CN117656525A - Reflector panel for geosynchronous orbit microwave imaging and manufacturing method thereof - Google Patents
Reflector panel for geosynchronous orbit microwave imaging and manufacturing method thereof Download PDFInfo
- Publication number
- CN117656525A CN117656525A CN202311548964.5A CN202311548964A CN117656525A CN 117656525 A CN117656525 A CN 117656525A CN 202311548964 A CN202311548964 A CN 202311548964A CN 117656525 A CN117656525 A CN 117656525A
- Authority
- CN
- China
- Prior art keywords
- reflector panel
- composite material
- temperature
- skin
- normal
- 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.)
- Pending
Links
- 238000004519 manufacturing process Methods 0.000 title claims abstract description 26
- 238000003384 imaging method Methods 0.000 title claims abstract description 25
- 239000002131 composite material Substances 0.000 claims abstract description 69
- 229920005989 resin Polymers 0.000 claims abstract description 43
- 239000011347 resin Substances 0.000 claims abstract description 43
- 239000011159 matrix material Substances 0.000 claims abstract description 20
- 239000000853 adhesive Substances 0.000 claims abstract description 15
- 230000001070 adhesive effect Effects 0.000 claims abstract description 15
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 34
- 239000004917 carbon fiber Substances 0.000 claims description 34
- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 31
- 239000000463 material Substances 0.000 claims description 13
- 238000007493 shaping process Methods 0.000 claims description 13
- 239000003795 chemical substances by application Substances 0.000 claims description 8
- 238000005520 cutting process Methods 0.000 claims description 8
- 239000004519 grease Substances 0.000 claims description 8
- 229920001296 polysiloxane Polymers 0.000 claims description 8
- 239000011248 coating agent Substances 0.000 claims description 7
- 238000000576 coating method Methods 0.000 claims description 7
- 239000000835 fiber Substances 0.000 claims description 7
- 239000012783 reinforcing fiber Substances 0.000 claims description 7
- 238000004804 winding Methods 0.000 claims description 4
- 239000003733 fiber-reinforced composite Substances 0.000 claims description 3
- 238000009849 vacuum degassing Methods 0.000 claims description 3
- 239000003822 epoxy resin Substances 0.000 claims description 2
- 239000003292 glue Substances 0.000 claims description 2
- 229920000647 polyepoxide Polymers 0.000 claims description 2
- 238000004026 adhesive bonding Methods 0.000 abstract description 6
- 238000000465 moulding Methods 0.000 abstract description 5
- 238000010438 heat treatment Methods 0.000 abstract 1
- 238000001514 detection method Methods 0.000 description 6
- XLJMAIOERFSOGZ-UHFFFAOYSA-M cyanate Chemical compound [O-]C#N XLJMAIOERFSOGZ-UHFFFAOYSA-M 0.000 description 4
- 238000002844 melting Methods 0.000 description 4
- 239000002313 adhesive film Substances 0.000 description 2
- 230000007613 environmental effect Effects 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 238000002360 preparation method Methods 0.000 description 2
- 229920002748 Basalt fiber Polymers 0.000 description 1
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 229920000271 Kevlar® Polymers 0.000 description 1
- 244000137852 Petrea volubilis Species 0.000 description 1
- 230000002411 adverse Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 239000003365 glass fiber Substances 0.000 description 1
- 239000012212 insulator Substances 0.000 description 1
- 239000004761 kevlar Substances 0.000 description 1
- 238000013507 mapping Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 238000002156 mixing Methods 0.000 description 1
- 230000035515 penetration Effects 0.000 description 1
- 238000011056 performance test Methods 0.000 description 1
- 238000005498 polishing Methods 0.000 description 1
- 239000010453 quartz Substances 0.000 description 1
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N silicon dioxide Inorganic materials O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 description 1
- 230000008646 thermal stress Effects 0.000 description 1
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
- 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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
-
- H—ELECTRICITY
- H01—ELECTRIC ELEMENTS
- H01Q—ANTENNAS, i.e. RADIO AERIALS
- H01Q15/00—Devices for reflection, refraction, diffraction or polarisation of waves radiated from an antenna, e.g. quasi-optical devices
- H01Q15/14—Reflecting surfaces; Equivalent structures
- H01Q15/141—Apparatus or processes specially adapted for manufacturing reflecting surfaces
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- Manufacturing & Machinery (AREA)
