CN111086240A - Vacuum heating device and process for equipment cabin for integrally forming and preparing composite material - Google Patents
Vacuum heating device and process for equipment cabin for integrally forming and preparing composite material Download PDFInfo
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- CN111086240A CN111086240A CN201911335607.4A CN201911335607A CN111086240A CN 111086240 A CN111086240 A CN 111086240A CN 201911335607 A CN201911335607 A CN 201911335607A CN 111086240 A CN111086240 A CN 111086240A
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- vacuum
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- glass fiber
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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
- B29C70/34—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
Abstract
The invention belongs to the technical field of integrated equipment cabins, and particularly relates to a vacuum heating device for an integrated equipment cabin for preparing a composite material and a process thereof. The invention uses the integral forming preparation process, ensures that the cabin body material is integrally formed and solidified, and improves various performances of the equipment cabin. The invention is used for preparing the glass fiber composite material.
Description
Technical Field
The invention belongs to the technical field of integrally formed equipment cabins, and particularly relates to a vacuum heating device and a vacuum heating process for an integrally formed equipment cabin for preparing a composite material.
Background
Composite material light equipment cabins have become a development trend in the industry. Compared with an aluminum skin foaming plate or a honeycomb sandwich plate shelter, the composite material light equipment shelter has a plurality of important advantages: the maintenance cost is low, the service life is long, the environmental pollution is low, and the cost is low; the anti-corrosion capability and the anti-explosion and bulletproof capability are improved; the weight is reduced, the energy utilization efficiency is increased, and the requirement of light weight is met. The composite material light equipment cabin ensures that the carrying platform has stronger power performance and maneuverability, has a farther moving range, expands the combat radius, is favorable for exerting larger combat efficiency and lightens the logistics supply pressure.
Hot press forming is an important process for producing high-performance resin-based composite materials. The existing preparation and forming process generally needs higher pressure and higher heating temperature, and the common compression molding can only prepare regular plate-type pieces and cannot prepare integrally-formed box-type equipment cabins; the size of the equipment cabin is about 4000mm 1000mm 800mm, the size is large, a large autoclave is needed for molding, the preparation of the equipment cabin is restricted, and the strength of the resin-based composite material prepared by normal-temperature curing can not meet the use requirements in the fields of aerospace and military industry. Patent document No. CN104827613A discloses a method for spontaneous heating and rapid curing molding by directly acting on a metal mold through a medium frequency electromagnetic induction coil. The method has the advantages of high heating speed, good uniformity of the temperature field, accurate control and small temperature overshoot. However, the method can be carried out only by self-heating of the metal mold, the non-metal auxiliary material for molding the composite material is not heated, and once the heating of the medium-frequency electromagnetic induction coil is stopped, the molding mold is stopped. This results in the sandwich composite material not being able to be heated on the side remote from the mould, resulting in incomplete curing and difficulty in shaping. The patent document No. CN105729827A discloses a mechanical pressing method for micro-blog curing composite material, which is a technology for converting microwave energy into heat energy by penetrating low-frequency electromagnetic waves through the material to uniformly heat the inside and outside of the material. However, the sandwich composite material is an anisotropic material and comprises materials with different components, so that the temperature uniformity cannot be ensured, and the high-performance composite material is difficult to prepare.
Disclosure of Invention
Aiming at the technical problems of overlarge cabin body type and uneven heating of the equipment, the invention provides the vacuum heating device and the process for preparing the composite material equipment cabin through integral forming, which have the advantages of small size, even heating and high efficiency.
In order to solve the technical problems, the invention adopts the technical scheme that:
a vacuum heating device of an equipment cabin for integrally forming and preparing composite materials comprises a metal mould, a vacuum system and a heating device, the metal mold is composed of five plane mold plates, the plane mold plates are riveted and fixed through screws, the metal mould is internally paved with a composite material and an isolation material, the isolation material is paved on the upper surface of the composite material, the vacuum system comprises a vacuum bag, a vacuum pipeline and a vacuum pump, the vacuum bag is coated outside the composite material and the isolation material, the vacuum bag is connected with a vacuum pump through a vacuum pipeline, the heating device comprises an aluminum casting module, a heating element, a thermocouple and a control instrument, the heating element and the thermocouple are laid in the cast aluminum module, the heating element and the thermocouple are both connected to a control instrument, the two heating devices are respectively fixed on the lower surface of the metal mold and the upper surface of the vacuum bag.
The isolation material adopts an isolation film, and the upper surface of the isolation film is paved with an air felt.
