CN113829648A - RTM (resin transfer molding) method for composite material blade - Google Patents
RTM (resin transfer molding) method for composite material blade Download PDFInfo
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- CN113829648A CN113829648A CN202110987002.4A CN202110987002A CN113829648A CN 113829648 A CN113829648 A CN 113829648A CN 202110987002 A CN202110987002 A CN 202110987002A CN 113829648 A CN113829648 A CN 113829648A
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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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/84—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks by moulding material on preformed parts to be joined
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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
- B29C70/68—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts by incorporating or moulding on preformed parts, e.g. inserts or layers, e.g. foam blocks
- B29C70/681—Component parts, details or accessories; Auxiliary operations
- B29C70/683—Pretreatment of the preformed part, e.g. insert
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29L—INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES
- B29L2031/00—Other particular articles
- B29L2031/08—Blades for rotors, stators, fans, turbines or the like, e.g. screw propellers
- B29L2031/082—Blades, e.g. for helicopters
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/70—Wind energy
- Y02E10/72—Wind turbines with rotation axis in wind direction
Abstract
The invention relates to a RTM (resin transfer molding) method of a composite blade, which adopts the principle of a composite vacuum assisted infiltration technology (namely a composite VARI technology), namely, a shaping agent is uniformly absorbed into a dry fan blade preform blank in a vacuum absorption mode, and then a diluent solvent in the shaping agent is volatilized under the conditions of vacuum action and proper temperature to obtain a pre-shaped blade preform blank, so that only uniformly distributed low-content resin is left in the fan blade preform blank, and the shaping effect is achieved without solvent foreign matters; and then twisting and cutting the preformed blade preform blank to obtain an accurate preform, and then placing the precise preform into a mold RTM (resin transfer molding) for molding, so that the fluffing and deformation phenomena of the dry fiber preform in the twisting and cutting processes are avoided, and the RTM molding quality of the woven composite material blade is obviously improved.
Description
Technical Field
The invention relates to the technical field of resin-based composite material liquid molding, in particular to an RTM (resin transfer molding) method for a composite material blade.
Background
The carbon fiber reinforced resin matrix composite material has the unique advantages of light weight, high specific strength, high specific modulus, good fatigue fracture resistance, corrosion resistance, convenience for large-area integral forming and the like, is widely applied to aviation aircrafts and engine structures, becomes a key material of aviation equipment, and the using amount of the carbon fiber reinforced resin matrix composite material also becomes one of the advanced marks of the aviation equipment. The composite material blade is a composite material part with high precision requirement widely applied to an aeroengine, directly influences the aerodynamic performance and noise index of the engine, simultaneously needs to bear huge centrifugal force generated by high-speed rotation, aerodynamic force generated by high-speed airflow, fatigue load generated by blade vibration, impact of foreign objects such as sand stones, birds and the like, and has extremely high requirements on material performance, forming quality and forming precision.
Resin Transfer Molding (RTM) is a liquid Molding composite material manufacturing technique that has been widely used in the fields of aviation and aerospace in recent years. The principle is that a dry fiber preformed body designed according to performance and structure requirements is laid in a rigid mold cavity, resin is heated to a set injection temperature in a specific pressure-resistant container, namely a resin storage tank, then low-viscosity resin is injected into the mold cavity by adopting injection equipment, so that the resin and the fiber are fully infiltrated, the temperature is raised and the resin is cured according to the process specification of the resin, and finally a composite material part with the same shape as the mold cavity is obtained. Due to the high-precision forming advantage of the RTM forming technology, the RTM forming technology is widely applied to composite material parts with special-shaped complex structures, particularly composite material blades of engines.
The prefabricated body is an intermediate of a composite material part before being molded by adopting an RTM technology, the precision of the prefabricated body determines the final molding quality of a molded composite material component, and the composite material blade of the engine has higher impact resistance requirement, so that the prefabricated body needs to be molded by adopting a 2.5D/3D woven structure. However, the 2.5D/3D woven preform integrally woven and formed by carbon fibers is formed by interweaving thousands of carbon fiber yarns, the internal structure of the preform cannot be compact, the thickness of the preform is thicker than the theoretical thickness, and particularly for the engine composite material blade with large thickness, the thickness change can be changed from 1.5mm to 60mm, and the shape is complex.
