CN111805946B - Method for preparing composite material by hot-pressing reinforcement - Google Patents
Method for preparing composite material by hot-pressing reinforcement Download PDFInfo
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- CN111805946B CN111805946B CN202010610775.6A CN202010610775A CN111805946B CN 111805946 B CN111805946 B CN 111805946B CN 202010610775 A CN202010610775 A CN 202010610775A CN 111805946 B CN111805946 B CN 111805946B
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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
- B29C70/74—Moulding material on a relatively small portion of the preformed part, e.g. outsert moulding
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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
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29K—INDEXING SCHEME ASSOCIATED WITH SUBCLASSES B29B, B29C OR B29D, RELATING TO MOULDING MATERIALS OR TO MATERIALS FOR MOULDS, REINFORCEMENTS, FILLERS OR PREFORMED PARTS, e.g. INSERTS
- B29K2705/00—Use of metals, their alloys or their compounds, for preformed parts, e.g. for inserts
- B29K2705/02—Aluminium
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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
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The invention relates to a method for preparing a composite material by hot-pressing reinforcement, which comprises the following steps: (1) machining the base body (4) to a design size; (2) sleeving a base body (4) on the lining plate (3), internally supporting and clamping the base body (4), and then paving a reinforcing body (5) on the outer side surface of the base body (4); (3) the outer hoop (6) is utilized to integrally hoop the base body (4) on which the reinforcement body (5) is laid, and the fastening torque of the outer hoop (6) is adjusted through bolts; (4) the high-frequency induction coil (8) is arranged on the outer side of the outer hoop (6) and is heated; (5) and cooling to room temperature, and then, finely machining the outer molded surface by taking the inner molded surface as a positioning reference to obtain the composite material. Compared with the prior art, the invention reduces the requirement of the aircraft shell on the performance of the original material of the product, and can realize the on-demand strengthening of the structural component in the product-level stage by adopting the traditional cast magnesium alloy or wrought magnesium alloy.
Description
Technical Field
The invention relates to the field of composite material manufacturing, in particular to a method for preparing a composite material by hot-pressing reinforcement.
Background
In the aerospace field, the light weight design of aircrafts, carrier rockets and missile products is pursued never, and magnesium and aluminum alloy are taken as one of the metal materials which are mature at present and have lighter density, so that the magnesium and aluminum alloy can be widely applied to important structural component products of various missile cabins, aircraft cabins and satellite platforms.
With the increasingly severe flight conditions of various new-generation aircrafts and missiles, the requirements on mechanical properties such as tensile strength, fatigue strength and the like of main structural member materials are continuously improved, and the traditional aluminum alloy material is difficult to meet the flight conditions of complex limits in some fields. At present, a commonly used solution adopts titanium alloy or other metal alloy with more excellent mechanical property, which means that a great deal of effective load of aircrafts and missile weapons is sacrificed, and the design index and task requirement of model products are difficult to meet.
The composite material is taken as a main development direction and a research hotspot of a modern novel material, and has been widely applied to the fields of aerospace, ships, traffic, energy, buildings, sports equipment and the like along with the continuous improvement of material performance and the continuous expansion of application range. The composite materials generally used at present are mainly classified into three types according to the matrix materials, namely resin matrix, metal matrix and ceramic matrix composite materials. However, metal matrix composites mainly include aluminum and titanium as matrix materials, TiB, TiC, SiC and the like as reinforcements, and composites including aluminum as a matrix material and carbon fibers as reinforcements are hardly found.
In view of the obvious difference between the product demand and the material capability, a method for preparing the composite material by hot-pressing reinforcement is urgently needed to be developed, and the lightweight design demand of the current aircraft and missile weapons under the complex and severe working conditions is met.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provide a method for preparing a composite material by hot-press strengthening, which reduces the requirement of an aircraft shell on the performance of a product raw material, and can realize the strengthening of a structural member as required at a product-level stage by adopting a traditional cast magnesium alloy or a wrought magnesium alloy.
