CN110948911A - Forming method of grid structure composite material component - Google Patents
Forming method of grid structure composite material component Download PDFInfo
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- CN110948911A CN110948911A CN201911307294.1A CN201911307294A CN110948911A CN 110948911 A CN110948911 A CN 110948911A CN 201911307294 A CN201911307294 A CN 201911307294A CN 110948911 A CN110948911 A CN 110948911A
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- 239000002131 composite material Substances 0.000 title claims abstract description 24
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- 238000002347 injection Methods 0.000 claims abstract description 32
- 239000007924 injection Substances 0.000 claims abstract description 32
- 230000008569 process Effects 0.000 claims abstract description 21
- 239000000463 material Substances 0.000 claims abstract description 13
- 238000003825 pressing Methods 0.000 claims abstract description 13
- 238000005192 partition Methods 0.000 claims abstract description 10
- 238000004026 adhesive bonding Methods 0.000 claims abstract description 9
- 238000004519 manufacturing process Methods 0.000 claims description 15
- 239000011347 resin Substances 0.000 claims description 15
- 229920005989 resin Polymers 0.000 claims description 15
- 238000000465 moulding Methods 0.000 claims description 8
- 229920000049 Carbon (fiber) Polymers 0.000 claims description 5
- 239000004917 carbon fiber Substances 0.000 claims description 5
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- VNWKTOKETHGBQD-UHFFFAOYSA-N methane Chemical compound C VNWKTOKETHGBQD-UHFFFAOYSA-N 0.000 claims description 5
- 239000002313 adhesive film Substances 0.000 claims description 4
- 238000005086 pumping Methods 0.000 claims description 4
- RYGMFSIKBFXOCR-UHFFFAOYSA-N Copper Chemical compound [Cu] RYGMFSIKBFXOCR-UHFFFAOYSA-N 0.000 claims description 3
- 239000010949 copper Substances 0.000 claims description 3
- 229910052802 copper Inorganic materials 0.000 claims description 3
- 238000005520 cutting process Methods 0.000 claims description 3
- 238000007599 discharging Methods 0.000 claims description 3
- 239000004744 fabric Substances 0.000 claims description 3
- 238000009434 installation Methods 0.000 claims description 3
- 238000003754 machining Methods 0.000 abstract description 3
- 238000009745 resin transfer moulding Methods 0.000 description 8
- 230000006872 improvement Effects 0.000 description 7
- 210000001503 joint Anatomy 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 2
- 239000011157 advanced composite material Substances 0.000 description 2
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Classifications
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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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
-
- 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
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/007—Tempering units for temperature control of moulds or cores, e.g. comprising heat exchangers, controlled valves, temperature-controlled circuits for fluids
-
- 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
- B29C35/00—Heating, cooling or curing, e.g. crosslinking or vulcanising; Apparatus therefor
- B29C35/02—Heating or curing, e.g. crosslinking or vulcanizing during moulding, e.g. in a mould
-
- 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
- B29C65/00—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor
- B29C65/48—Joining or sealing of preformed parts, e.g. welding of plastics materials; Apparatus therefor using adhesives, i.e. using supplementary joining material; solvent bonding
-
- 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
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/44—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding
- B29C70/443—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using isostatic pressure, e.g. pressure difference-moulding, vacuum bag-moulding, autoclave-moulding or expanding rubber-moulding and impregnating by vacuum or injection
-
- 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
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Health & Medical Sciences (AREA)
- Oral & Maxillofacial Surgery (AREA)
- Thermal Sciences (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The invention discloses a forming method of a grid structure composite material component, which comprises the following steps: 1, forming the grid structure in a partition mode, and respectively forming a plurality of frames and side wall plates independently by adopting an autoclave process; 2, gluing the plurality of frames and the side wall plates into a whole through a gluing tool; 3, detecting the position relation among the frames after the gluing is finished, and confirming that the size of the frames meets the requirements of a drawing; filling an R angle among the frame, the frame and the side wall plate by adopting a mould pressing process; 5, wrapping and connecting the plurality of frames and the side wall plates together by adopting a wrapping material; 6, placing the wrapped frame and the wrapped side wall plate into an RTM glue injection mold for glue injection; 7, placing the mould subjected to glue injection in an oven for curing; 8, demoulding to obtain the grid structure composite material component, the invention ensures the size of the product to be ensured by the RTM mould cavity, basically does not need machining, and has high size precision; the surface of the product is a mould attaching surface, so that the product is obviously lightened while the strength and the rigidity of the product are met, and the cost is reduced.