- Physics & Mathematics (AREA)
- Electromagnetism (AREA)
Abstract
The invention provides a reflector panel for geosynchronous orbit microwave imaging and a manufacturing method thereof, wherein the reflector panel comprises an inner skin, an outer skin and a composite material pipe, and the manufacturing steps comprise: the inner and outer skins of the reflector and the composite tube are manufactured separately. The inner skin, the composite material pipe and the outer skin are sequentially placed in a die, the inner skin, the composite material pipe and the outer skin are integrated into a whole through secondary curing of a resin matrix by pressurizing and heating, and the number, the diameter and the wall thickness of the composite material pipe are adjusted according to the specific size of the reflector panel. The invention adopts the mode of secondary curing of the body resin matrix to realize the gluing of all parts, breaks through the integral molding mode of the existing reflector panel by combining all parts into a whole through the adhesive, greatly reduces the weight of the reflector panel, simultaneously greatly reduces the gluing deformation of the reflector panel caused by the adhesive, and greatly improves the integral rigidity and molding precision of the structure.
Description
Technical Field
The invention belongs to the technical field of composite material molding, and particularly relates to a reflector panel for geosynchronous orbit microwave imaging and a manufacturing method thereof. In particular to a light-weight and high-thermal-stability reflector panel for geosynchronous orbit microwave imaging.
Background
As global climate warms up since the 21 st century, annual extreme environmental disasters have increased significantly worldwide, with significant loss events caused by extreme environmental disasters exceeding 300 ten thousand dollars worldwide in 1980-2018, and thus the importance of climate environment detection has become increasingly prominent.
The stationary orbit microwave detection satellite combines the high timeliness advantage of the stationary orbit remote sensing detection with the microwave detection penetration capability, adopts the millimeter wave and submillimeter wave detector to perform all-day, all-weather and large-range high-frequency three-dimensional detection on the atmospheric temperature and humidity elements in the stationary orbit, and greatly improves the detection and prediction capability of the climate change.
The reflector panel for microwave imaging is a core functional component. The main receiving of the reflector panel is electromagnetic wave in microwave band, the surface accuracy of the reflector panel is less than 5 μm/square meter according to the mapping relation between the receiving microwave frequency of the reflecting surface and the RMS value of the reflecting panel, and the extreme temperature alternating environment of the geosynchronous orbit also provides extremely high requirements for the thermal stability of the reflector panel. The reflective panel of the all-carbon structure is the preferred scheme of the reflector panel structure due to the advantages of low thermal expansion, high precision and light weight. However, for the reflective panel with all-carbon structure, which is both the carbon honeycomb sandwich structure and the grid sandwich structure, because the parts are required to be connected by the adhesive, the thermal performance of the adhesive and the thermal performance of the parts are greatly different, which results in that the molding accuracy, weight and thermal stability of the reflector panel often cannot achieve the ideal objective.
Patent document CN108963466a discloses a composite material tubular array structure reflector and a manufacturing method thereof, the composite material tubular array structure reflector comprises an inner skin, an outer skin and a composite material tubular array structure, the inner skin and the outer skin are positioned on two sides of the composite material tubular array structure; the composite material pipe array structure comprises a plurality of composite material pipe fittings which are vertically arranged according to an array.
The patent document CN108963466a requires adhesive connection between parts such as adhesive films, which results in relatively heavy reflector, and the thermal expansion coefficient of the adhesive is generally 50×10 -6 The thermal expansion coefficient of the heat insulator is greatly different from that of carbon fiber and the like, so that the thermal deformation of the reflector is relatively large under the environments of high temperature, low temperature and the like.