The composite material comprises glass fiber prepreg, epoxy structure adhesive films, a sandwich material and embedded parts, wherein the glass fiber prepreg is laid on the demolding cloth, the epoxy structure adhesive films are laid on the upper surface and the lower surface of the sandwich material, the glass fiber prepreg is provided with at least two layers, the sandwich material is laid between the glass fiber prepreg through the epoxy structure adhesive films, and the embedded parts are arranged in the middle of the sandwich material.
The release cloth is laid on the inner surface of the vacuum bag.
The epoxy structural adhesive film is of an elastomer modified epoxy resin type.
The glass fiber prepreg is made of plain woven glass fiber epoxy cloth.
The demolding cloth is made of glass fiber cloth coated with polytetrafluoroethylene, and silica gel is arranged on one side of the demolding cloth.
A vacuum heating process for an equipment cabin for integrally forming and preparing a composite material comprises the following steps:
s1, laying the cut glass fiber prepreg according to the structure of the mould, laying 4 layers of glass fiber prepreg, laying one layer by one layer, staggering the lap joints, and exhausting air wrapped between the laid layers in the laying process;
s2, laying 1 layer of epoxy structure adhesive film on the glass fiber prepreg, laying 27mm sandwich material, placing embedded parts inside, fixing through hole positions, continuously laying 1 layer of epoxy structure adhesive film on the surface, and then laying 6 layers of glass fiber prepreg;
s3, coating the composite material by using an isolating film and an air-permeable felt, and completely coating the composite material in the molding die;
s4, completely coating the isolation film and the breathable felt by using a vacuum bag, wherein one end of a vacuum pipeline penetrates through the vacuum bag to be in contact with the breathable material, and the other end of the vacuum pipeline is vacuumized by a vacuum pump to ensure that the vacuum degree reaches below 1 KPa;
s5, respectively fixing the customized heating device on the lower surface of the metal mold and the upper surface of the vacuum bag, completely covering the surfaces, switching on a power supply, starting heating and curing, setting the temperature of the heating device to 90 ℃, the heating rate to be 3 ℃/min, keeping the temperature for 1h, enabling the epoxy structure adhesive film to start to fully flow, mutually infiltrating and uniformly distributing the composite materials, then setting the temperature of the heating device to be 130 ℃, the heating rate to be 3 ℃/min, keeping the temperature for 3h, and completely curing the epoxy structure adhesive film;
s6, setting the temperature of the heating device to 90 ℃, preserving the heat for 1h, then stopping heating and vacuumizing, naturally cooling the equipment cabin to room temperature, and demoulding.
Compared with the prior art, the invention has the following beneficial effects:
the invention overcomes the problem that the prior art is difficult to solve the heating curing molding problem in the process of preparing the integral molding equipment cabin, creatively uses the flexible and combinable heating module to directly heat the metal mold and the composite material, and has simple operation.
The heating module used in the invention belongs to a decomposable and customized cast aluminum heating plate, can be adjusted according to the use requirement, and has the heating power of 3W/cm2Less consumption and energy saving. The heating rate is 3-5 ℃/min, and the working efficiency is greatly improved.
The invention overcomes the problems of poor overall mechanical strength, poor electrical continuity and poor electromagnetic shielding performance in the process of preparing the equipment cabin in modules and then splicing the equipment cabin into a whole in the prior art, creatively uses an integral forming preparation process, ensures that cabin body materials are integrally formed and cured, and improves various performances of the equipment cabin.