The forming process flow of the woven composite material fan blade comprises weaving a woven blade preform in a flattened state, twisting and cutting the preform, positioning a preform mold, forming and closing the mold, injecting by an RTM (resin transfer molding) process, curing and demolding. Among them, a method of positioning a preform in a mold is disclosed. The twisting and trimming processes of the preform are finished after the preform is woven and before RTM curing molding. Because the woven blade preform is woven by dry fibers and is in a flexible state before forming, the deformation phenomenon is easy to occur in the processes of carrying, twisting, edge cutting and die assembly, so that the structure of the formed part is deformed; in addition, the dry fibers are easy to rub, fluff and break, so that the phenomenon is more obvious in the edge cutting process of the prefabricated body, edge fiber fluffing is easy to generate, and local surface layer fiber breakage can be caused in serious cases; or the cut chopped fibers enter the interior of the preform to generate the phenomenon that foreign matters pollute the preform. If the defects are not overcome, the quality of the woven composite material blade formed by RTM is unstable, and the requirements of high quality and high consistency of engine parts cannot be met.
Accordingly, the inventors provide a method of improving the yield of RTM-molded composite blades.
Disclosure of Invention
(1) Technical problem to be solved
The embodiment of the invention provides a RTM (resin transfer molding) method for a composite material blade, which solves the technical problems that the woven composite material blade formed by RTM in the prior art is unstable in quality and cannot meet the requirements of high quality and high consistency of engine parts.
(2) Technical scheme
The embodiment of the invention provides an RTM (resin transfer molding) method for a composite material blade, wherein the composite material blade comprises a tenon and a blade body, and the RTM method at least comprises the following steps of S110-S170:
step S110, installing the dry-state blade preform blank in a flattened state on a blank shaping template, placing a rubber inlet pipe at the position of the tenon, placing a rubber outlet pipe at the position of the blade body, and then packaging a vacuum bag to form a closed system.
And step S120, placing the closed system in an oven for vacuumizing, sucking the sizing agent into the blade preform blank through the rubber inlet pipe by adopting a vacuum assisted resin permeation method, and closing the vacuum after the redundant sizing agent is discharged out of the closed system through the rubber outlet pipe.
And step S130, heating the closed system, keeping the temperature for 30min to 1h, and continuously vacuumizing for 5min to 10 min.
And step S140, cooling the closed system, removing the vacuum bag, and taking down the preformed blade preform blank from the blank forming template.
S150, placing the blade preform blank after the pre-shaping on a torsional deformation platform, heating and softening the blade preform blank through a heating device arranged in the torsional deformation platform, and slowly compressing to obtain a twisted blade preform blank;
and step S160, cooling the torsional deformation platform, and performing edge cutting treatment on the twisted blade preform blank to obtain a twisted blade preform with a near net size.
And S170, placing the blade preform obtained in the step S160 into a forming die, and performing injection molding on the blade preform by adopting a resin and RTM (resin transfer molding) process to obtain the composite material blade.
Further, the blade preform blank is a blank preform of the composite material blade before RTM forming, and is woven and formed in a weaving mode.
Furthermore, a first sealing groove is formed between the die body and the side die.
Further, in the step S110, the profile of the blank sizing template is processed by using the profile of the lower surface of the blade preform in the state of the blank being flattened.
Further, in the step S120, the setting agent is obtained by diluting with a resin [50] and a solvent at a dilution ratio of 1: 20-1: 50, the solvent is a low-boiling point acetone or ethanol solvent, and the resin used in the setting agent is consistent with the resin system used in the step S170.
Further, in the step S120, the vacuum degree of the sizing agent sucked into the blade preform blank through the vacuum inlet tube by using the vacuum assisted resin infiltration method is-0.02 MPa to-0.05 MPa.
Further, in step S150, the torsional deformation platform includes an upper mold half and a lower mold half, and a profile of the upper mold half and the profile of the lower mold half are respectively consistent with a suction surface and a pressure surface of the molded composite blade.
Further, the upper mold half is designed in a block manner, in the step S150, the block of the upper mold half is matched with the lower mold half, and the regional torsional deformation control is performed on the blade preform blank pre-shaped in the step S140.
(3) Advantageous effects
1. The dry blade preform is pre-shaped, so that the dry blade preform has certain stiffness, the internal structure is stable, the deformation phenomenon of the blade preform in the processes of carrying, twisting, edge cutting and die assembly is avoided, and the friction fluffing and fracture phenomenon of dry fibers in the process of edge cutting of the preform can be prevented.
