
此外，还可根据实际需求对上述流程适当的增加或者减少相应的流程，例如，根据本发明的一个实施例，步骤S35还包括：根据预设的第二温度梯度，将合模结构加热至第二预设温度，并在第二时间段内保温保压；根据本发明的另一个实施例，步骤S36还包括：根据预设的第二压力梯度，将罐内的压力加压至第三预设压力。
为了便于理解本发明的上述技术方案，下面通过具体的实施例进行详细的描述。
实施例一
该复合材料构件的成型方法包括以下步骤：
步骤A：根据产品的形状制造模具的阳模1，并且下料泡沫材料2和预浸料；
步骤B：将预浸料按铺层工艺要求裁剪、铺覆于带脱模布的阳模1上；
步骤C：将阳模1与柔性泡沫材料2压实连接，形成一个密封的空间，且柔性泡沫材料2上包裹隔离膜，合模；
步骤E：对密封模具用真空泵抽真空，-0.95Bar以下至少15分钟，除去模具及预浸料之间的空气；
步骤F：利用压力为60～80psi的有压流体将罐内加压至第一预设压力100～115psi；
步骤G：将模具以1℃/min加热至预设温度65℃，保温保压15min，使预浸料被充分压实成型；
步骤H：继续增加压合板3上压力至第二预设压力120～180psi，按固化曲线加热模具，树脂固化，脱模处理。
实施例二
本实施例中的流程与实施例一基本相同，其不同之处在于：在步骤G中增加温度梯度，按温度梯度保温保压。在固化阶段，进一步提高树脂的浸润程度，可以使产品更紧密，制造复杂结构产品。该复合材料构件的成型方法包括以下步骤：
步骤A：根据产品的形状制造模具的阳模1，并且下料泡沫材料2和预浸料；
步骤B：将预浸料按铺层工艺要求裁剪、铺覆于带脱模布的阳模1上；
步骤C：将阳模1与柔性泡沫材料2压实连接，形成一个密封的空间，且柔性泡沫材料2上包裹隔离膜，合模；
步骤E：对密封模具用真空泵抽真空，-0.95Bar以下至少15分钟，除去模具及预浸料之间的空气；
步骤F：利用压力为60～80psi的有压流体将气囊加压至第一预设压力100～115psi；
步骤G：将模具以1℃/min加热至预设温度30℃，保温保压10min；之后以1℃/min加热至预设温度65℃，保温保压30min；树脂充分浸润；
步骤H：继续增加压合板3上的压力至第二预设压力120～180psi，按固化曲线加热模具，树脂固化，脱模处理。
实施例三
本实施例中的流程与实施例一基本相同，其不同之处在于：在步骤H中增加压力梯度，按压力梯度保温保压。在固化阶段，进一步提高树脂的浸润程度，可以使产品更紧密，制造复杂结构产品。该复合材料构件的成型方法包括以下步骤：
步骤A：根据产品的形状制造模具的阳模1，并且下料泡沫材料2和预浸料；
步骤B：将预浸料按铺层工艺要求裁剪、铺覆于带脱模布的阳模1上；
步骤C：将阳模1与柔性泡沫材料2压实连接，形成一个密封的空间，且柔性泡沫材料2上包裹隔离膜，合模；
步骤E：对密封模具用真空泵抽真空，-0.95Bar以下至少15分钟，除去模具及预浸料之间的空气；
步骤F：利用压力为60～80psi的有压流体将罐内加压至第一预设压力100～115psi；
步骤G：将模具以1℃/min加热至预设温度30℃，保温保压10min；之后以1℃/min加热至预设温度65℃，保温保压30min；树脂充分浸润；
步骤H：继续增加压合板3上的压力至第二预设压力120～150psi，继续增加压合板3的压力至第三预设压力150psi～180psi；按固化曲线加热模 具，树脂固化，脱模处理。
根据本发明的实施例，还提供了一种复合材料构件。
该复合材料构件包括：复合材料构件通过上述任一项复合材料构件的成型方法制得。
综上所述，借助于本发明的上述技术方案，通过按照实际要求，准备阳模、泡沫材料和预浸料，随后在阳模上，按照设计的铺层顺序及层数铺贴预浸料，随后将阳模和泡沫材料压实连接，以得到合模结构，然后使预浸料在设计的温度、压力和时间条件下固化成型，最后在固化结束后，脱模取出固化的复合材料构件，从而通过利用阳模和泡沫材料作为压实预浸料的辅助手段，由于泡沫材料在受压时可塑性很好且能保证构件各方向受力均匀可调，再则通过工艺设置压力和温度加工曲线，使得构件被充分均匀压实，从而达到改善分层，气孔和气隙等未压实现象。
以上所述仅为本发明的较佳实施例而已，并不用以限制本发明，凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。