Drawings
FIG. 1 is a schematic external view of the present invention;
FIG. 2 is a schematic view of the heating apparatus according to the present invention;
FIG. 3 is a schematic view of the internal structure of the metal mold of the present invention;
FIG. 4 is a schematic diagram of the vacuum system of the present invention;
wherein: the manufacturing method comprises the following steps of 1, 2, a vacuum system, 3, a heating device, 11, an isolating membrane, 12, an air-permeable felt, 13, a glass fiber prepreg, 14, an epoxy structural adhesive film, 15, a sandwich material, 16, an embedded part, 17, demolding cloth, 21, a vacuum bag, 22, a vacuum pipeline, 23, a vacuum pump, 31, an aluminum casting module, 32, a heating element, 33, a thermocouple and 34, wherein the metal mold is a metal mold, the vacuum system is a vacuum system, the heating device is a heating device, the isolating membrane is an isolating.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are only a part of the embodiments of the present invention, and not all of the embodiments. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
The utility model provides an integrated into one piece prepares combined material equipment cabin vacuum heating device, as shown in figure 1, including metal mold 1, vacuum system 2, heating device 3, metal mold 1 comprises five plane mould boards, rivet through the screw between the plane mould board and fix, combined material, barrier material have been laid in metal mold 1, barrier material lays the upper surface at combined material, as shown in figure 2, vacuum system 2 includes vacuum bag 21, vacuum pipeline 22, vacuum pump 23, vacuum bag 21 cladding is in combined material and barrier material's outside, vacuum bag 21 is connected with vacuum pump 23 through vacuum pipeline 22, pump 21 vacuums to vacuum bag through vacuum pump 23, provide the negative pressure for the shaping process. As shown in fig. 3, the heating device 3 includes a cast aluminum module 31, a heating element 32, a thermocouple 33, and a control instrument 34, wherein the heating element 32 and the thermocouple 33 are laid inside the cast aluminum module 31, the heating element 32 and the thermocouple 33 are both connected to the control instrument 34, and the thermocouple 33 can directly measure the temperature and transmit the signal to a display instrument of the control instrument 34, so as to facilitate the temperature control of the heating element 32. The heating devices 3 are two in number, and the two heating devices 3 are respectively fixed on the lower surface of the metal mold 1 and the upper surface of the vacuum bag 21.
Further, preferably, the isolation material is an isolation film 11, and an air-permeable felt 12 is laid on the upper surface of the isolation film 11.
Further, as shown in fig. 4, the composite material includes a glass fiber prepreg 13, an epoxy structure adhesive film 14, a sandwich material 15, and an embedded part 16, the glass fiber prepreg 13 is laid on a release fabric 17, the epoxy structure adhesive films 14 are laid on both the upper surface and the lower surface of the sandwich material 15, the glass fiber prepreg 13 has at least two layers, the sandwich material 15 is laid between the glass fiber prepregs 13 through the epoxy structure adhesive films 14, and the embedded part 16 is disposed in the middle of the sandwich material 15.
Further, a release cloth 17 is laid on the inner surface of the vacuum bag 21.
Further, it is preferable that the epoxy structural adhesive film 14 is of an elastomer-modified epoxy type. The adhesive is used for increasing the adhesive strength between polyurethane foam and glass fiber, and the peel strength can reach more than 60N/cm.
Further, preferably, the glass fiber prepreg 13 is plain woven glass fiber epoxy cloth.
Further, preferably, the release cloth 17 is made of glass fiber cloth coated with polytetrafluoroethylene, and one side of the release cloth 17 is provided with silica gel, so that the release cloth is convenient to adhere to the surface of the metal mold 1.
A vacuum heating process for an equipment cabin for integrally forming and preparing a composite material comprises the following steps:
s1, laying the cut glass fiber prepreg according to the structure of the mould, laying 4 layers of glass fiber prepreg, laying one layer by one layer, staggering the lap joints, and exhausting air wrapped between the laid layers in the laying process;
s2, laying 1 layer of epoxy structure adhesive film on the glass fiber prepreg, laying 27mm sandwich material, placing embedded parts inside, fixing through hole positions, continuously laying 1 layer of epoxy structure adhesive film on the surface, and then laying 6 layers of glass fiber prepreg;
s3, coating the composite material by using an isolating film and an air-permeable felt, and completely coating the composite material in the molding die;
s4, completely coating the isolation film and the breathable felt by using a vacuum bag, wherein one end of a vacuum pipeline penetrates through the vacuum bag to be in contact with the breathable material, and the other end of the vacuum pipeline is vacuumized by a vacuum pump to ensure that the vacuum degree reaches below 1 KPa;
s5, respectively fixing the customized heating device on the lower surface of the metal mold and the upper surface of the vacuum bag, completely covering the surfaces, switching on a power supply, starting heating and curing, setting the temperature of the heating device to 90 ℃, the heating rate to be 3 ℃/min, keeping the temperature for 1h, enabling the epoxy structure adhesive film to start to fully flow, mutually infiltrating and uniformly distributing the composite materials, then setting the temperature of the heating device to be 130 ℃, the heating rate to be 3 ℃/min, keeping the temperature for 3h, and completely curing the epoxy structure adhesive film;
s6, setting the temperature of the heating device to 90 ℃, preserving the heat for 1h, then stopping heating and vacuumizing, naturally cooling the equipment cabin to room temperature, and demoulding.
Although only the preferred embodiments of the present invention have been described in detail, the present invention is not limited to the above embodiments, and various changes can be made without departing from the spirit of the present invention within the knowledge of those skilled in the art, and all changes are encompassed in the scope of the present invention.