2. The content of the sizing agent adopted by the invention is low (2-5%), and the sizing agent is consistent with a resin system adopted during injection, so that the permeation of the resin to a prefabricated body is not hindered, and the problem of inconsistent compatibility between the resin and the sizing agent system during resin injection and curing is solved;
3. the special blank shaping template for the prefabricated body can maintain the step-shaped thickness form of the blade prefabricated body blank, the phenomenon that the molded surface of the prefabricated body changes in the pre-shaping process can not occur, and the consistency of the form of the blade prefabricated body blank can be kept;
4. the torsional deformation platform adopted by the invention can be in a split form, so that the controllability of the torsional deformation process of the prefabricated body is high, and the consistency is good;
5. the invention is simple to implement, does not need to carry out large-scale transformation on the prior RTM process equipment and the prior mould, and has good RTM process universality;
in conclusion, the invention provides the RTM forming method of the composite material blade, which is a method for carrying out resin impregnation presetting on a dry woven preform of the composite material blade, then twisting and cutting to obtain an accurate preform, and then placing the preform into a mold for RTM forming, so that the fluffing and deformation phenomena of the dry fiber preform in the twisting and cutting processes are avoided, and the RTM forming quality of the woven composite material blade is obviously improved.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings needed to be used in the embodiments of the present invention will be briefly described below, and it is obvious that the drawings described below are only some embodiments of the present invention, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a schematic illustration of a composite blade preform blank in an embodiment of the invention;
FIG. 2 is a schematic view of a predetermined closed system of a blade preform blank in an embodiment of the invention;
FIG. 3 is a schematic view of a torsional deformation scenario of a blade preform blank in an embodiment of the present invention;
FIG. 4 is a schematic view of a near net-size blade preform after torsional deformation trimming in an embodiment of the present invention;
FIG. 5 is a schematic view of a composite blade after RTM molding in an embodiment of the present invention.
In the figure:
1-a blade preform blank; 1 a-pre-shaping a blade preform blank; 1 b-twisting the blade prefabricated body blank; 1 c-a near net size twisted blade preform; 2-tenon; 3-leaf body; 3-outer forming die; 4-feeding rubber tube; 5-rubber outlet pipe; 6-blank shaping template; 7-a shaping agent; 8-a closed system; 30-a torsional deformation platform; 31-upper template; 32-a lower template; 10-composite blade.
Detailed Description
The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following detailed description of the embodiments and the accompanying drawings are provided to illustrate the principles of the invention and are not intended to limit the scope of the invention, i.e., the invention is not limited to the embodiments described, but covers any modifications, alterations, and improvements in the parts, components, and modes of operation without departing from the spirit of the invention.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present application will be described in detail below with reference to the embodiments with reference to the attached drawings.
Referring to fig. 1 to 5, the present invention provides an RTM forming method for a composite blade, which relates to a forming mold, a blade preform blank 1, and a formed composite blade 10, wherein the composite blade 10 includes a tenon 2 and a blade body 3, and the forming method includes the following steps S110 to S170:
step S110, installing the dry-state blade prefabricated body blank 1 in a flattened state on a blank shaping template 6, placing a rubber inlet pipe 4 at the position of the tenon 2, placing a rubber outlet pipe 5 at the position of the blade body 3, and then packaging a vacuum bag to form a closed system 8.
In this step, the blade preform blank 1 is a blank preform of the composite material blade before RTM molding, and is woven and molded by a weaving method. The profile of the blank shaping template 6 is processed by adopting the lower surface profile of the blade prefabricated body blank 1 in a flattening state.
And S120, putting the closed system in an oven for vacuumizing, wherein the vacuum degree is-0.02 MPa to-0.05 MPa, sucking the sizing agent 7 into the blade preform blank 1 through the rubber inlet pipe 4 by adopting a vacuum assisted resin infiltration method, and closing the vacuum after the redundant sizing agent 7 is discharged out of the closed system 8 through the rubber outlet pipe 5.
In the step, the setting agent 7 is obtained by diluting resin and a solvent in a dilution ratio of 1: 20-1: 50, the solvent is a low-boiling point acetone or ethanol solvent, and the resin used for the setting agent 7 is consistent with the resin system used in the injection in the step S170.
And step S130, heating the closed system 8, keeping the temperature for 30 min-1 h, and continuously vacuumizing for 5 min-10 min.
Step S140, cooling the closed system 8, removing the vacuum bag, and removing the pre-shaped blade preform blank 1a from the blank shaping mold 6.
Step S150, the blade preform blank 1a after the pre-shaping is placed on the torsional deformation platform 30, the blade preform blank 1a is heated and softened by a heating device arranged in the torsional deformation platform 30, and then is slowly compressed, so that the twisted blade preform blank 1b is obtained.