The purpose of the invention can be realized by the following technical scheme:
the invention firstly provides a device for preparing a composite material by hot-pressing strengthening, which comprises a lining plate, an outer hoop and a high-frequency induction coil; the composite material substrate is sleeved outside the lining plate, the composite material reinforcement is laid outside the substrate, the outside hoop is arranged outside the reinforcement body, and the high-frequency induction coil is arranged outside the outside hoop. The reinforcement body is pressed into the semi-solid state matrix by applying external pressure to the outer hoop under the internal and external supporting action of the lining plate and the outer hoop and the high-frequency induction coil heating environment, and the purposes of improving the strength and tensile property of the matrix after cooling are achieved.
Furthermore, the number of the lining plates is 3-6, the gap between every two lining plates is not more than 0.1mm, and the thickness of the lining plates is not less than the difference between the radius of the core flange and the radius of the flange surface of the inner supporting ring.
Furthermore, the lining plate is internally provided with an inner supporting ring, a chuck base is arranged below the inner supporting ring, and the inner supporting ring clamps the whole inner support of the base body through the chuck base and accurately positions the base body. The chuck clamping torque is not less than 150 N.m.
Furthermore, an inner core for preventing the inner support ring from bending and deforming at high temperature is arranged above the inner support ring.
Further, the inner core is further provided with a core flange, and the core flange and the inner support ring are fastened through bolts. The inner core can prevent the inner support ring from bending and deforming under the high-temperature environment to influence the hot-pressing strengthening quality.
Furthermore, the inner diameter of the inner supporting ring is matched with the outer diameter of the inner core, and the gap between the inner supporting ring and the inner core is not more than 0.08 mm.
Further, the lining plate, the inner supporting ring or the inner core is made of Invar36 low expansion alloy.
Furthermore, the weaving type of the reinforcement is a plain weave or a woven weave, the void ratio is 45-75%, and the reinforcement comprises carbon fiber woven cloth. The number of the reinforcement body layers is laid according to the design requirement, meanwhile, a sacrificial layer must be laid on the outermost layer, and the number of the sacrificial layer is controlled to be 10-45% by the number of the total carbon fiber woven fabric layers for finish machining removal of the final product.
Further, the base body is an aluminum alloy cylinder section.
Furthermore, the number of the outer hoops is 3-6, all the outer hoops are connected through bolts, and the surface roughness of the outer hoops is lower than Ra0.4. The generation of micro-cracks on the surface of the carbon fiber is prevented. The fastening torque of the outer hoop is adjusted through bolts and is determined by the outer diameter of the base body, the number of the reinforced body layers, the type of fabric, the void ratio and the heating temperature.
The invention also provides a method for preparing the composite material by hot-pressing strengthening, which comprises the following steps:
(1) processing the substrate to a design size, wherein no allowance is reserved on the inner profile surface, and the allowance is reserved on the outer profile surface; the residual value is the sum of the outer diameter expansion amount of the extruded and plastic-flowed matrix and the thickness of the reinforced body layer sacrificial layer;
(2) sleeving a base body on the lining plate, internally supporting and clamping the base body, and then paving a reinforcing body on the outer side surface of the base body;
(3) the outer hoop is utilized to integrally hoop the substrate on which the reinforcement is laid, and the fastening torque of the outer hoop is adjusted through bolts, wherein the fastening torque is determined by the outer diameter of the substrate, the number of layers of the reinforcement, the type of fabric, the void ratio and the heating temperature;
(4) placing the high-frequency induction coil outside the outer hoop, heating to ensure that the outer surface of the matrix is in a semi-solid state, and pressing the reinforcement into the matrix in a surface semi-solid state;
(5) and cooling to room temperature, then removing the high-frequency induction coil, the outer hoop, the inner support ring and the lining plate, and then finely machining the outer profile by taking the inner profile as a positioning reference to obtain the composite material.
Further, the substrate is an aluminum alloy cylinder section; the weaving type of the reinforcement is plain weave or woven weave type, the void ratio is 45-75%, and the reinforcement comprises carbon fiber woven fabric.
Furthermore, the number of the lining plates is 3-6, and the thickness of the lining plates is not less than the difference between the radiuses of the surfaces of the core flange and the inner supporting ring flange; the number of the outer hoops is 3-6, the outer hoops are connected through bolts, and the surface roughness of the outer hoops is lower than Ra0.4.
