CN109397782B - Honeycomb sandwich structure plate for satellite and forming process thereof - Google Patents
Honeycomb sandwich structure plate for satellite and forming process thereof Download PDFInfo
- Publication number
- CN109397782B CN109397782B CN201811520187.2A CN201811520187A CN109397782B CN 109397782 B CN109397782 B CN 109397782B CN 201811520187 A CN201811520187 A CN 201811520187A CN 109397782 B CN109397782 B CN 109397782B
- Authority
- CN
- China
- Prior art keywords
- honeycomb
- photoinitiator
- satellite
- panel
- modified
- Prior art date
- Legal status (The legal status 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 status listed.)
- Active
Links
- 238000000034 method Methods 0.000 title claims abstract description 18
- 229920005989 resin Polymers 0.000 claims abstract description 29
- 239000011347 resin Substances 0.000 claims abstract description 29
- 239000002313 adhesive film Substances 0.000 claims abstract description 26
- 229920000049 Carbon (fiber) Polymers 0.000 claims abstract description 21
- 239000004917 carbon fiber Substances 0.000 claims abstract description 21
- 239000000853 adhesive Substances 0.000 claims abstract description 18
- 230000001070 adhesive effect Effects 0.000 claims abstract description 18
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims abstract description 17
- 239000002131 composite material Substances 0.000 claims abstract description 11
- 239000003822 epoxy resin Substances 0.000 claims abstract description 9
- 229920000647 polyepoxide Polymers 0.000 claims abstract description 9
- 229910000838 Al alloy Inorganic materials 0.000 claims abstract description 8
- 238000004519 manufacturing process Methods 0.000 claims abstract description 7
- 238000000465 moulding Methods 0.000 claims abstract description 5
- 125000005520 diaryliodonium group Chemical group 0.000 claims description 9
- 238000001227 electron beam curing Methods 0.000 claims description 9
- 229910052782 aluminium Inorganic materials 0.000 claims description 7
- XAGFODPZIPBFFR-UHFFFAOYSA-N aluminium Chemical compound [Al] XAGFODPZIPBFFR-UHFFFAOYSA-N 0.000 claims description 7
- 238000001723 curing Methods 0.000 claims description 7
- 238000007789 sealing Methods 0.000 claims description 7
- 125000005409 triarylsulfonium group Chemical group 0.000 claims description 7
- 239000004643 cyanate ester Substances 0.000 claims description 6
- 239000000956 alloy Substances 0.000 claims description 5
- 238000007664 blowing Methods 0.000 claims description 4
- 238000005520 cutting process Methods 0.000 claims description 4
- 229910052751 metal Inorganic materials 0.000 claims description 4
- 239000002184 metal Substances 0.000 claims description 4
- 230000002093 peripheral effect Effects 0.000 claims description 4
- 229910018134 Al-Mg Inorganic materials 0.000 claims description 3
- 229910018467 Al—Mg Inorganic materials 0.000 claims description 3
- 239000002390 adhesive tape Substances 0.000 claims description 3
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 abstract 1
- 238000010894 electron beam technology Methods 0.000 abstract 1
- 230000007547 defect Effects 0.000 description 4
- 238000005516 engineering process Methods 0.000 description 3
- 239000000463 material Substances 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 229920001187 thermosetting polymer Polymers 0.000 description 2
- 239000011157 advanced composite material Substances 0.000 description 1
- 239000004411 aluminium Substances 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005265 energy consumption Methods 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000003287 optical effect Effects 0.000 description 1
- 239000000758 substrate Substances 0.000 description 1
Images
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B7/00—Layered products characterised by the relation between layers; Layered products characterised by the relative orientation of features between layers, or by the relative values of a measurable parameter between layers, i.e. products comprising layers having different physical, chemical or physicochemical properties; Layered products characterised by the interconnection of layers
- B32B7/04—Interconnection of layers
- B32B7/12—Interconnection of layers using interposed adhesives or interposed materials with bonding properties
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/04—Layered products comprising a layer of metal comprising metal as the main or only constituent of a layer, which is next to another layer of the same or of a different material
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B15/00—Layered products comprising a layer of metal
- B32B15/20—Layered products comprising a layer of metal comprising aluminium or copper
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B3/00—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form
- B32B3/10—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material