In this step, the torsional deforming platform 30 comprises an upper mold half 31 and a lower mold half 32, the profiles of the upper mold half 31 and the lower mold half 32 respectively corresponding to the suction surface and the pressure surface of the molded composite blade 10.
As an alternative embodiment, the upper mold half 31 is designed as a block, and in step S150, the block of the upper mold half 31 is matched with the lower mold half 32 to perform the regional torsional deformation control on the blade preform blank 1a pre-shaped in step S140.
And step S160, cooling the torsional deformation platform 30 to harden the twisted blade preform blank 1b, and then performing edge cutting processing on the twisted blade preform blank 1b to obtain a twisted blade preform 1c with a near net size.
And S170, placing the blade preform obtained in the step S160 into a forming die, and performing injection molding on the blade preform by adopting a resin and RTM (resin transfer molding) process to obtain the composite material blade 10.
The working principle of the invention is as follows:
1. the invention adopts the principle of composite material vacuum assisted infiltration technology (namely composite material VARI technology), namely, a shaping agent is uniformly absorbed into a dry fan blade preform in a vacuum absorption mode, and then a diluent solvent in the shaping agent is volatilized under the conditions of vacuum action and proper temperature, so that only uniformly distributed low-content resin is left in the fan blade preform, thereby achieving the shaping effect and not leaving solvent foreign matters;
2. the invention adopts the lower surface profile of the blade preform blank in a flattening state to process the profile of the blank shaping template, and the principle is to ensure that the profile is consistent with the design state in the blade preform presetting process and prevent the preform from deforming under the combined action of vacuum pressure and a contact template;
3. the invention adopts the condition of lower vacuum degree (-0.02MPa to-0.05 MPa) to adsorb the shaping agent, so as to prevent the dry-state fan blade preform from generating compression deformation under higher vacuum pressure, and the lower vacuum degree can not only realize the adsorption of the shaping agent to the blade preform, but also can not generate the compression deformation of the preform;
4. the principle of the invention that the heating split type torsional deformation platform is adopted to carry out torsional deformation on the pre-set blade prefabricated body is that the prefabricated body is softened by heating and can be extruded and deformed by the molded surfaces of an upper die and a lower die, and the upper die adopts a split pressing block mode so as to meet the difference of inconsistent compression strokes of blade areas with different thicknesses; after the torsional deformation is finished, the softened blade prefabricated body is hardened again through cooling, and the purpose of maintaining the shape before and in the process of die filling is achieved.
The following is illustrated by specific example 1:
the blade preform blank 1 is a variable-thickness 2.5D woven structure fan blade preform made of CCF800, and the fiber volume content of the material is 58% +/-3%; the CCF800 is a T800-grade carbon fiber fabric with the specification of 12K, which is an expanded product of the Shandong Weihai, the resin for injection adopts ACTECH1304 high-toughness liquid molding resin of China aviation composite material, the external dimension of the blade preform 10 is 780mm multiplied by 320mm (length multiplied by width), and the specific molding method comprises the following steps:
step S110, processing the special rubber tube 6, wherein the molded surface of the blank shaping template 6 is processed by adopting the lower surface molded surface of the blade prefabricated body blank 1 in a flattening state, and the template is made of Q235 steel. Then, the blade prefabricated body blank 1 in a flattened state is placed on a special blank shaping template 6, a rubber inlet pipe 4 is placed at the position of the tenon 2, a rubber outlet pipe 5 is placed at the position of the blade body 3, the rubber inlet pipe 4 is connected with a liquid storage tank filled with a shaping agent 7, the rubber outlet pipe 5 is connected with a vacuum system, and then a vacuum bag is packaged to form a closed system 8;
step S120, preparing the fixing agent 7 according to the ratio of the resin to the solvent of 1:30, wherein the solvent is acetone, and pouring the prepared fixing agent 7 into a liquid storage tank. Vacuumizing the closed system 8 in an oven, maintaining the vacuum degree of the system between-0.04 MPa and-0.05 MPa, opening the rubber inlet pipe 4 to enable the sizing agent 7 to be sucked into the blade preform blank 1 through the rubber inlet pipe 4 under the action of vacuum, fully infiltrating the blade preform blank 1 by the to-be-sized 7, discharging the redundant sizing agent 7 out of the closed system 8 through the rubber outlet pipe 5, and then closing the vacuum of the system.