The parts of the invention are formed by secondary curing of the resin matrix, namely, the parts are formed by reinforcing fibers and the resin matrix, the parts are molded by curing at a lower temperature, and then the resin matrix is secondarily cured by a higher temperature, so that the parts form a whole, and the adverse effect of the adhesive is removed.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a reflector panel for geosynchronous orbit microwave imaging and a manufacturing method thereof.
The invention provides a reflector panel for geosynchronous orbit microwave imaging, which comprises: an inner skin 1, an outer skin 2, and a composite tube 3;
the inner skin 1 and the outer skin 2 are respectively positioned at the inner side and the outer side of the composite material pipe 3;
the inner skin 1 and the outer skin 2 are connected by an intermediate composite tube 3.
Preferably, the inner skin 1 constitutes the use surface of the reflector; the outer skin 2 is made of resin-based fiber reinforced composite material;
any two parts or any plurality of parts of the inner skin 1, the outer skin 2 and the composite material pipe 3 are formed by secondary curing of a resin matrix, namely, the parts are formed by reinforcing fibers and the resin matrix, all parts are molded by curing at a lower temperature, and then the resin matrix is secondarily cured by curing at a higher temperature, so that all the parts form a whole without adopting adhesives.
Preferably, the composite material pipe 3 is a composite carbon fiber pipe; the thickness of the inner skin 1 and the outer skin 2 is 0.2-5 mm, the sandwich height of the matrix structure of the composite material pipe 3 is 50-100 mm, the thickness of the pipe wall of the composite material pipe 3 forming the matrix structure is 0.01-5 mm, and the pipe diameter is 1-20 mm.
The invention provides a manufacturing method of a reflector panel for geosynchronous orbit microwave imaging, which comprises the following steps:
step A: manufacturing an inner skin 1 and an outer skin 2;
and (B) step (B): manufacturing a composite material pipe 3;
step C: the inner skin 1, the outer skin 2 and the composite tube 3 are combined.
Preferably, the step a includes:
step 1: the component A, B of the normal-temperature curing resin is subjected to vacuum degassing to obtain the mixed normal-temperature curing resin; wherein the component A, B of the cured resin is epoxy resin AB glue;
step 2: placing the carbon fiber on a platform, and uniformly coating the mixed normal-temperature curing resin on the carbon fiber serving as the reinforcing fiber; adjusting the distance between the roller and the platform, extruding redundant normal-temperature curing resin on the reinforced fiber through the roller, and taking out to obtain carbon fiber normal-temperature prepreg;
step 3: cutting the carbon fiber normal-temperature prepreg according to the shape of the surface of the reflector panel;
step 4: coating silicone grease or a release agent on the mold, sequentially laying the cut carbon fiber normal-temperature prepreg on the mold according to the thickness of the reflector panel skin, wrapping the whole mold by a vacuum bag, and extracting air in the bag to ensure that the normal-temperature prepreg is subjected to vacuum pressure of 0.1MPa and is cured at normal temperature for 24 to 48 hours;
step 5: and taking out the cured skin from the mold, and removing the redundant materials at the edges to obtain the inner skin 1 and the outer skin 2 of the reflector panel.
Preferably, the step B includes:
step 6: cutting the carbon fiber normal-temperature prepreg according to the shape of a rod-shaped die for forming the composite material pipe 3;
step 7: coating silicone grease or a release agent on the mold, sequentially winding the cut carbon fiber normal-temperature prepreg on a rod-shaped mold according to the thickness of the composite material pipe 3, wrapping the whole mold by a vacuum bag, and extracting air in the bag to ensure that the carbon fiber normal-temperature prepreg is subjected to vacuum pressure of 0.1MPa and is cured at normal temperature for 24 to 48 hours;
step 8: and taking the cured skin out of the mold, and removing the redundant edge material to obtain the reflector panel composite material pipe 3.