Furthermore, the heating temperature is 550-580 ℃, and the time for pressing the reinforcement body into the surface layer semi-solid state matrix is 3-4 h.
Further, the step (2) is specifically as follows:
(2-1) splicing the lining plates;
(2-2) sleeving the substrate on the lining plate;
(2-3) inserting the inner supporting ring into the lining plate, inserting and abutting the chuck base and the inner supporting ring, clamping the whole inner support of the base body through the chuck base and accurately positioning, transforming the chuck base into a lathe three-jaw chuck, and radially expanding and clamping the clamping jaws through guide grooves of the chuck body; due to the working condition requirements of the composite shell, the reinforcing effect at the rear end of the shell is higher than that at the front end, namely, more embedding amount needs to be generated at the rear end of the shell to realize the reinforcing effect. The chuck base is mainly used for pre-adding a certain deflection to the inner supporting ring, so that a certain interference magnitude is generated at the bottom of the composite material shell, and further more embedding magnitudes are generated between the rear end of the magnesium alloy shell and the carbon fiber under the high-temperature semi-solid action, so as to meet the requirements of design indexes;
(2-4) installing an inner core in the inner supporting ring;
and (2-5) laying a reinforcing body on the outer side surface of the matrix.
Further, in the step (2-1), the gap between every two lining plates is not more than 0.1 mm; the clamping torque of the inner support clamping in the step (2-3) is 150-300 N.m.
Further, the inner diameter of the inner support ring in the step (2-4) is matched with the outer diameter of the inner core, and the gap between the inner support ring and the inner core is not more than 0.08 mm; and (3) paving a sacrificial layer on the outermost layer of the reinforcement in the step (2-5), wherein the number of the sacrificial layer is 10-45% of the total reinforcement paving number, and the sacrificial layer is used for finish machining and removing of a final product.
Further, the step (4) specifically comprises:
(4-1) placing the high-frequency induction coil outside the outer hoop for heating;
(4-2) adjusting the bolts at intervals, and checking the fastening torque of the outer hoop to enable the fastening torque to reach a required value;
(4-3) after repeating the adjustment for several times, pressing the reinforcement body into the surface layer of the semi-solid matrix.
Further, the time interval in the step (4-2) is 20-40min, and the fastening torque is maintained between 150 and 160 N.m.
Further, the number of times of the repeated adjustment in the step (4-3) is 6-8.
Compared with the prior art, the invention has the following advantages:
(1) the invention firstly provides a device for preparing a composite material by hot-pressing reinforcement, so that a matrix is pressed into the matrix in a semi-solid state by applying external pressure to an outer hoop under the internal and external supporting action of a lining plate and the outer hoop and a high-frequency induction coil heating environment, and the aims of improving the matrix strength, the tensile property and the like are fulfilled after cooling is finished;
(2) due to the working condition requirements of the composite shell, the reinforcing effect at the rear end of the shell is higher than that at the front end, namely, more embedding amount needs to be generated at the rear end of the shell to realize the reinforcing effect. The chuck base is mainly used for pre-adding a certain deflection to the inner supporting ring, so that a certain interference magnitude is generated at the bottom of the composite material shell, and further more embedding magnitudes are generated between the rear end of the magnesium alloy shell and the carbon fiber under the high-temperature semi-solid action, so as to meet the requirements of design indexes;
(3) the invention reduces the requirement of the aircraft shell on the performance of the original material of the product, and can realize the method for strengthening the structural member as required at the product level by adopting the traditional cast magnesium alloy or wrought magnesium alloy.
Drawings
FIG. 1 is a perspective view of the device of the embodiment;
FIG. 2 is a front sectional view of the device in the example;
FIG. 3 is an exploded view of the device of the example;
the reference numbers in the figures indicate: the high-frequency induction chuck comprises a chuck base 1, an inner supporting ring 2, a lining plate 3, a base body 4, a reinforcing body 5, an outer hoop 6, an inner core 7, a core flange 71 and a high-frequency induction coil 8.