Description
Technical Field
The invention belongs to the technical field of aviation, and particularly relates to a forming method of a grid structure composite material component.
Background
The advanced composite material can correspondingly reduce the weight by 20-30% when being used for aerospace structures, which is an effect that other advanced technologies cannot achieve, so that the advanced composite material is increasingly widely applied in the aerospace field, and is rapidly developed into one of four aerospace structure materials after aluminum, steel and titanium.
The carbon fiber reinforced material is a marked product in the field of composite materials, has the advantages of anisotropy (designability), high specific strength, high specific modulus, corrosion resistance, fatigue resistance and the like, has good flexibility in design, can reduce the weight of a structure on the premise of meeting the requirements of rigidity, strength and fatigue performance, and has obvious advantages in the field of aerospace structure design.
The composite material with the grid structure is often selected in the structural design, has the characteristics of high strength, high rigidity and the like, and the composite material component with the grid structure has certain difficulty in molding due to the complex structure, so that the composite material component cannot be successfully produced in a single molding mode.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a method for forming a composite material member with a grid structure, which obviously reduces the weight of a product and reduces the cost while meeting the strength and rigidity of the product.
The purpose of the invention is realized as follows: a method of forming a lattice-structured composite material member, comprising the steps of:
step 1: forming the grid structure in a partition mode, wherein a plurality of frames and side wall plates are formed independently by adopting an autoclave process;
step 2: the frames and the side wall plates are glued into a whole through a gluing tool;
and step 3: after the gluing is finished, detecting the position relation among the frames, and confirming that the size of the frames meets the requirements of a drawing;
and 4, step 4: filling an R angle among the frame, the frame and the side wall plate by adopting a mould pressing process;
and 5: wrapping the plurality of frames and the side wall plates together by using a wrapping material;
step 6: placing the wrapped frame and the wrapped side wall plate into an RTM glue injection mold for glue injection;
and 7: placing the mould after glue injection in an oven for curing;
and 8: demolding to obtain the composite material member with lattice structure.
Compared with the prior art, the technical scheme adopted by the invention has the beneficial effects that: the grid structure composite material component is formed by combining an autoclave process and an RTM process, the size of a product is ensured by a mold cavity of an RTM mold, machining is basically not needed, and the size precision is high; the surface of the workpiece has no visible defects such as scratches, depressions, cracks, holes, excess materials, fiber breakage and the like; the final component is continuous, complete and uniform before and after various environmental tests, and has no phenomena of fiber exposure, no foaming, no cracks and the like; the surface of the product is a mould attaching surface, so that the product is obviously lightened while the strength and the rigidity of the product are met, and the cost is reduced.
As a further improvement of the present invention, in step 1, the plurality of frames include 6 closed frames and 1C-shaped frame, the 6 closed frames include 5 first typical frames and 1 second typical frame, the C-shaped frame is a third typical frame, and the side wall panels are U-shaped side wall panels.