Claims (10)

  1. 一种复合材料构件的成型方法，其特征在于，包括：
    步骤S1，按照实际要求，准备阳模、泡沫材料和预浸料；
    步骤S2，在所述阳模上，按照设计的铺层顺序及层数铺贴所述预浸料；
    步骤S3，将所述阳模和所述泡沫材料压实连接，以得到合模结构，然后使所述预浸料在设计的温度、压力和时间条件下固化成型；
    步骤S4，在固化结束后，脱模取出固化的复合材料构件。
  2. 根据权利要求1所述的成型方法，其特征在于，所述步骤S3包括：
    步骤S31，根据预设的第一预设压力，将所述合模结构加压至所述第一预设压力；
    步骤S32，根据预设的第一温度梯度，将所述合模结构加热至第一预设温度，并在第一时间段内保温保压；
    步骤S33，根据预设的第一压力梯度，将所述合模结构加压至第二预设压力。
  3. 根据权利要求3所述的成型方法，其特征在于，所述步骤S32和所述步骤S33之间还包括：
    根据预设的第二温度梯度，将所述合模结构加热至第二预设温度，并在第二时间段内保温保压。
  4. 根据权利要求4所述的成型方法，其特征在于，所述步骤S33还包括：
    根据预设的第二压力梯度，将所述合模结构加压至第三预设压力。
  5. 根据权利要求1所述的成型方法，其特征在于，所述步骤S1还包括：
    在所述阳模的内表面上涂抹脱模剂。
  6. 根据权利6所述的成型方法，其特征在于，所述步骤S1还包括：
    将所述阳模和压合板固定连接。
  7. 根据权利要求2所述的成型方法，其特征在于，所述步骤S31之前包括：
    在第三时间段内，对所述合模结构进行抽真空处理。
  8. 根据权利要求7所述的成型方法，其特征在于，所述步骤S3包括：
    将所述合模结构放置到真空袋内，并将所述真空袋和真空泵连接，从而通过所述真空泵进行所述抽真空处理。
  9. 根据权利要求5所述的成型方法，其特征在于，所述脱模剂包括以下至少之一：油酸、石蜡、硬脂酸、硅脂脱模剂、有机硅油脱模剂、硬脂酸锌、硅脂或硅橡胶。
  10. 一种复合材料构件，其特征在于，所述复合材料构件通过权利要求1-9任一项所述的复合材料构件的成型方法制得。
PCT/CN2018/125133 2018-01-31 2018-12-29 一种复合材料构件的成型方法和复合材料构件 WO2019149010A1 (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201810094645.4 2018-01-31
CN201810094645.4A CN110091521B (zh) 2018-01-31 2018-01-31 一种复合材料构件的成型方法和复合材料构件

Publications (1)

Publication Number Publication Date
WO2019149010A1 true WO2019149010A1 (zh) 2019-08-08

Family

ID=67442580

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2018/125133 WO2019149010A1 (zh) 2018-01-31 2018-12-29 一种复合材料构件的成型方法和复合材料构件

Country Status (2)

Country Link
CN (1) CN110091521B (zh)
WO (1) WO2019149010A1 (zh)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113400527A (zh) * 2021-07-08 2021-09-17 湖南航天环宇通信科技股份有限公司 一种复合材料多向接头的整体模压成型模具及成型工艺
CN114953499A (zh) * 2022-01-28 2022-08-30 航天材料及工艺研究所 一种多结构特征复合材料雪车用模具及雪车制备方法
CN116001321A (zh) * 2022-12-09 2023-04-25 中电科芜湖钻石飞机制造有限公司 复合材料泡沫夹芯件及其制备方法

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112743875B (zh) * 2020-12-29 2022-10-14 东莞泰合复合材料有限公司 一种复合材料工件成型方法和复合材料工件

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04332612A (ja) * 1991-05-09 1992-11-19 Okura Ind Co Ltd 発泡成形体の製造方法
CN103407170A (zh) * 2013-07-26 2013-11-27 北京卫星制造厂 一种星载天线反射面的制备方法