Preferably, the step C includes:
step 9: placing the inner skin 1 in a mold, uniformly placing the composite material pipe 3 on the inner skin 1, and placing the outer skin 2 on the composite material pipe 3;
step 10: and (3) placing the assembled reflector panel into a forming die for high-temperature curing and shaping, and taking out the reflector panel from the die after the completion of the high-temperature curing and shaping.
Preferably, the component A, B of the normal-temperature-cured resin has a curing temperature of 20 ℃ to 45 ℃, the curing degree of the normal-temperature-cured resin is 50% to 60%, the normal-temperature-cured resin is subjected to secondary curing at 120 ℃, and the curing degree of the normal-temperature-cured resin is 95% to 100% after the secondary curing; and placing the assembled reflector panel in a forming die, curing and shaping at a high temperature of 120 ℃, and taking out the reflector panel from the die after the completion of the curing and shaping.
Preferably, the manufacturing method is a manufacturing method of the reflector panel for geosynchronous orbit microwave imaging.
According to the reflector panel provided by the invention, the reflector panel is manufactured according to the manufacturing method of the reflector panel for the geosynchronous orbit microwave imaging.
Therefore, compared with the prior art, the invention has the beneficial effects that:
1. the invention has no addition of any adhesive in the process of forming the reflector panel, breaks the current situation that most reflectors adopt adhesives to fix all parts into a whole, and realizes the gelation-free light weight of the sandwich reflector structure; that is, the reflector panel adopts the mode of secondary curing of the resin matrix of the body to realize the gluing of all parts, so that the existing reflector panel is broken through the integral forming mode of combining all parts into a whole through the adhesive, the weight of the reflector panel is greatly reduced, meanwhile, the gluing deformation of the reflector panel caused by the adhesive is greatly reduced, and the integral rigidity and the forming precision of the structure are greatly improved.
2. The composite material matrix and the reinforcing fiber used in the whole structure of the reflector panel are made of the same material, so that the thermal stress and the thermal deformation of the inside of the reflector panel caused by inconsistent thermal expansion of the materials are greatly reduced.
3. The invention enables the reflector panel to truly realize an all-carbon structure.
Drawings
Other features, objects and advantages of the present invention will become more apparent upon reading of the detailed description of non-limiting embodiments, given with reference to the accompanying drawings in which:
FIG. 1 is a schematic diagram of a composite matrix structural reflector according to the present invention.
The figure shows:
an inner skin 1; an outer skin 2; a composite material pipe 3; individual composite tubes 4
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 present invention, but are not intended to limit the invention in any way. It should be noted that variations and modifications could be made by those skilled in the art without departing from the inventive concept. These are all within the scope of the present invention.
As shown in fig. 1, the structure of the light-weight high-thermal-stability reflector panel for geosynchronous orbit microwave imaging according to the present invention comprises: an inner skin 1, an outer skin 2, a composite tube 3. The inner skin 1 and the outer skin 2 are positioned on the inner side and the outer side of the composite material pipe 3. The inner skin 1 is the use surface of the reflector, and the inner skin 1 and the outer skin 2 are connected by an intermediate composite tube 3, such as a plurality of carbon fiber tubes. The reflector is of a sandwich structure and is divided into three layers, wherein the innermost layer is an inner skin 1, the middle layer is a composite material pipe 3, and the outermost layer is an outer skin 2.
The thickness of the inner skin 1 and the outer skin 2 is 0.2-5 mm, the sandwich height of the matrix structure of the composite material tube 3 is 50-100 mm, the thickness of the tube wall forming the matrix structure of the composite material tube is 0.01-5 mm, and the tube diameter is 1-20 mm.
According to the preparation method of the reflector panel provided by the invention, the inner skin 1 and the outer skin 2 are resin-based fiber reinforced composite materials, wherein the fibers comprise any one or any plurality of various fibers such as carbon fibers, glass fibers, kevlar fibers, quartz fibers, basalt fibers and the like. The inner skin 1, the composite material pipe 3 and the outer skin 2 are sequentially placed in a die, the outer side is pressurized and heated, and the inner skin 1, the composite material pipe 3 and the outer skin 2 are integrated into a whole through secondary curing of a resin matrix, wherein the number, the diameter and the wall thickness of the composite material pipe are adjusted according to the specific size of the reflector panel.