Claims (8)
1. The utility model provides an integrated into one piece preparation combined material equipment cabin vacuum heating device which characterized in that: including metal mold (1), vacuum system (2), heating device (3), metal mold (1) constitutes through five plane mould boards, rivet fixedly through the screw between the plane mould board, combined material, barrier material have been laid in metal mold (1), barrier material lays at combined material's upper surface, vacuum system (2) includes vacuum bag (21), vacuum pipeline (22), vacuum pump (23), vacuum bag (21) cladding is in combined material and barrier material's outside, vacuum bag (21) is connected with vacuum pump (23) through vacuum pipeline (22), heating device (3) are including cast aluminium module (31), heating element (32), thermocouple (33), control instrument (34), heating element (32), thermocouple (33) are laid in the inside of cast aluminium module (31), the heating elements (32) and the thermocouples (33) are connected to a control instrument (34), the number of the heating devices (3) is two, and the two heating devices (3) are respectively fixed on the lower surface of the metal mold (1) and the upper surface of the vacuum bag (21).
2. The vacuum heating device for the equipment cabin integrally formed and prepared from composite materials, according to claim 1, is characterized in that: the isolation material adopts an isolation film (11), and an air-permeable felt (12) is laid on the upper surface of the isolation film (11).
3. The vacuum heating device for the equipment cabin integrally formed and prepared from composite materials, according to claim 1, is characterized in that: the composite material comprises glass fiber prepregs (13), epoxy structure adhesive films (14), sandwich materials (15) and embedded parts (16), wherein the glass fiber prepregs (13) are laid on demolding cloth (17), the epoxy structure adhesive films (14) are laid on the upper surface and the lower surface of the sandwich materials (15), the glass fiber prepregs (13) are at least two layers, the sandwich materials (15) are laid between the glass fiber prepregs (13) through the epoxy structure adhesive films (14), and the embedded parts (16) are arranged in the middle of the sandwich materials (15).
4. The vacuum heating device for the equipment cabin integrally formed and prepared from composite materials, according to claim 1 or 3, is characterized in that: the release cloth (17) is laid on the inner surface of the vacuum bag (21).
5. The vacuum heating device for the equipment cabin integrally formed and prepared from composite materials, according to claim 3, is characterized in that: the epoxy structural adhesive film (14) is of an elastomer modified epoxy resin type.
6. The vacuum heating device for the equipment cabin integrally formed and prepared from composite materials, according to claim 3, is characterized in that: the glass fiber prepreg (13) is made of plain woven glass fiber epoxy cloth.
7. The vacuum heating device for the equipment cabin integrally formed and prepared from composite materials, according to claim 3, is characterized in that: the demolding cloth (17) is made of glass fiber cloth coated with polytetrafluoroethylene, and silica gel is arranged on one side of the demolding cloth (17).
8. The vacuum heating process for the equipment cabin for integrally forming and preparing the composite material is characterized by comprising the following steps of: comprises the following steps:
s1, laying the cut glass fiber prepreg according to the structure of the mould, laying 4 layers of glass fiber prepreg, laying one layer by one layer, staggering the lap joints, and exhausting air wrapped between the laid layers in the laying process;
s2, laying 1 layer of epoxy structure adhesive film on the glass fiber prepreg, laying 27mm sandwich material, placing embedded parts inside, fixing through hole positions, continuously laying 1 layer of epoxy structure adhesive film on the surface, and then laying 6 layers of glass fiber prepreg;
s3, coating the composite material by using an isolating film and an air-permeable felt, and completely coating the composite material in the molding die;
s4, completely coating the isolation film and the breathable felt by using a vacuum bag, wherein one end of a vacuum pipeline penetrates through the vacuum bag to be in contact with the breathable material, and the other end of the vacuum pipeline is vacuumized by a vacuum pump to ensure that the vacuum degree reaches below 1 KPa;