- B32B3/12—Layered products comprising a layer with external or internal discontinuities or unevennesses, or a layer of non-planar shape; Layered products comprising a layer having particular features of form characterised by a discontinuous layer, i.e. formed of separate pieces of material characterised by a layer of regularly- arranged cells, e.g. a honeycomb structure
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/10—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure
- B32B37/1018—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by the pressing technique, e.g. using action of vacuum or fluid pressure using only vacuum
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B32—LAYERED PRODUCTS
- B32B—LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM
- B32B37/00—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding
- B32B37/12—Methods or apparatus for laminating, e.g. by curing or by ultrasonic bonding characterised by using adhesives
-
- C—CHEMISTRY; METALLURGY
- C08—ORGANIC MACROMOLECULAR COMPOUNDS; THEIR PREPARATION OR CHEMICAL WORKING-UP; COMPOSITIONS BASED THEREON
- C08K—Use of inorganic or non-macromolecular organic substances as compounding ingredients
- C08K7/00—Use of ingredients characterised by shape
- C08K7/02—Fibres or whiskers
- C08K7/04—Fibres or whiskers inorganic
- C08K7/06—Elements
Landscapes
- Chemical & Material Sciences (AREA)
- Health & Medical Sciences (AREA)
- Chemical Kinetics & Catalysis (AREA)
- Medicinal Chemistry (AREA)
- Polymers & Plastics (AREA)
- Organic Chemistry (AREA)
- Physics & Mathematics (AREA)
- Fluid Mechanics (AREA)
- Laminated Bodies (AREA)
Abstract
The invention provides a honeycomb sandwich structure plate for a satellite and a forming process thereof, wherein the honeycomb sandwich structure plate for the satellite is composed of a carbon fiber composite material panel (1), a honeycomb core (2) and an adhesive (3). The carbon fiber composite material panel (1) is composed of carbon fiber filaments and resin; the carbon fibers may be high strength T300, T700, T800, T1000 and high modulus M35, M40, M55J, M60, etc.; the resin is epoxy resin or cyanate resin modified by photoinitiator. The honeycomb core (2) is a 5A02 aluminum alloy regular hexagon perforated durable honeycomb. The adhesive (3) is an adhesive film modified by a photoinitiator, and the thickness specification of the adhesive film is 0.1mm, 0.15mm, 0.25mm and 0.3 mm. The molding process comprises the following steps: laying a panel, pre-compacting, assembling a honeycomb plate and curing by an electron beam. The honeycomb sandwich structure plate prepared by the invention has the advantages of high precision, small residual stress, high dimensional stability, high curing speed, short molding period, low production cost and the like.
Description
Technical Field
The invention relates to the field of novel material application, in particular to a honeycomb sandwich structure plate for a satellite and a forming process thereof.
Background
The new generation of satellite load has the characteristics of high precision and high stability, and the satellite structure platform is required to have the characteristics of light weight, high precision, high stability and long service life. With the development of aerospace technology, carbon fiber composite materials, honeycomb sandwich structures and the like are increasingly widely applied to satellite structures. Foreign countries, the composite material structural member accounts for more than 80% of the whole star structural member. The application of advanced composite materials in satellites in China is more and more extensive, various new materials and new processes are rapidly developed, and the weight of a composite material component in the whole satellite structure is about 70%, so that the weight ratio of the satellite structure is greatly reduced.
The honeycomb sandwich structure plate has the characteristics of light weight, high rigidity, high strength and the like, and is widely applied to satellite structures such as a satellite bearing cylinder, a satellite load mounting plate, a satellite shell, an antenna reflector, a solar cell array substrate and the like. With the development of new technology, the requirement for lightweight of the satellite is more and more urgent, so that the application of the honeycomb sandwich plate in the field of the satellite is more and more emphasized. Meanwhile, as the requirements on the precision and stability of satellite loads, particularly optical loads, are higher and higher, the requirements on the precision and stability of honeycomb sandwich structure plates for installation are higher and higher. The traditional honeycomb sandwich plate formed by means of thermosetting through a curing furnace has the defects of large deformation and poor dimensional stability, and the forming requirements of the honeycomb sandwich plate with high precision and high stability which are increasingly improved are difficult to meet.