As a further improvement of the present invention, the grid structure partition forming specifically includes: the manufacturing method comprises the steps of manufacturing by adopting a vacuum bag autoclave preforming process, prefabricating a first typical frame by using unidirectional prepreg according to a designed laying sequence, wherein the first typical frame is of a closed structure and adopts a butt-joint laying mode, a butt-joint port needs to be staggered, vacuumizing is performed once every 5 layers of laying, air bubbles are discharged by compaction, and bag manufacturing is performed in an autoclave and finally cured;
the manufacturing method comprises the steps of manufacturing by adopting a vacuum bag autoclave preforming process, prefabricating a second typical frame by using a unidirectional prepreg according to a designed laying sequence, wherein the second typical frame is also of a closed structure and adopts a butt-joint laying mode, butt-joint ports need to be staggered, the laying butt-joint ports need to avoid the installation position of a copper sleeve, vacuumizing is performed once every 5 layers are laid, air bubbles are discharged by compaction, and bag making is performed after laying is completed, and the second typical frame enters the autoclave for final curing;
the third typical frame is of a half-open structure, stacking type laying is adopted, a blanking drawing is designed into a rectangular strip to manufacture a regular rectangular frame, an arc shape is added by a post machine, every 5 layers are laid, vacuum pumping is performed once, air bubbles are compacted and discharged, bag making is performed after laying is completed, the bag is placed into the autoclave for precuring, and cold pressing is performed at the curing parameter of 80 ℃;
a male die is adopted for paving and pasting, an autoclave molding process is adopted for molding the U-shaped side wall plate, a thickness change area is formed in the partition design of the side wall plate, and the gradual change of the thickness is realized by losing layers in the layer paving design.
As a further improvement of the method, in order to increase the bonding strength of the contact surface, 2B board glue films are laid on the contact surface between the parts in the step 2.
As a further improvement of the present invention, the R-angle filling in step 4 specifically includes: and (3) utilizing the unidirectional prepreg to pave, cover and pack an adhesive film, bagging and compacting to prepare the prepreg containing the adhesive film, cutting the prepreg according to the designed width, wrapping the prepreg into a carbon fiber bundle, putting the carbon fiber bundle into a mould for mould pressing, and finally, mould pressing to obtain a relevant shape.
As a further improvement of the invention, the wrapping material in the step 5 is 5 layers of dry plain cloth, and the wrapping material needs to be cut according to a certain shape and position.
As a further improvement of the present invention, the glue injection process in step 6 specifically includes: selecting 125 ℃ solidified RTM glue injection resin, filling the resin into a glue injection tank, and connecting the resin with a glue inlet and a glue outlet between the dies; repeatedly discharging residual air in the glue tank and the mould before formal glue injection; and (3) adding 0.6MPa of pressure to the glue injection tank during glue injection to enable the resin to slowly enter the mold, observing the glue outlet, repeatedly injecting glue for 3-5 times when the resin flows out from the glue outlet, and then finishing the glue injection.
As a further improvement of the invention, in the step 7, the inner cavity of the die is connected with a thermocouple, the curing temperature is 125 ℃, and the curing time is 3 hours.
Drawings
FIG. 1 is a schematic structural view of the present invention.
FIG. 2 is a schematic view of the partition structure of the present invention.
Wherein 1 a first typical frame, 2 a second typical frame, 3 a third typical frame, 4 side panel walls, 5R corners.
Detailed Description
A method of forming a lattice-structured composite material member as shown in the drawings, comprising the steps of:
step 1: the grid structure is formed in a partition mode, a plurality of frames and the side wall plates 4 are formed independently through an autoclave process respectively, the frames comprise 6 closed character-returning frames and 1C-shaped frame, the 6 closed character-returning frames comprise 5 first typical frames 1 and 1 second typical frame 2, the C-shaped frame is a third typical frame 3, and the side wall plates 4 are U-shaped side wall plates. The grid structure partition molding specifically comprises: the manufacturing method comprises the steps of manufacturing by adopting a vacuum bag autoclave preforming process, prefabricating a first typical frame 1 by using a unidirectional prepreg according to a design laying sequence, wherein the first typical frame 1 is of a closed structure and adopts a butt-joint laying mode, a butt-joint port needs to be staggered, vacuumizing is performed once every 5 layers of laying, air bubbles are discharged by compaction, and bag making is carried out and is finally cured in an autoclave;
the manufacturing method comprises the steps that a vacuum bag autoclave preforming process is adopted, a second typical frame 2 is prefabricated by using one-way prepreg according to a designed laying sequence, the second typical frame 2 is also of a closed structure, a butt joint laying mode is adopted, butt joints need to be staggered, the laying butt joints need to avoid the installation position of a copper sleeve, every 5 layers are laid, vacuum pumping is carried out once, air bubbles are compacted and discharged, and bag making is carried out after laying is finished, and the bag is put into the autoclave for final curing;
the third typical frame 3 is of a half-open structure, stacking type laying is adopted, a blanking drawing is designed into a rectangular strip to form a regular rectangular frame, the third typical frame 3 is of an arc shape, every 5 layers are laid, vacuum pumping is performed once, air bubbles are compacted and discharged, bag making is carried out after laying is completed, the bag is placed in an autoclave for precuring, and cold pressing is carried out at the curing parameter of 80 ℃;
the male die is adopted for paving and pasting, the U-shaped side wall plate 4 is molded by an autoclave molding process, a thickness change area is formed on the side wall of the side wall plate 4 during partition design, and the thickness is gradually changed by losing layers in the layer paving design.