Detailed Description
The invention is described in detail below with reference to the figures and the specific embodiments.
Examples
A hot-press strengthening device for preparing composite materials is shown in figures 1-3 and comprises a lining plate 3, an outer hoop 6 and a high-frequency induction coil 8; the composite material matrix 4 is sleeved outside the lining plate 3, the composite material reinforcement 5 is paved outside the matrix 4, the outer hoop 6 is arranged outside the reinforcement 5, and the high-frequency induction coil 8 is arranged outside the outer hoop 6. Under the internal and external supporting action of the lining plate 3 and the outer hoop 6 and the heating environment of the high-frequency induction coil 8, the base body 4 applies external pressure to the outer hoop 6 to press the reinforcement body 5 into the base body 4 in a semi-solid state, and the purposes of improving the strength and tensile property of the base body 4 and the like are achieved after cooling is completed.
The number of the lining plates 3 is 3, the gap between every two lining plates 3 is not more than 0.1mm, and the thickness of the lining plates 3 is not less than the difference between the radius of the flange surface of the core flange 71 and the radius of the flange surface of the inner supporting ring 2. Be equipped with interior vaulting ring 2 in the welt 3, this interior vaulting ring 2 below is equipped with chuck base 1, and this chuck base 1 alternates the butt with interior vaulting ring 2. The inner support ring 2 is used for internally supporting and clamping the whole base body 4 through the chuck base 1 and accurately positioning the base body. The chuck clamping torque is not less than 150 N.m. Due to the working condition requirements of the composite shell, the reinforcing effect at the rear end of the shell is higher than that at the front end, namely, more embedding amount needs to be generated at the rear end of the shell to realize the reinforcing effect. The chuck base 1 is mainly used for pre-adding a certain amount of deflection to the inner support ring 2, so that a certain magnitude of interference is generated at the bottom of the composite material shell, and further more embedding amount is generated between the rear end of the magnesium alloy shell and the carbon fiber under the action of high-temperature semi-solid state, so as to meet the requirement of design indexes. An inner core 7 for preventing the inner support ring 2 from bending and deforming at high temperature is also arranged in the inner support ring 2. The inner core 7 is also provided with a core flange 71, and the core flange 71 is fastened with the inner support ring 2 through bolts. The inner core 7 can prevent the inner support ring 2 from bending and deforming under a high-temperature environment to influence the hot-pressing strengthening quality. The inner diameter of the inner support ring 2 is matched with the outer diameter of the inner core 7, and the gap between the inner support ring 2 and the inner core 7 is not more than 0.08 mm. The material of the liner plate 3, the inner support ring 2 or the inner core 7 is Invar36 low expansion alloy.
The number of the outside hoops 6 is 3, the outside hoops 6 are connected through bolts, and the surface roughness of the outside hoops 6 is lower than Ra0.4. Preventing the generation of micro cracks on the surface of the carbon fiber. The fastening torque of the outer hoop 6 is adjusted through bolts and is determined by the outer diameter of the base 4, the number of layers of the reinforcement 5, the type of fabric, the void ratio and the heating temperature.