In order to overcome the defects of the prior art, the invention aims to provide a honeycomb sandwich structure plate for a satellite and a forming process thereof, so as to solve the technical problems of large deformation, poor dimensional stability and the like of the honeycomb plate in the prior art.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a honeycomb sandwich structure plate for a satellite and a forming process thereof.
The honeycomb sandwich structure plate for the satellite comprises a panel, a honeycomb core and an adhesive; the face sheet is attached to the honeycomb core by an adhesive.
Preferably, the panel has a thickness ranging from 0.1mm to 0.6mm and is prepared by using a carbon fiber composite material, wherein the carbon fiber composite material comprises a resin and carbon fibers, and the content of the resin ranges from 20wt% to 40 wt%.
Preferably, the carbon fiber comprises any one or any combination of high-strength T300, high-strength T700, high-strength T800, high-strength T1000, high model M35, high model M40, high model M55J and high model M60; the resin comprises an epoxy resin modified with a first photoinitiator and/or a cyanate ester resin modified with a first photoinitiator.
Preferably, the first photoinitiator is a diaryliodonium salt and/or a triarylsulfonium salt; the dosage of the first photoinitiator in the epoxy resin modified by the first photoinitiator and/or the cyanate ester resin modified by the first photoinitiator accounts for 0.5 to 3 weight percent of the total weight of the resin.
Preferably, the honeycomb core is a regular hexagonal porous honeycomb and is made of an aluminum alloy material, and the aluminum alloy material comprises Al-Mg series antirust aluminum 5A 02; the wall thickness range of the honeycomb core is 0.03 mm-0.06 mm, and the side length range of the core grid is 3 mm-6 mm.
Preferably, the adhesive comprises a structural adhesive film modified by a second photoinitiator, wherein the structural adhesive film comprises any one or any combination of J-47C, J-78B and Redox 312.
Preferably, the second photoinitiator comprises a diaryliodonium salt and/or a triarylsulfonium salt; the structural adhesive film modified by the second photoinitiator has the dosage of 1-5 wt% of the total weight of the structural adhesive film.
According to the invention, the forming process of the honeycomb sandwich structure plate for the satellite is used for manufacturing the honeycomb sandwich structure plate for the satellite, and comprises the following steps:
s1, preparing a prepreg by adopting resin modified by a photoinitiator and carbon fiber, wherein the resin content is 20-40 wt%, and the thickness is 0.1-0.3 mm;
s2, cutting the prepreg according to the design size, then paving a panel (1) on the surface of the metal mold according to the paving requirement, and sticking a layer of photoinitiator modified adhesive (3) or a glue film on the uppermost layer;
s3, vacuumizing the laid prepreg until the relative pressure of the reference standard atmospheric pressure is not more than-0.097 MPa, and vacuumizing for not less than 4 h;
s4, sequentially placing a lower panel prepreg, a honeycomb core and an upper panel prepreg on the forming die, and pre-bonding the prepregs and the honeycomb core by hot air blowing.
S5, adhering 1-5 layers of photoinitiator modified adhesive films around the honeycomb plate.
And S6, performing electron beam curing on the upper surface, the lower surface and the peripheral edge sealing positions of the honeycomb plate by adopting electron beam curing equipment, wherein the irradiation dose is 50 keV-300 keV.
Preferably, the forming process of the honeycomb sandwich structure plate for the satellite further comprises the following steps:
and S7, after the curing is finished, sealing edges of the honeycomb plate by 1170 aluminum-based adhesive tapes.