s5, respectively fixing the customized heating device on the lower surface of the metal mold and the upper surface of the vacuum bag, completely covering the surfaces, switching on a power supply, starting heating and curing, setting the temperature of the heating device to 90 ℃, the heating rate to be 3 ℃/min, keeping the temperature for 1h, enabling the epoxy structure adhesive film to start to fully flow, mutually infiltrating and uniformly distributing the composite materials, then setting the temperature of the heating device to be 130 ℃, the heating rate to be 3 ℃/min, keeping the temperature for 3h, and completely curing the epoxy structure adhesive film;
s6, setting the temperature of the heating device to 90 ℃, preserving the heat for 1h, then stopping heating and vacuumizing, naturally cooling the equipment cabin to room temperature, and demoulding.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111890708A (en) * | 2020-07-16 | 2020-11-06 | 张家港保税区百瑞坤航空材料科技有限公司 | Composite material thermal diaphragm method preform forming process |
| CN112590250A (en) * | 2020-12-12 | 2021-04-02 | 江西洪都航空工业集团有限责任公司 | Method for manufacturing low-curvature parts in batches by adopting automatic tape laying technology |
| CN112607048A (en) * | 2020-11-16 | 2021-04-06 | 南京航空航天大学 | Temperature-adjustable solar composite material repairing device |
| CN112829336A (en) * | 2020-12-30 | 2021-05-25 | 广联航空工业股份有限公司 | Manufacturing method of Kevlar electronic product protective shell with shockproof function |
| CN114683575A (en) * | 2022-03-18 | 2022-07-01 | 南京聚隆复合材料技术有限公司 | Preparation method of carbon fiber composite material rail obstacle clearing device |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6017484A (en) * | 1997-01-21 | 2000-01-25 | Harold P. Hale | Method for manufacture of minimum porosity, wrinkle free composite parts |
| CN102765198A (en) * | 2012-07-13 | 2012-11-07 | 中国人民解放军国防科学技术大学 | Vacuum assisted molding system of composite and molding method of composite |
| CN102825797A (en) * | 2012-08-30 | 2012-12-19 | 内蒙古金岗重工有限公司 | Large-scale composite wind blade forming process |
| CN102869487A (en) * | 2009-11-13 | 2013-01-09 | F·波尔希名誉工学博士公司 | Method for producing component from fibre-reinforced material |
| CN108673909A (en) * | 2018-04-28 | 2018-10-19 | 武汉理工大学 | A kind of carbon fiber product molding/decoration integrated technique |
| CN110126303A (en) * | 2019-05-31 | 2019-08-16 | 连云港中复连众复合材料集团有限公司 | A method of fan blade of wind generating set girder is prepared with the wide pultruded panels of whole picture |
-
2019
- 2019-12-23 CN CN201911335607.4A patent/CN111086240B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6017484A (en) * | 1997-01-21 | 2000-01-25 | Harold P. Hale | Method for manufacture of minimum porosity, wrinkle free composite parts |
| CN102869487A (en) * | 2009-11-13 | 2013-01-09 | F·波尔希名誉工学博士公司 | Method for producing component from fibre-reinforced material |
| CN102765198A (en) * | 2012-07-13 | 2012-11-07 | 中国人民解放军国防科学技术大学 | Vacuum assisted molding system of composite and molding method of composite |
| CN102825797A (en) * | 2012-08-30 | 2012-12-19 | 内蒙古金岗重工有限公司 | Large-scale composite wind blade forming process |
| CN108673909A (en) * | 2018-04-28 | 2018-10-19 | 武汉理工大学 | A kind of carbon fiber product molding/decoration integrated technique |
| CN110126303A (en) * | 2019-05-31 | 2019-08-16 | 连云港中复连众复合材料集团有限公司 | A method of fan blade of wind generating set girder is prepared with the wide pultruded panels of whole picture |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111890708A (en) * | 2020-07-16 | 2020-11-06 | 张家港保税区百瑞坤航空材料科技有限公司 | Composite material thermal diaphragm method preform forming process |
| CN112607048A (en) * | 2020-11-16 | 2021-04-06 | 南京航空航天大学 | Temperature-adjustable solar composite material repairing device |
| CN112607048B (en) * | 2020-11-16 | 2022-04-22 | 南京航空航天大学 | Temperature-adjustable solar composite material repairing device |
| CN112590250A (en) * | 2020-12-12 | 2021-04-02 | 江西洪都航空工业集团有限责任公司 | Method for manufacturing low-curvature parts in batches by adopting automatic tape laying technology |
| CN112829336A (en) * | 2020-12-30 | 2021-05-25 | 广联航空工业股份有限公司 | Manufacturing method of Kevlar electronic product protective shell with shockproof function |
| CN114683575A (en) * | 2022-03-18 | 2022-07-01 | 南京聚隆复合材料技术有限公司 | Preparation method of carbon fiber composite material rail obstacle clearing device |
| CN114683575B (en) * | 2022-03-18 | 2024-02-27 | 南京聚隆复合材料技术有限公司 | Preparation method of carbon fiber composite material track obstacle clearing device |
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