The weaving type of the reinforcement 5 of the embodiment is a carbon fiber layer, specifically a T800 carbon fiber cloth, the structure is a plain weave fabric, the void ratio is 55%, the number of the layers is 12, and the number of sacrificial layers is 3, and the reinforcement is used for finishing the final productAnd (6) processing and removing. The base 4 is a ZM5 cast aluminum alloy cylinder section with the outer diameter
Inner diameter
Total height 530mm, inner diameter of flange face
A method for preparing a composite material by hot-press strengthening, which comprises the following steps:
(1) processing the aluminum alloy cylinder section casting blank to a semi-precise state, processing the inner profile without remaining allowance, and processing to a design size; the allowance is reserved on the outer surface, the allowance of 0.8mm is reserved on a single side, the roundness of the outer circle is superior to 0.05mm, the surface smoothness is superior to Ra0.8, and inclusions, cracks and holes are not allowed to appear;
(2-1) splicing lining plates 3 processed by 6 pieces of Invar36 low-expansion alloy, wherein the gap between every two lining plates 3 is not more than 0.1mm, and the thickness is 20 mm;
(2-2) mounting a lining plate 3 which is accurately shaped on the inner side surface of the aluminum alloy cylinder section 4;
(2-3) inserting the inner support ring 2 into the lining plate 3, inserting the chuck base 1 and the inner support ring 2 into the lining plate to be abutted, integrally and internally supporting and clamping the aluminum alloy cylinder section 4 by the inner support ring 2 through the chuck base 1, and accurately positioning the aluminum alloy cylinder section, wherein the chuck clamping torque is 150 N.m;
(2-4) installing an inner core 7 in the inner support ring 2, wherein the inner diameter of the inner support ring 2 is matched with the outer diameter of the inner core 7, the gap between the inner diameter of the inner support ring 2 and the outer diameter of the inner core 7 is not more than 0.08mm, and the inner core 7 and the inner support ring 2 are fastened through bolts;
(2-5) winding carbon fiber woven fabric 5 on the outer side surface of the aluminum alloy cylinder section 4 according to design requirements, wherein the weaving type is plain weave, the void ratio is 55%, the number of carbon fiber total layers is 15, the flange surfaces are exposed at two ends of the carbon fiber total layers by 2-3mm, and the carbon fiber is not allowed to have defects of fracture, bundling and the like;
(3) utilize 3 outside staple bolts 6 with 4 whole staple bolts of aluminum alloy section of thick bamboo section, the interior profile of outside staple bolt 6 is weaved 5 direct contact with carbon fiber, requires outside staple bolt6 inner profile surface roughness lower than Ra0.4 and inner profile diameter
The fastening torque of the outer hoop 6 is adjusted through bolts, and is determined by the outer diameter of the base 4, the number of layers of the reinforcement 5, the type of fabric, the void ratio and the heating temperature;
(4-1) placing the high-frequency induction coil 8 outside the outer hoop 6, and integrally heating to 560 +/-10 ℃ to ensure that the outer surface of the aluminum alloy cylinder section 4 is in a semi-solid state;
(4-2) working time is 3 hours at rated temperature, wherein bolts are adjusted every 30min to check whether the fastening torque of the outer hoop 6 is a process requirement value (150- & lt300 & gtN & m);
(4-3) pressing the carbon fiber woven fabric 5 into the surface layer semi-solid state aluminum alloy cylinder section 4 under the pressure action of the outer hoop 6.
(5) And (3) after air cooling to room temperature, sequentially removing the high-frequency induction coil 8, the outer hoop 6, the inner support ring 2 and the lining plate 3, taking the inner molded surface as a positioning reference, and finely processing the outer molded surface to obtain the composite material, wherein the allowance of the outer molded surface is 0.8 mm.
Claims (9)
1. A method for preparing a composite material by hot-press strengthening is characterized by comprising the following steps:
(1) processing the substrate (4) to a design size, wherein no allowance is reserved on the inner profile surface, and the allowance is reserved on the outer profile surface;
(2) sleeving a base body (4) on a lining plate (3), internally supporting and clamping the base body (4), and then paving a reinforcing body (5) on the outer side surface of the base body (4), wherein the method comprises the following specific steps:
(2-1) splicing the lining plates (3);
(2-2) sleeving the substrate (4) on the lining plate (3);
(2-3) inserting the inner support ring (2) into the lining plate (3), inserting the chuck base (1) and the inner support ring (2) in a penetrating and abutting mode, and integrally and internally supporting and clamping the base body (4) through the chuck base (1) and accurately positioning;
(2-4) installing an inner core (7) in the inner supporting ring (2);
(2-5) paving a reinforcement body (5) on the outer side surface of the substrate (4);
(3) the outer hoop (6) is utilized to integrally hoop the base body (4) on which the reinforcement body (5) is laid, and the fastening torque of the outer hoop (6) is adjusted through bolts;
(4) placing a high-frequency induction coil (8) at the outer side of the outer hoop (6), and heating to press the reinforcement (5) into the surface layer of the semi-solid state matrix (4);
(5) and cooling to room temperature, then removing the high-frequency induction coil (8), the outer hoop (6), the inner supporting ring (2) and the lining plate (3), and then finely machining the outer profile by taking the inner profile as a positioning reference to obtain the composite material.