Compared with the prior art, the invention has the following beneficial effects:
1. the honeycomb sandwich structure plate for the satellite is low in cost, simple in structure, free from the size limitation of a curing furnace, capable of producing large-size honeycomb plates and high in production efficiency;
2. the forming process of the honeycomb sandwich structure plate for the satellite, provided by the invention, has the advantages of low residual stress in the forming process, high product precision and high stability;
3. the honeycomb sandwich structure plate for the satellite and the forming process thereof can effectively overcome the defect of high energy consumption of the existing thermosetting technology.
Drawings
Other features, objects and advantages of the invention will become more apparent upon reading of the detailed description of non-limiting embodiments with reference to the following drawings:
fig. 1 is a schematic view of a honeycomb sandwich structure plate for a satellite according to the present invention;
fig. 2 is a schematic size diagram of a preferred embodiment of the honeycomb sandwich structure plate for a satellite provided by the invention.
The figures show that:
Honeycomb core 2
Detailed Description
The present invention will be described in detail with reference to specific examples. The following examples will assist those skilled in the art in further understanding the invention, but are not intended to limit the invention in any way. It should be noted that it would be obvious to those skilled in the art that various changes and modifications can be made without departing from the spirit of the invention. All falling within the scope of the present invention.
The honeycomb sandwich structure plate for the satellite comprises a panel 1, a honeycomb core 2 and an adhesive 3; the face sheet 1 is connected to the honeycomb core 2 by means of an adhesive 3.
Preferably, the panel 1 has a thickness ranging from 0.1mm to 0.6mm, and is manufactured using a carbon fiber composite material, wherein the components of the carbon fiber composite material include a resin and carbon fibers, and the content of the resin ranges from 20wt% to 40 wt%. The carbon fiber comprises any one or combination of more of a high-strength T300, a high-strength T700, a high-strength T800, a high-strength T1000, a high model M35, a high model M40, a high model M55J and a high model M60; the resin comprises an epoxy resin modified with a first photoinitiator and/or a cyanate ester resin modified with a first photoinitiator. The first photoinitiator is diaryl iodonium salt and/or triaryl sulfonium salt; the dosage of the first photoinitiator in the epoxy resin modified by the first photoinitiator and/or the cyanate ester resin modified by the first photoinitiator accounts for 0.5 to 3 weight percent of the total weight of the resin. The honeycomb core 2 is a regular hexagonal porous honeycomb and is made of an aluminum alloy material, and the aluminum alloy material comprises Al-Mg series antirust aluminum 5A 02; the wall thickness range of the honeycomb core 2 is 0.03 mm-0.06 mm, and the side length range of the core grid is 3 mm-6 mm. The adhesive 3 comprises a structural adhesive film modified by a second photoinitiator, wherein the structural adhesive film comprises any one or any combination of J-47C, J-78B and Redox 312. The second photoinitiator comprises a diaryliodonium salt and/or a triarylsulfonium salt; the structural adhesive film modified by the second photoinitiator has the dosage of 1-5 wt% of the total weight of the structural adhesive film.
According to the invention, the forming process of the honeycomb sandwich structure plate for the satellite is used for manufacturing the honeycomb sandwich structure plate for the satellite, and comprises the following steps:
s1, preparing a prepreg by adopting resin modified by a photoinitiator and carbon fiber, wherein the resin content is 20-40 wt%, and the thickness is 0.1-0.3 mm;
s2, cutting the prepreg according to the design size, then paving the panel 1 on the surface of the metal mold according to the paving requirement, and sticking a layer of photoinitiator modified adhesive 3 or an adhesive film on the uppermost layer;
s3, vacuumizing the laid prepreg until the relative pressure of the reference standard atmospheric pressure is not more than-0.097 MPa, and vacuumizing for not less than 4 h;
s4, sequentially placing a lower panel prepreg, the honeycomb core 2 and an upper panel prepreg on the forming die, and pre-attaching the prepregs and the honeycomb core 2 by hot air blowing.
S5, adhering 1-5 layers of photoinitiator modified adhesive films around the honeycomb plate.
And S6, performing electron beam curing on the upper surface, the lower surface and the peripheral edge sealing positions of the honeycomb plate by adopting electron beam curing equipment, wherein the irradiation dose is 50 keV-300 keV.