Step S130, heating the closed system 8 to 100 ℃, preserving heat for 45min, and then vacuumizing for 5min to remove the solvent;
step S140, cooling the closed system 8 to room temperature, removing the vacuum bag, and taking down the pre-shaped blade preform blank 1a from the blank shaping template 60;
step S150, placing the blade preform blank 1a after presetting on a torsional deformation platform 30, heating the blade preform blank 1a to 90 ℃ through a heating device arranged in the torsional deformation platform 30 to soften the blade preform blank, and slowly pressing the blade preform blank 1a after presetting in different areas to obtain a blade preform blank 1b after torsion;
step S160, cooling the torsional deformation platform 30 to room temperature to harden the twisted blade preform blank 1b, and then performing edge cutting processing on the twisted blade preform blank 1b to obtain a twisted blade preform 1c with a near net size;
step S170, the blade preform 1c is placed into a forming die, and the blade preform 1c is subjected to injection molding by adopting the resin ACTECH1304 and RTM processes to obtain the composite material blade 10.
The appearance quality and the internal quality of the molded composite material blade 10 are detected, and both the appearance quality and the internal quality meet the design requirements.
The above description is only an example of the present application and is not limited to the present application. Various modifications and alterations to this application will become apparent to those skilled in the art without departing from the scope of this invention. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present application should be included in the scope of the claims of the present application.
Claims (7)
1. A RTM forming method for a composite material blade comprises a tenon and a blade body, and is characterized by comprising the following steps:
step S110, installing the dry-state blade prefabricated body blank in a flattened state on a blank shaping template, placing a rubber inlet pipe at the position of a tenon, placing a rubber outlet pipe at the position of a blade body, and then packaging a vacuum bag to form a closed system;
step S120, placing the closed system in an oven for vacuumizing treatment, sucking a sizing agent into the blade preform blank through the rubber inlet pipe in a vacuum manner by adopting a vacuum assisted resin permeation method, and closing the vacuum after the redundant sizing agent is discharged out of the closed system through the rubber outlet pipe;
step S130, heating the closed system, keeping the temperature for 30min to 1h, and continuously vacuumizing for 5min to 10 min;
step S140, cooling the closed system, removing the vacuum bag, and taking down the preformed blade preform blank from the blank forming template;
s150, placing the blade preform blank after the pre-shaping on a torsional deformation platform, heating and softening the blade preform blank through a heating device arranged in the torsional deformation platform, and slowly compressing to obtain a twisted blade preform blank;
step S160, cooling the torsional deformation platform to harden the twisted blade preform blank, and performing trimming treatment on the twisted blade preform blank to obtain a twisted blade preform with a near net size;
and S170, placing the blade preform obtained in the step S160 into a forming die, and performing injection molding on the blade preform by adopting a resin and RTM (resin transfer molding) process to obtain the composite material blade.
2. The RTM method of a composite blade according to claim 1, wherein said blade preform blank is a blank preform of a composite blade before RTM, and is woven in a weaving manner.
3. The RTM method for forming a composite blade according to claim 1, wherein in step S110, the profile of the blank sizing form is machined using the lower surface profile of the blade preform blank in a flattened state.
4. The RTM forming method for the composite material blade according to claim 1, wherein in the step S120, the sizing agent is obtained by diluting a resin and a solvent at a dilution ratio of 1:20 to 1:50, the solvent is a low-boiling point acetone or ethanol solvent, and the resin used in the sizing agent is consistent with the resin system used in the injection in the step S170.
5. The RTM method for forming a composite blade according to claim 1, wherein in step S120, the vacuum degree of the sizing agent sucked into the blade preform blank through the hose by vacuum assisted resin infiltration is-0.02 MPa to-0.05 MPa.
6. The RTM method according to claim 1, wherein in step S150, the torsional deformation platform comprises an upper mold half and a lower mold half, and a profile of the upper mold half and the lower mold half respectively corresponds to a suction surface and a pressure surface of the molded composite blade.
7. The RTM method according to claim 6, wherein said upper mold half is of a split design, and in step S150, said split of said upper mold half and said lower mold half cooperate to perform a split torsional deformation control of the blade preform blank pre-shaped in step S140.
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| CN109304876A (en) * | 2018-11-16 | 2019-02-05 | 中航复合材料有限责任公司 | A kind of RTM forming method of composite material blade |
| CN111169044A (en) * | 2019-12-13 | 2020-05-19 | 中航复合材料有限责任公司 | RTM (resin transfer molding) forming die and method for composite material blade |
| CN111152483A (en) * | 2019-12-19 | 2020-05-15 | 中国航空制造技术研究院 | Forming device and method for torsion variable-thickness composite material structure |
| CN112009065A (en) * | 2020-07-31 | 2020-12-01 | 北京卫星制造厂有限公司 | Preparation method of integrated gradient structure thermal protection material |
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