2. The method for preparing the composite material by hot press strengthening according to claim 1, wherein the substrate (4) is an aluminum alloy cylinder section; the weaving type of the reinforcement (5) is plain weave or woven weave, the void ratio is 45-75%, and the reinforcement comprises carbon fiber woven fabric.
3. The method for preparing the composite material by hot press strengthening according to claim 1, wherein the number of the lining boards (3) is 3-6; the number of the outer hoops (6) is 3-6, the outer hoops (6) are connected through bolts, and the surface roughness of the outer hoops (6) is lower than Ra0.4.
4. The method for preparing a composite material by hot press strengthening as claimed in claim 1, wherein the heating temperature is 550 ℃ and 580 ℃, and the time required for pressing the reinforcement (5) into the surface layer of the matrix (4) in the semi-solid state is 3-4 h.
5. The method for preparing the composite material by hot press strengthening according to claim 1, wherein in the step (2-1), the gaps between the lining plates (3) are not more than 0.1 mm; the clamping torque of the inner support clamping in the step (2-3) is 150-300 N.m.
6. The method for preparing the composite material by hot press strengthening according to claim 1, wherein the inner diameter of the inner support ring (2) in the step (2-4) is matched with the outer diameter of the inner core (7), and the gap between the inner support ring (2) and the inner core (7) is not more than 0.08 mm; and (3) paving a sacrificial layer on the outermost layer of the reinforcement (5) in the step (2-5), wherein the quantity of the sacrificial layer is 10-45% of the total quantity of the layers of the reinforcement (5).
7. The method for preparing the composite material by hot press strengthening according to claim 1, wherein the step (4) is specifically as follows:
(4-1) placing a high-frequency induction coil (8) outside the outer hoop (6) for heating;
(4-2) adjusting the bolts at intervals, and checking the fastening torque of the outer hoop (6) to enable the fastening torque to reach a required value;
(4-3) after repeated adjustment for several times, the reinforcement (5) is pressed into the surface layer semisolid state matrix (4).
8. The method for preparing a composite material by hot press strengthening as claimed in claim 7, wherein the time interval in step (4-2) is 20-40min, and the fastening torque is maintained between 150-160N · m.
9. The method for preparing a composite material by hot press strengthening according to claim 7, wherein the number of times of the repeated adjustment in the step (4-3) is 6-8 times.
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| CN110696388A (en) * | 2019-10-24 | 2020-01-17 | 王明明 | High-pressure gas tank forming device made of polymer-based carbon fiber composite material |
| CN111070719A (en) * | 2018-10-22 | 2020-04-28 | 空中客车德国运营有限责任公司 | Reinforcing element for a structural profile, structural device, aircraft or aerospace vehicle and method for producing a structural device |
| CN111219432A (en) * | 2020-01-13 | 2020-06-02 | 广德固特力制动材料有限公司 | Friction plate of speed reducer of railway switch machine and production method thereof |
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2020
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111070719A (en) * | 2018-10-22 | 2020-04-28 | 空中客车德国运营有限责任公司 | Reinforcing element for a structural profile, structural device, aircraft or aerospace vehicle and method for producing a structural device |
| CN109367070A (en) * | 2018-11-28 | 2019-02-22 | 山东泰氏新材料科技有限责任公司 | A kind of vacuum perfusion process producing composite material support roller |
| CN110281542A (en) * | 2019-06-17 | 2019-09-27 | 中广核核电运营有限公司 | Have the pressure vessel and its manufacturing method of anti-ionising radiation |
| CN110696388A (en) * | 2019-10-24 | 2020-01-17 | 王明明 | High-pressure gas tank forming device made of polymer-based carbon fiber composite material |
| CN111219432A (en) * | 2020-01-13 | 2020-06-02 | 广德固特力制动材料有限公司 | Friction plate of speed reducer of railway switch machine and production method thereof |
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