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5487854A (en) * 1994-09-08 1996-01-30 United Technologies Corporation Two-state co-cure method for fabricating a composite article
US5626382A (en) * 1995-04-03 1997-05-06 Lear Corporation Molded plastic panel having integrated, localized soft-touch aesthetic feature
ATE487581T1 (de) * 2004-01-20 2010-11-15 Touchstone Res Lab Ltd Kohlenstoffschaumverbundwerkzeug und verwendungsverfahren dafür
CN102868021B (zh) * 2012-09-27 2015-09-09 中国科学院长春光学精密机械与物理研究所 一种高性能频率选择雷达罩
CN103029307B (zh) * 2012-12-12 2015-04-22 江西洪都航空工业集团有限责任公司 一种复合材料盒型结构主梁的制作方法
CN103192536B (zh) * 2013-03-26 2015-01-14 南京航空航天大学 纤维增强树脂基复合材料的微波高压间歇固化法及模具
CN104290338A (zh) * 2014-08-14 2015-01-21 航天海鹰(镇江)特种材料有限公司 一种高强度软性工装实现加强筋腹板复材制件共固化的方法
CN104494160B (zh) * 2014-11-25 2017-01-25 中联重科股份有限公司 折叠臂架、纤维增强树脂基复合材料臂节及其制造方法
CN105150557B (zh) * 2015-09-15 2017-09-12 沈阳飞机工业（集团）有限公司 一种用于大曲率异形c型框类零件成型的自制辅助工装制造方法
CN105346099B (zh) * 2015-10-29 2018-01-16 西安康本材料有限公司 一种碳纤维复合材料薄壁曲线管件的制备方法
CN105936132A (zh) * 2016-05-11 2016-09-14 铱格斯曼航空科技集团有限公司 一种碳纤维复合材料一体化壳体结构模具的制备方法
CN105984154A (zh) * 2016-06-14 2016-10-05 沈阳飞机工业（集团）有限公司 一种u型梁类复合材料制件的成型方法
CN106799848B (zh) * 2016-12-09 2019-05-24 中国商用飞机有限责任公司 “c”形橡胶芯模成型方法、用于“工”形构件的成型方法和用于“工”形构件的成型装置

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH04332612A (ja) * 1991-05-09 1992-11-19 Okura Ind Co Ltd 発泡成形体の製造方法
CN103407170A (zh) * 2013-07-26 2013-11-27 北京卫星制造厂 一种星载天线反射面的制备方法

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN113400527A (zh) * 2021-07-08 2021-09-17 湖南航天环宇通信科技股份有限公司 一种复合材料多向接头的整体模压成型模具及成型工艺
CN113400527B (zh) * 2021-07-08 2023-04-11 湖南航天环宇通信科技股份有限公司 一种复合材料多向接头的整体模压成型模具及成型工艺
CN114953499A (zh) * 2022-01-28 2022-08-30 航天材料及工艺研究所 一种多结构特征复合材料雪车用模具及雪车制备方法
CN116001321A (zh) * 2022-12-09 2023-04-25 中电科芜湖钻石飞机制造有限公司 复合材料泡沫夹芯件及其制备方法

Also Published As

Publication number Publication date
CN110091521B (zh) 2023-04-07
CN110091521A (zh) 2019-08-06

Similar Documents

Publication Publication Date Title
WO2019149010A1 (zh) 一种复合材料构件的成型方法和复合材料构件
CA2778258C (en) High temperature composite tool
ES2770400T3 (es) Método y aparato para formar estructuras compuestas termoplásticas
CN102765198A (zh) 复合材料真空辅助模压成型系统及成型方法
JP2009542483A (ja) 複合部品の製造方法
JP6320460B2 (ja) 強化繊維と熱可塑性樹脂を含む成形品のプレス成形装置およびプレス成形方法
WO2011043253A1 (ja) 繊維強化プラスチックの製造方法および装置
JP2015536260A5 (zh)
CN109397724B (zh) 一种耐高温复合材料及其高温热膨胀成型方法
JP6578030B2 (ja) 強化繊維と熱可塑性樹脂を含む成形品のプレス成形方法
CN213056086U (zh) 一种无人机复合材料零部件的成型模具
CN111070503A (zh) 3d打印技术辅助碳纤维构件的成型方法及结构、成型模具
CN105711110A (zh) 一种复合材料成型件的模具及模压成型方法
JP6384213B2 (ja) 複合材料の製造方法、複合材料の製造装置
JPH01221228A (ja) 繊維強化複合物品の製造方および装置
JP6750735B2 (ja) 複合材料の成形方法および複合材料の成形装置
CN112829334B (zh) 一种变厚度防热层、变厚度防热层成型模具以及成型方法
WO2018014735A1 (zh) 复合材料制件的阴模成型方法
CN115923183A (zh) 带褶皱-孔隙耦合缺陷试验件的制造方法及装置
WO2020000980A1 (zh) 一种踝足矫形器的一步成型工艺和踝足矫形器
KR101567515B1 (ko) 섬유복합재 구조물 성형장치 및 섬유복합재 구조물 성형방법
TW201527081A (zh) 熱塑性纖維複合材料的成形方法及其成形模具
WO2024143468A1 (ja) 複合材料製部品の成形方法
JPH0243011A (ja) 繊維強化複合部材の製造方法
CN115709583A (zh) 封头组件的成型方法及发动机壳体

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 18904379

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 18904379

Country of ref document: EP

Kind code of ref document: A1