Specifically, the forming process of the honeycomb sandwich structure plate for the satellite provided by the invention further comprises the following steps:
and S7, after the curing is finished, sealing edges of the honeycomb plate by 1170 aluminum-based adhesive tapes.
More specifically, in the honeycomb sandwich structure plate for the satellite, the honeycomb core 2 is a regular hexagon perforated durable honeycomb made of 5A02(LF2Y) aluminum alloy, the wall thickness can be 0.03mm, 0.04mm, 0.05mm and 0.06mm, and the side length of the core grid can be 3mm, 4mm, 5mm and 6 mm. The adhesive 3 is a film modified by a photoinitiator, and has the thickness specifications of 0.1mm, 0.15mm, 0.25mm and 0.3 mm. The adhesive film can be J-47C, J-78B, Redux312 adhesive film modified by a photoinitiator. The adhesive 3 or the adhesive film is modified by a photoinitiator, wherein the photoinitiator is diaryl iodonium salt or triaryl sulfonium salt, and the dosage of the photoinitiator is 1 to 5 weight percent of the weight of the adhesive 3.
Further, in a preferred example of the honeycomb sandwich structure plate for a satellite provided by the invention, the honeycomb sandwich plate is as shown in fig. 2. The external dimension is 1000mm multiplied by 2000mm multiplied by 30mm, and the whole plate flatness is 0.5 mm. The inner panel and the outer panel are 0.3mm thick, M55J/photoinitiator modified Ag80 epoxy resin; the adhesive 3 is a J78B adhesive film modified by a photoinitiator; the honeycomb core 2 was a 6mm × 0.03mm regular hexagonal perforated durable honeycomb of 5a02(LF2Y) aluminum alloy. Wherein, the photoinitiator is Ag80 epoxy resin modified by a photoinitiator, the photoinitiator is diaryl iodonium salt, and the addition amount is 2 wt%; the photoinitiator modified J78B adhesive film is prepared from diaryl iodonium salt in an amount of 2.5 wt%.
The manufacturing process comprises the following steps:
preparing a prepreg with the thickness of 0.1mm and the resin content of 33% by adopting resin modified by a photoinitiator and carbon fiber; cutting the prepreg according to the design size, then paving a panel 1 on the surface of a metal mold according to the paving requirement, and sticking a layer of photoinitiator modified J78B adhesive film on the uppermost layer; vacuumizing the laid prepreg for 6 hours, wherein the vacuum degree is less than or equal to-0.097 MPa; sequentially placing a lower panel prepreg, the honeycomb core 2 and an upper panel prepreg on a forming die, and pre-attaching the prepregs and the honeycomb core 2 by hot air blowing; pasting 1-5 layers of photoinitiator modified adhesive films on the periphery of the honeycomb plate; and (3) performing electron beam curing on the upper surface and the peripheral edge sealing positions of the honeycomb plate by adopting electron beam curing equipment, wherein the irradiation dose is 150keV, turning over the honeycomb plate by using a tool, and performing electron beam curing on the lower surface of the honeycomb plate, wherein the irradiation dose is 150 keV. After curing, the edges were sealed with 1170 aluminium-based tape 40mm wide. After molding, the flatness of the honeycomb plate reaches 0.35 mm.
The honeycomb plate formed by the method has the advantages of high precision, small residual stress, high dimensional stability, high curing speed, short forming period, low production cost and the like.
In the description of the present application, it is to be understood that the terms "upper", "lower", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like indicate orientations or positional relationships based on those shown in the drawings, and are only for convenience in describing the present application and simplifying the description, but do not indicate or imply that the referred device or element must have a specific orientation, be constructed in a specific orientation, and be operated, and thus, should not be construed as limiting the present application.
The foregoing description of specific embodiments of the present invention has been presented. It is to be understood that the present invention is not limited to the specific embodiments described above, and that various changes or modifications may be made by one skilled in the art within the scope of the appended claims without departing from the spirit of the invention. The embodiments and features of the embodiments of the present application may be combined with each other arbitrarily without conflict.