Step 2: the frames and the side wall plates 4 are glued into a whole through a gluing tool, and 2B plate glue films are laid on contact surfaces among all parts;
and step 3: after the gluing is finished, detecting the position relation among the frames, and confirming that the size of the frames meets the requirements of a drawing;
and 4, step 4: filling an R angle 5 among the frame, the frame and the side wall plate by adopting a mould pressing process, spreading a coating film by utilizing a unidirectional prepreg, bagging and compacting to prepare the prepreg containing the coating film, cutting the prepreg according to the designed width, wrapping the prepreg into a carbon tow, putting the carbon tow into a mould for mould pressing, and finally mould pressing to obtain a relevant shape;
and 5: wrapping and connecting the plurality of frames and the side wall plates 4 together by adopting wrapping materials, wherein the wrapping materials are 5 layers of dry plain cloth, and the wrapping materials are required to be cut according to a certain shape and position;
step 6: placing the wrapped frame and the side wall plate into an RTM glue injection mold for glue injection, selecting RTM glue injection resin cured at 125 ℃, placing the resin into a glue injection tank, and connecting a glue inlet and a glue outlet between the resin and the mold; repeatedly discharging residual air in the glue tank and the mould before formal glue injection; adding 0.6MPa pressure to the glue injection tank during glue injection to enable the resin to slowly enter the mold, observing a glue outlet, repeatedly injecting glue for 3-5 times when the resin flows out from the glue outlet, and then finishing the glue injection;
and 7: placing the mold after glue injection in an oven for curing, wherein the inner cavity of the mold is connected with a thermocouple, the curing temperature is 125 ℃, and the curing time is 3 hours;
and 8: demolding to obtain the composite material member with lattice structure.
The grid structure composite material component is formed by combining an autoclave process and an RTM process, the size of a product is ensured by a mold cavity of an RTM mold, machining is basically not needed, and the size precision is high; the surface of the product is a mould attaching surface, so that the product is obviously lightened while the strength and the rigidity of the product are met, and the cost is reduced.
The present invention is not limited to the above-mentioned embodiments, and based on the technical solutions disclosed in the present invention, those skilled in the art can make some substitutions and modifications to some technical features without creative efforts according to the disclosed technical contents, and these substitutions and modifications are all within the protection scope of the present invention.
Claims (8)
1. A method of forming a lattice-structured composite material member, comprising the steps of:
step 1: forming the grid structure in a partition mode, wherein a plurality of frames and side wall plates are formed independently by adopting an autoclave process;
step 2: the frames and the side wall plates are glued into a whole through a gluing tool;
and step 3: after the gluing is finished, detecting the position relation among the frames, and confirming that the size of the frames meets the requirements of a drawing;
and 4, step 4: filling an R angle among the frame, the frame and the side wall plate by adopting a mould pressing process;
and 5: wrapping the plurality of frames and the side wall plates together by using a wrapping material;
step 6: placing the wrapped frame and the wrapped side wall plate into an RTM glue injection mold for glue injection;
and 7: placing the mould after glue injection in an oven for curing;
and 8: demolding to obtain the composite material member with lattice structure.