The preparation method of the reflector panel comprises the following steps:
step A: manufacturing an inner skin 1 and an outer skin 2;
and (B) step (B): manufacturing a composite material pipe 3;
step C: the inner skin 1, the outer skin 2 and the composite tube 3 are combined.
The step A comprises the following steps:
step 1: uniformly mixing the components of the normal-temperature curing resin A, B according to the ratio of 2:5, and carrying out vacuum degassing to obtain the mixed normal-temperature curing resin;
step 2: placing M55J carbon fibers on a platform horizontally, and uniformly coating the mixed normal-temperature curing resin on the M55J carbon fibers serving as reinforcing fibers; adjusting the distance between the roller and the platform, extruding redundant normal-temperature curing resin on the reinforced fiber through the roller, and taking out to obtain the M55J carbon fiber normal-temperature prepreg;
step 3: cutting the M55J carbon fiber normal-temperature prepreg according to the shape of the surface of the reflector panel;
step 4: and (3) smearing silicone grease or a release agent on the mold, sequentially laying the cut M55J carbon fiber normal-temperature prepreg on the mold according to the thickness of the reflector panel skin, wrapping the whole mold by a vacuum bag, and extracting air in the bag to ensure that the normal-temperature prepreg is subjected to vacuum pressure of 0.1MPa and is cured at normal temperature for 24 to 48 hours.
Step 5: and taking out the cured skin from the mold, and removing the redundant materials at the edges to obtain the inner skin 1 and the outer skin 2 of the reflector panel.
The step B comprises the following steps:
step 6: cutting the M55J carbon fiber normal-temperature prepreg according to the shape of a rod-shaped die for forming the composite material pipe 3;
step 7: and (3) smearing silicone grease or a release agent on the mold, sequentially winding the cut M55J carbon fiber normal-temperature prepreg on a rod-shaped mold according to the thickness of the composite material pipe 3, wrapping the whole mold by a vacuum bag, and extracting air in the bag to ensure that the M55J carbon fiber normal-temperature prepreg is subjected to vacuum pressure of 0.1MPa, and curing at normal temperature for 24 to 48 hours.
Step 8: and taking the cured skin out of the mold, and removing the redundant edge material to obtain the reflector panel composite material pipe 3.
The step C comprises the following steps:
step 9: placing the inner skin 1 in a mold, uniformly placing the composite material pipe 3 on the inner skin 1, and placing the outer skin 2 on the composite material pipe 3;
step 10: and (3) placing the assembled reflector panel into a forming die for high-temperature curing and shaping, and taking out the reflector panel from the die after the completion of the high-temperature curing and shaping. The assembled reflector panel is placed in a forming die as a preferable scheme, high-temperature curing and shaping are carried out at 120 ℃, and the reflector panel is taken out from the die after finishing.
The light high-heat stable reflector panel for the geosynchronous orbit microwave imaging is characterized in that the thickness of the inner skin 1 and the outer skin 2 is 0.2-5 mm, the sandwich height of the tubular array structure of the composite material tube 3 is 50-100 mm, the thickness of the tube wall of the composite material tubular array structure is 0.01-5 mm, and the tube diameter is 1-20 mm.
The manufacturing method of the light high-thermal stability reflector panel for the geosynchronous orbit microwave imaging is characterized in that the normal-temperature curing resin is characterized in that: comprises A, B two components, the curing temperature is 20-45 ℃, the curing degree of the resin after normal temperature curing is 50-60%, the resin after normal temperature curing is subjected to secondary curing at 120 ℃, and the curing degree of the resin after normal temperature curing after secondary curing is 95-100%.