Claims (7)
1. A honeycomb sandwich structure plate for a satellite is characterized by comprising a panel (1), a honeycomb core (2) and an adhesive (3); the panel (1) is connected with the honeycomb core (2) through an adhesive (3);
the thickness range of the panel (1) is 0.1-0.6 mm, and the panel is prepared from a carbon fiber composite material, wherein the carbon fiber composite material comprises resin and carbon fibers, and the content range of the resin is 20-40 wt%;
the carbon fiber comprises any one or combination of more of a high-strength T300, a high-strength T700, a high-strength T800, a high-strength T1000, a high model M35, a high model M40, a high model M55J and a high model M60; the resin comprises an epoxy resin modified with a first photoinitiator and/or a cyanate ester resin modified with a first photoinitiator.
2. The satellite honeycomb sandwich panel according to claim 1, wherein the first photoinitiator is a diaryliodonium salt and/or a triarylsulfonium salt; in the epoxy resin modified by the first photoinitiator and/or the cyanate ester resin modified by the first photoinitiator, the amount of the first photoinitiator is 0.5wt% to 3wt% of the total weight of the resin.
3. The honeycomb sandwich structure plate for the satellite according to claim 1, wherein the honeycomb core (2) is a regular hexagonal perforated honeycomb and is made of an aluminum alloy material including Al-Mg series rust-preventive aluminum 5a 02; the wall thickness range of the honeycomb core (2) is 0.03 mm-0.06 mm, and the side length range of the core grid is 3 mm-6 mm.
4. The satellite honeycomb sandwich structure plate according to claim 1, wherein the adhesive (3) comprises a structural adhesive film modified by a second photoinitiator, the structural adhesive film comprising any one or any combination of J-47C, J-78B and Redox 312.
5. The satellite honeycomb sandwich panel according to claim 4, wherein the second photoinitiator comprises a diaryliodonium salt and/or a triarylsulfonium salt; in the structural adhesive film modified by the second photoinitiator, the amount of the second photoinitiator accounts for 1-5 wt% of the total weight of the structural adhesive film.
6. A process for molding a satellite honeycomb sandwich panel for manufacturing the satellite honeycomb sandwich panel according to any one of claims 1 to 5, comprising:
s1, preparing a prepreg by using resin modified by a first photoinitiator and carbon fiber, wherein the resin content is 20-40 wt%, and the thickness is 0.1-0.3 mm;
s2, cutting the prepreg according to the design size, then paving the panel (1) on the surface of the metal mold according to the paving requirement, and sticking a layer of structural adhesive film modified by a second photoinitiator on the uppermost layer;
s3, vacuumizing the laid prepreg until the relative pressure of the reference standard atmospheric pressure is not more than-0.097 MPa, and vacuumizing for not less than 4 h;
s4, sequentially placing a lower panel prepreg, a honeycomb core (2) and an upper panel prepreg on a forming die, and pre-attaching the prepregs and the honeycomb core (2) by hot air blowing to obtain a honeycomb plate;
s5, adhering 1-5 layers of second photoinitiator modified structural adhesive films to the periphery of the honeycomb plate;
and S6, performing electron beam curing on the upper surface, the lower surface and the peripheral edge sealing positions of the honeycomb plate by adopting electron beam curing equipment, wherein the irradiation dose is 50 keV-300 keV.