2. A method of forming a composite structural member having a lattice structure according to claim 1, wherein in step 1 the plurality of frames includes 6 closed loop frames and 1C-shaped frame, the 6 closed loop frames include 5 first and 1 second exemplary frames, the C-shaped frame is a third exemplary frame, and the side wall panels are U-shaped side wall panels.
3. The method for forming a lattice-structured composite material member according to claim 2, wherein the step of forming the lattice-structured composite material member in a partitioned manner specifically includes:
the manufacturing method comprises the steps of manufacturing by adopting a vacuum bag autoclave preforming process, prefabricating a first typical frame by using unidirectional prepreg according to a designed laying sequence, wherein the first typical frame is of a closed structure and adopts a butt-joint laying mode, a butt-joint port needs to be staggered, vacuumizing is performed once every 5 layers of laying, air bubbles are discharged by compaction, and bag manufacturing is performed in an autoclave and finally cured;
the manufacturing method comprises the steps of manufacturing by adopting a vacuum bag autoclave preforming process, prefabricating a second typical frame by using a unidirectional prepreg according to a designed laying sequence, wherein the second typical frame is also of a closed structure and adopts a butt-joint laying mode, butt-joint ports need to be staggered, the laying butt-joint ports need to avoid the installation position of a copper sleeve, vacuumizing is performed once every 5 layers are laid, air bubbles are discharged by compaction, and bag making is performed after laying is completed, and the second typical frame enters the autoclave for final curing;
the third typical frame is of a half-open structure, stacking type laying is adopted, a blanking drawing is designed into a rectangular strip to manufacture a regular rectangular frame, an arc shape is added by a post machine, every 5 layers are laid, vacuum pumping is performed once, air bubbles are compacted and discharged, bag making is performed after laying is completed, the bag is placed into the autoclave for precuring, and cold pressing is performed at the curing parameter of 80 ℃;
a male die is adopted for paving and pasting, an autoclave molding process is adopted for molding the U-shaped side wall plate, a thickness change area is formed in the partition design of the side wall plate, and the gradual change of the thickness is realized by losing layers in the layer paving design.
4. The method for forming a lattice structure composite material member according to claim 1, wherein 2B board glue films are laid on the contact surfaces between the components in the step 2.
5. The method for forming a lattice-structured composite material member according to claim 1, wherein the R-angle filling in step 4 specifically includes: and (3) utilizing the unidirectional prepreg to pave, cover and pack an adhesive film, bagging and compacting to prepare the prepreg containing the adhesive film, cutting the prepreg according to the designed width, wrapping the prepreg into a carbon fiber bundle, putting the carbon fiber bundle into a mould for mould pressing, and finally, mould pressing to obtain a relevant shape.
6. The method as claimed in claim 1, wherein the wrapping material in step 5 is 5 layers of dry plain cloth, and the wrapping material is cut according to a certain shape and position.
7. The method for forming a grid structure composite material member according to claim 1, wherein the glue injection process in the step 6 specifically comprises: selecting 125 ℃ solidified RTM glue injection resin, filling the resin into a glue injection tank, and connecting the resin with a glue inlet and a glue outlet between the dies; repeatedly discharging residual air in the glue tank and the mould before formal glue injection; and (3) adding 0.6MPa of pressure to the glue injection tank during glue injection to enable the resin to slowly enter the mold, observing the glue outlet, repeatedly injecting glue for 3-5 times when the resin flows out from the glue outlet, and then finishing the glue injection.
8. The method of claim 1, wherein the thermocouple is connected to the inner cavity of the mold in step 7, the curing temperature is 125 ℃, and the curing time is 3 hours.
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| CN201911307294.1A CN110948911A (en) | 2019-12-18 | 2019-12-18 | Forming method of grid structure composite material component |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN115163552A (en) * | 2022-07-20 | 2022-10-11 | 江苏航宇航空装备制造有限公司 | Carbon fiber blade root connection structure |
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