The surface accuracy RMS value of the use surface of the reflector panel is less than or equal to 10 micrometers per square meter. The variation of the surface profile accuracy RMS of the reflector panel is less than or equal to 3 microns/square meter in the range of-170 ℃ to 130 ℃. The density of the reflector panel is less than or equal to 42kg/m 3 。
The reflector panel adopts the mode of secondary curing of the resin matrix of the body to realize the gluing of all parts, breaks through the integral forming mode of the existing reflector panel by combining all parts into a whole through the adhesive, greatly reduces the weight of the reflector panel, simultaneously greatly reduces the gluing deformation of the reflector panel caused by the adhesive, and greatly improves the integral rigidity and forming precision of the structure.
The present invention will be described in more detail below.
Step 1: cutting the M55J carbon fiber cyanate thermal melting prepreg according to the shape of the reflector panel surface;
step 2: and (3) smearing silicone grease or a release agent on the mold, sequentially laying the cut M55J carbon fiber cyanate hot-melting prepreg on the mold according to the thickness of the reflector panel skin, wrapping the whole mold by a vacuum bag, extracting air in the bag, ensuring that the prepreg is subjected to vacuum pressure of 0.1MPa at normal temperature, and curing for 24 hours at 180 ℃.
Step 3: and taking out the cured skin from the mold, and removing the redundant materials at the edges to obtain the inner skin 1 and the outer skin 2 of the reflector panel.
Step 4: cutting the M55J carbon fiber cyanate hot-melting prepreg according to the shape of a rod-shaped die for forming the composite material pipe 3;
step 5: and (3) smearing silicone grease or a release agent on the mold, sequentially winding the cut M55J carbon fiber cyanate hot-melting prepreg on a rod-shaped mold according to the thickness of the composite material pipe 3, wrapping the whole mold by a vacuum bag, extracting air in the bag, ensuring that the prepreg is subjected to vacuum pressure of 0.1MPa at normal temperature, and curing for 24 hours at 180 ℃.
Step 6: and taking the cured skin out of the mold, and removing the redundant edge material to obtain the reflector panel composite material pipe 3.
Step 7: and (3) polishing the bonding surfaces of the inner skin 1 and the outer skin 2 by sand paper, and paving a layer of medium-temperature curing adhesive film on the bonding surfaces.
Step 8: placing the inner skin 1 in a mold, uniformly placing the composite material pipe 3 on the inner skin 1, and placing the outer skin 2 on the composite material pipe 3;
step 9: and (3) placing the assembled reflector panel into a forming die for high-temperature curing and shaping, and taking out the reflector panel from the die after the completion of the high-temperature curing and shaping.
The performance test results of the carbon fiber array structure prepared in the preferred embodiment are as follows: density 63.78kg/m 3 The method comprises the steps of carrying out a first treatment on the surface of the The surface profile molding accuracy RMS value of the reflector panel was 30 microns/square meter. The reflector panel used a 20 micron/square meter variation in areal profile accuracy RMS in the range of-170 ℃ to 130 ℃.
In the description of the present application, it should 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 the orientations or positional relationships illustrated in the drawings, merely to facilitate description of the present application and simplify the description, and do not indicate or imply that the devices or elements being referred to must have a specific orientation, be configured and operated in a specific orientation, and are not to be construed as limiting the present application.
The foregoing describes specific embodiments of the present invention. It is to be understood that the invention is not limited to the particular embodiments described above, and that various changes or modifications may be made by those skilled in the art within the scope of the appended claims without affecting the spirit of the invention. The embodiments of the present application and features in the embodiments may be combined with each other arbitrarily without conflict.
Claims (10)
1. A reflector panel for geosynchronous orbit microwave imaging, comprising: an inner skin (1), an outer skin (2), and a composite tube (3);
the inner skin (1) and the outer skin (2) are respectively positioned at the inner side and the outer side of the composite material pipe (3);
the inner skin (1) and the outer skin (2) are connected through a middle composite material pipe (3).
2. Reflector panel for geosynchronous orbit microwave imaging according to claim 1, characterized in that said inner skin (1) constitutes the use surface of the reflector; the outer skin (2) is made of resin-based fiber reinforced composite material;
any two parts or any plurality of parts of the inner skin (1), the outer skin (2) and the composite material pipe (3) are formed by secondary curing of the resin matrix, namely, the parts are formed by reinforcing fibers and the resin matrix, all parts are molded by curing at a lower temperature, and then the resin matrix is secondarily cured at a higher temperature, so that all the parts form a whole without adopting adhesives.
3. The reflector panel for geosynchronous orbit microwave imaging according to claim 1, wherein the composite material tube (3) is a composite carbon fiber tube; the thickness of the inner skin (1) and the outer skin (2) is 0.2-5 mm, the sandwich height of the tubular array structure of the composite material tube (3) is 50-100 mm, the thickness of the tube wall of the composite material tube (3) forming the tubular array structure is 0.01-5 mm, and the tube diameter is 1-20 mm.
4. A method of making a reflector panel for geosynchronous orbit microwave imaging, comprising:
step A: manufacturing an inner skin (1) and an outer skin (2);
and (B) step (B): manufacturing a composite material pipe (3);
step C: the inner skin (1), the outer skin (2) and the composite tube (3) are combined.
5. The method of manufacturing a reflector panel for geosynchronous orbit microwave imaging according to claim 4, wherein said step a comprises:
step 1: the component A, B of the normal-temperature curing resin is subjected to vacuum degassing to obtain the mixed normal-temperature curing resin; wherein the component A, B of the cured resin is epoxy resin AB glue;
step 2: placing the carbon fiber on a platform, and uniformly coating the mixed normal-temperature curing resin on the carbon fiber serving as the reinforcing fiber; adjusting the distance between the roller and the platform, extruding redundant normal-temperature curing resin on the reinforced fiber through the roller, and taking out to obtain carbon fiber normal-temperature prepreg;
step 3: cutting the carbon fiber normal-temperature prepreg according to the shape of the surface of the reflector panel;
step 4: coating silicone grease or a release agent on the mold, sequentially laying the cut carbon fiber normal-temperature prepreg on the mold according to the thickness of the reflector panel skin, wrapping the whole mold by a vacuum bag, and extracting air in the bag to ensure that the normal-temperature prepreg is subjected to vacuum pressure of 0.1MPa and is cured at normal temperature for 24 to 48 hours;
step 5: and taking out the cured skin from the mold, and removing the redundant material at the edge to obtain the inner skin (1) and the outer skin (2) of the reflector panel.
6. The method of manufacturing a reflector panel for geosynchronous orbit microwave imaging according to claim 5, wherein said step B comprises:
step 6: cutting the carbon fiber normal-temperature prepreg according to the shape of a rod-shaped die for forming the composite material pipe (3);
step 7: coating silicone grease or a release agent on the mold, sequentially winding the cut carbon fiber normal-temperature prepreg on a rod-shaped mold according to the thickness of a composite material pipe (3), wrapping the whole mold by a vacuum bag, and extracting air in the bag to ensure that the carbon fiber normal-temperature prepreg is subjected to vacuum pressure of 0.1MPa and is cured at normal temperature for 24 to 48 hours;
step 8: and taking the cured skin out of the mold, and removing the redundant material at the edge to obtain the reflector panel composite material pipe (3).
7. The method of manufacturing a reflector panel for geosynchronous orbit microwave imaging according to claim 6, wherein said step C comprises:
step 9: placing the inner skin (1) in a mould, uniformly placing the composite material pipe (3) on the inner skin (1), and placing the outer skin (2) on the composite material pipe (3);
step 10: and (3) placing the assembled reflector panel into a forming die for high-temperature curing and shaping, and taking out the reflector panel from the die after the completion of the high-temperature curing and shaping.
8. The method of manufacturing a reflector panel for microwave imaging of geosynchronous orbit according to claim 4, wherein the component A, B is a room temperature curing resin, the curing temperature is 20 ℃ to 45 ℃, the curing degree of the room temperature curing resin is 50% to 60%, the room temperature curing resin is subjected to secondary curing at 120 ℃, and the curing degree of the room temperature curing resin is 95% to 100%; and placing the assembled reflector panel in a forming die, curing and shaping at a high temperature of 120 ℃, and taking out the reflector panel from the die after the completion of the curing and shaping.
9. The method of manufacturing a reflector panel for geosynchronous orbit microwave imaging according to claim 4, wherein the method of manufacturing a reflector panel for geosynchronous orbit microwave imaging according to any one of claims 1 to 3.
10. A reflector panel, characterized in that it is manufactured by the manufacturing method of the reflector panel for geosynchronous orbit microwave imaging according to any one of claims 4 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311548964.5A CN117656525A (en) | 2023-11-20 | 2023-11-20 | Reflector panel for geosynchronous orbit microwave imaging and manufacturing method thereof |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311548964.5A CN117656525A (en) | 2023-11-20 | 2023-11-20 | Reflector panel for geosynchronous orbit microwave imaging and manufacturing method thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN117656525A true CN117656525A (en) | 2024-03-08 |
Family
ID=90070479
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311548964.5A Pending CN117656525A (en) | 2023-11-20 | 2023-11-20 | Reflector panel for geosynchronous orbit microwave imaging and manufacturing method thereof |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117656525A (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118046592A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
-
2023
- 2023-11-20 CN CN202311548964.5A patent/CN117656525A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118046592A (en) * | 2024-04-15 | 2024-05-17 | 上海复合材料科技有限公司 | Pipe array structure and manufacturing method thereof |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US5683646A (en) | Fabrication of large hollow composite structure with precisely defined outer surface | |
| CN109638445B (en) | Preparation method of high-temperature-resistant foam A interlayer composite material radome | |
| CN103273662B (en) | The preparation method of low-thermal-expansion carbon fiber enhancement resin base composite material mould | |
| CN105552567A (en) | Antenna reflection plane and preparation method therefor | |
| CN106019436B (en) | A kind of optical system full carbon fiber composite material reflector and manufacturing method | |
| CN108511920A (en) | Covering reinforced structure antenna reflector and preparation method thereof | |
| CN106739192B (en) | A kind of full carbon fiber composite material reflector substrate and preparation method thereof | |
| CN117656525A (en) | Reflector panel for geosynchronous orbit microwave imaging and manufacturing method thereof | |
| CN109407188B (en) | Preparation method of carbon fiber composite material reflector and related reflector | |
| CN106042503B (en) | A kind of preparation method of Ultralight sandwich structure composite material | |
| CN105643955A (en) | High-precision copying method of carbon fiber composite space optical mirror plane | |
| CN109130336A (en) | A kind of high precision high stability composite material antenna reflective face and preparation method thereof | |
| CN106671557A (en) | Molding method of aramid fiber composite material frequency selection surface reflector | |
| CN105459474A (en) | Low-density and high-performance composite sandwich structure and preparation method thereof | |
| CN112537047B (en) | Forming and assembling method for composite material reflector | |
| CN108000968A (en) | A kind of new Terahertz carbon fiber composite panel structure | |
| CN112537435A (en) | Composite material wing beam with high-precision curved surface and large length-diameter ratio and preparation method thereof | |
| CN114801237A (en) | Forming method of full-height edge-covered sandwich composite material part | |
| CN114889233B (en) | Light rib and forming method thereof | |
| Kuo et al. | Composite materials application on FORMOSAT-5 remote sensing instrument structure | |
| CN110789145B (en) | Checking structure for secondary bonding molding of composite material honeycomb sandwich structure | |
| CN118046592B (en) | Pipe array structure and manufacturing method thereof | |
| CN110757909A (en) | Novel carbon-fibre composite telescope antenna panel structure | |
| CN109273862A (en) | Carbon fiber parabola antenna and its focusing assembly method | |
| CN217531534U (en) | Assembled composite material forming tool |
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 |