7. The process for molding a honeycomb sandwich panel for a satellite according to claim 6, further comprising:
and S7, after the curing is finished, sealing edges of the honeycomb plate by 1170 aluminum-based adhesive tapes.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811520187.2A CN109397782B (en) | 2018-12-12 | 2018-12-12 | Honeycomb sandwich structure plate for satellite and forming process thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201811520187.2A CN109397782B (en) | 2018-12-12 | 2018-12-12 | Honeycomb sandwich structure plate for satellite and forming process thereof |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN109397782A CN109397782A (en) | 2019-03-01 |
| CN109397782B true CN109397782B (en) | 2020-09-04 |
Family
ID=65458764
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201811520187.2A Active CN109397782B (en) | 2018-12-12 | 2018-12-12 | Honeycomb sandwich structure plate for satellite and forming process thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN109397782B (en) |
Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109969432B (en) * | 2019-04-04 | 2021-02-05 | 北京卫星制造厂有限公司 | Detachable heat-proof structure and preparation method and application thereof |
| CN111300943A (en) * | 2020-03-25 | 2020-06-19 | 西北工业大学 | Thick-wall honeycomb sandwich structure and method |
| CN112895611B (en) * | 2021-02-19 | 2023-04-18 | 航天科工空间工程发展有限公司 | Satellite structure cabin board |
| CN114030241B (en) * | 2021-10-11 | 2024-05-14 | 航天材料及工艺研究所 | Carbon fiber composite honeycomb, preparation method and application |
| CN114275196A (en) * | 2021-12-31 | 2022-04-05 | 中国电子科技集团公司第三十八研究所 | Satellite-borne temperature control and installation integrated plate based on thermoelectric effect |
Family Cites Families (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP3180455B2 (en) * | 1992-07-23 | 2001-06-25 | スズキ株式会社 | Method and apparatus for manufacturing three-dimensional honeycomb-shaped structure |
| CN102009501B (en) * | 2009-09-08 | 2013-11-27 | 上海卫星工程研究所 | Enhanced honeycomb sandwich structural slab and production method thereof |
| CN106216176A (en) * | 2016-07-22 | 2016-12-14 | 苏州芳磊蜂窝复合材料有限公司 | A kind of glass cloth honeycomb glue spreading method and the glue spreading apparatus of use thereof |
-
2018
- 2018-12-12 CN CN201811520187.2A patent/CN109397782B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN109397782A (en) | 2019-03-01 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN109397782B (en) | Honeycomb sandwich structure plate for satellite and forming process thereof | |
| CN101269553B (en) | Magnesium alloy cellular board and manufacturing technique | |
| US10828870B2 (en) | Process for manufacturing apron board of high-speed rail equipment cabin using composite material | |
| CN107139503B (en) | The forming method of composite material cylinder component partial honeycomb sandwich construction | |
| CN106739192B (en) | A kind of full carbon fiber composite material reflector substrate and preparation method thereof | |
| EP2399739A1 (en) | Method for producing resin-based composite | |
| CN103552252A (en) | Manufacture method of high-precision carbon fiber composite antenna panel | |
| CN106019436B (en) | A kind of optical system full carbon fiber composite material reflector and manufacturing method | |
| CN109130336A (en) | A kind of high precision high stability composite material antenna reflective face and preparation method thereof | |
| US20140233121A1 (en) | Sandwich structure unit for solar collector mirrors | |
| CN104749735A (en) | Splicing type conformal optical window | |
| CN104999672A (en) | Molding method of double-curvature variable-section variable-thickness through beam | |
| CN210885911U (en) | High-performance buffering heat dissipation material for OLED product | |
| CN114256371A (en) | Lightweight photovoltaic module and preparation method and application thereof | |
| CN107968131B (en) | Solar cell back sheet, preparation method thereof and solar cell module comprising same | |
| CN201883606U (en) | Special-shaped aluminium cellular board | |
| CN102501502A (en) | KT (Karat) board for advertisement and preparation method thereof | |
| CN207474482U (en) | A kind of high altitude long time solar energy unmanned plane photovoltaic aerofoil | |
| CN217531534U (en) | Assembled composite material forming tool | |
| CN111300943A (en) | Thick-wall honeycomb sandwich structure and method | |
| CN105116516A (en) | Solar thermal power generation composite backboard and preparation method | |
| CN205755092U (en) | A kind of positioning carrier of the laminate for surface mount process | |
| CN109435274A (en) | A kind of the positioning assemble method and device of part and composite material skeleton stressed-skin construction | |
| CN220095758U (en) | Layering structure of radar reflector | |
| CN220012517U (en) | Outdoor double-sided adhesive tape for bonding in extremely cold region |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |