CN111365143A - Carbon fiber composite material storage tank bracket and manufacturing method thereof - Google Patents
Carbon fiber composite material storage tank bracket and manufacturing method thereof Download PDFInfo
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- CN111365143A CN111365143A CN202010314083.7A CN202010314083A CN111365143A CN 111365143 A CN111365143 A CN 111365143A CN 202010314083 A CN202010314083 A CN 202010314083A CN 111365143 A CN111365143 A CN 111365143A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K9/00—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof
- F02K9/42—Rocket-engine plants, i.e. plants carrying both fuel and oxidant therefor; Control thereof using liquid or gaseous propellants
- F02K9/60—Constructional parts; Details not otherwise provided for
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
- B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
- B29B15/122—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex
- B29B15/125—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length with a matrix in liquid form, e.g. as melt, solution or latex by dipping
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29B—PREPARATION OR PRETREATMENT OF THE MATERIAL TO BE SHAPED; MAKING GRANULES OR PREFORMS; RECOVERY OF PLASTICS OR OTHER CONSTITUENTS OF WASTE MATERIAL CONTAINING PLASTICS
- B29B15/00—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00
- B29B15/08—Pretreatment of the material to be shaped, not covered by groups B29B7/00 - B29B13/00 of reinforcements or fillers
- B29B15/10—Coating or impregnating independently of the moulding or shaping step
- B29B15/12—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length
- B29B15/14—Coating or impregnating independently of the moulding or shaping step of reinforcements of indefinite length of filaments or wires
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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
- B29C70/30—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
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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
- B29C70/30—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
- B29C70/38—Automated lay-up, e.g. using robots, laying filaments according to predetermined patterns
-
- 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
-
- 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
- B29L2031/30—Vehicles, e.g. ships or aircraft, or body parts thereof
- B29L2031/3097—Cosmonautical vehicles; Rockets
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Robotics (AREA)
- Combustion & Propulsion (AREA)
- General Engineering & Computer Science (AREA)
- Reinforced Plastic Materials (AREA)
Abstract
A carbon fiber composite material storage tank bracket and a manufacturing method thereof relate to the technical field of aerospace craft structures. The invention solves the problem that the existing carrier rocket tank bracket adopts a metal tank bracket and cannot meet the requirements of high performance and light weight of spaceflight. The carbon fiber composite material storage tank bracket comprises a storage tank bracket shell and two metal support lugs, wherein a left rib plate, a right rib plate and a web plate are sequentially connected end to form a storage tank bracket frame body; the forming method for manufacturing the carbon fiber composite material storage tank bracket is realized by the following steps of firstly, rechecking a prepreg; step two, blanking prepreg; step three, preparing a forming die; step four, laying prepreg; step five, die assembly; step six, curing; and step seven, demolding and finishing. The method is used for manufacturing the carbon fiber composite material storage tank bracket.
Description
Technical Field
The invention relates to the technical field of aerospace craft structures, in particular to a carbon fiber composite material storage box support and a manufacturing method thereof.
Background
The composite material is a material basis of high-performance products and is an important guarantee for realizing advanced design concepts and technologies. High performance composites have been successfully used in a number of national areas of emphasis due to their structural advantages of being lightweight and strong. A storage tank support matched with a power system currently adopts a metal engine and a storage tank support, and cannot meet the requirements of high performance and light weight of spaceflight. The carbon fiber composite material storage tank bracket is used for researching the design and series key technologies of the carrier rocket storage tank bracket, and a precedent that aerospace bracket products are formed by adopting composite materials does not exist in China. The high-performance and light-weight carrier rocket is an upgrading and updating project of the carrier rocket in China, has multiple innovation difficulties, large technical span and high complexity, and represents the highest level of the carrier rocket in China. The composite material support product has high structural efficiency and good reliability, completely meets the requirements of high performance and light weight of aerospace, ensures the smooth operation of series models, and promotes the application of the carbon fiber composite material series support in the aspect of aerospace.
In conclusion, the conventional carrier rocket tank bracket adopts a metal tank bracket, and the problems that the requirements of high performance and light weight of spaceflight cannot be met exist.
Disclosure of Invention
The invention aims to solve the problem that the existing carrier rocket tank bracket adopts a metal tank bracket and cannot meet the requirements of high performance and light weight of spaceflight, and further provides a carbon fiber composite tank bracket and a manufacturing method thereof.
The technical scheme of the invention is as follows:
a carbon fiber composite material storage tank support comprises a storage tank support shell and two metal support lugs 5, wherein the storage tank support shell comprises a left rib plate 1, a right rib plate 2, a web plate 3 and a reinforcing plate 4, the web plate 3 is horizontally arranged, a circular arc-shaped groove 31 matched with the excircle of a storage tank is arranged in the middle of the upper end face of the web plate 3, two metal support lugs 5 are respectively arranged on two sides of the upper end face of the web plate 3, a steel belt connecting hole 51 is formed in each metal support lug 5, the right rib plate 2 is vertically arranged on the lower portion of the right side of the web plate 3, the upper end of the right rib plate 2 is connected with the right end of the web plate 3, the left rib plate 1 is obliquely arranged between the web plate 3 and the right rib plate 2, the upper end of the left rib plate 1 is connected with the left end of the web plate 3, the lower end of the left rib plate 1 is connected with the lower end of the right rib plate 2, the left rib, the reinforcing plate 4 is obliquely arranged inside the storage box support frame body, the lower end of the reinforcing plate 4 is connected with the middle of the left rib plate 1, the upper end of the reinforcing plate 4 is connected with the joint of the web plate 3 and the right rib plate 2, the outer side edges of the left rib plate 1, the right rib plate 2 and the web plate 3 simultaneously extend to two ends to form wing plates, and the left rib plate 1, the right rib plate 2, the web plate 3 and the reinforcing plate 4 are of an integrated structure.
Further, the angle between the reinforcing plate 4 and the upper end face of the web 3 is α -40 °.
Further, the metal support lug 5 is made of titanium alloy TC4, the storage box support shell is made of carbon fiber reinforced epoxy resin matrix composite material, and the carbon fiber is made of M40 material; the resin is an epoxy resin material.
Further, the length of the tank holder housing is L, L being 435mm, and the height of the tank holder housing is H, H being 448 mm.
Further, the metal support lug further comprises four first bolts, two first screw holes 32 are formed in two sides of the upper end face of the web plate 3 respectively in the vertical direction, and each metal support lug 5 is connected with the web plate 3 through the two first bolts.
Furthermore, the lower end face of the metal support lug 5 is fixedly connected with the upper end face of the web plate 3 in a gluing mode, and the adhesive is J-133 adhesive.
Further, the novel aircraft engine further comprises four second bolts, two second screw holes 33 are formed in the upper portions of the two ends of the web plate 3 respectively, and the two ends of the web plate 3 are connected with the external cabin section through the two second bolts respectively.
A method of manufacturing a carbon fibre composite tank cradle, the method being carried out by,
step one, prepreg retesting:
the environmental condition requirements of the prepreg reinspection are as follows: the environmental temperature is 10-35 ℃ and the relative humidity is less than or equal to 65 percent; preparing materials, tools and measuring tools required by rechecking, detecting the thickness, the volume content of carbon fibers, the mass per unit area, the volatile matter content and the gel time of the prepreg, rechecking the epoxy value of epoxy resin in the prepreg, and rechecking the strand tensile strength and the tensile modulus of carbon fibers in the prepreg;
step two, prepreg blanking:
the environmental condition requirement of prepreg blanking is as follows: the environmental temperature is 15-35 ℃ and the humidity is less than or equal to 65 percent; taking out the prepreg from the freezer, placing the prepreg for 2-4 hours at room temperature, and then using the prepreg, wherein the blanking angle is 0 degree on the basis of the datum line, blanking is carried out according to the directions of 0 degree, 90 degrees, +45 degrees and-45 degrees, and recording;
step three, preparing a forming die:
cleaning the mold by using a tool, and brushing a release agent on the surface of the mold;
step four, laying prepreg;
a. the storage box bracket shell is divided into four small pieces to be laid, namely a left rib plate 1, a right rib plate 2, a web plate 3 and a reinforcing plate 4, the four small pieces of surfaces are laid separately, the definition is that the direction parallel to the frame is 0 degree, the direction vertical to the frame is 90 degrees,
firstly, laying a left rib plate 1, laying according to the directions of 0 degree, 90 degrees, +45 degrees, -45 degrees, 0 degree and 90 degrees by taking a short straight edge as 0 degree, and recording; laying the long straight edge at 0 degree, laying according to the directions of 0 degree, 90 degrees, +45 degrees, -45 degrees, 0 degrees and 90 degrees, and recording; laying the materials according to the directions of 0 degree, 90 degrees, 0 degree and 90 degrees with the bent edge as 0 degree, and recording;
then, laying a right rib plate 2, wherein the specific steps of laying the right rib plate 2 are the same as those of laying the left rib plate 1;
then, laying a web 3, wherein the concrete steps of laying the web 3 are the same as those of laying the left rib plate 1;
finally, laying the reinforcing plate 4, wherein the concrete steps of laying the reinforcing plate 4 are the same as those of laying the left rib plate 1;
so far, the independent laying of the left rib plate 1, the right rib plate 2, the web plate 3 and the reinforcing plate 4 is completed;
b. combining all the small blocks, and then laying a reinforcement area layer;
c. after the reinforcing area is paved, prepressing, and paving layers after paving the combined small blocks;
step five, die assembly:
the method comprises the following steps of (1) pressurizing and closing the dies by adopting bolts, ensuring that the front and rear positions of the dies are aligned when the dies are closed, symmetrically fastening the pressurizing bolts when the dies are closed, so as to close the upper and lower dies, after the dies are closed, putting the dies into a curing furnace, heating the dies in the curing furnace for 3 hours at 100 ℃, taking out a product, and closing the dies to be in place with the die closing gap smaller than 0.1 mm;
step six, curing:
curing according to a curing system of (100 +/-5) ° c/(1 +/-10 min) h → (150 +/-5) ° c/(2 +/-10 min) h → (170 +/-5) ° c/(4 +/-10 min), raising the temperature at a constant speed, and storing curing curve data;
step seven, demolding and finishing:
d. taking out the solidified product and the mould from the solidifying furnace, naturally cooling to room temperature for demoulding,
e. all bolts are disassembled, the upper die, the lower die, the left die and the right die are removed, the blocks in the opening cover are removed in sequence, the product is taken out, and the molding surface of the die cannot be scratched during demolding;
f. cleaning the die, and cleaning the surface of the die by using a copper sheet or an aluminum sheet;
g. the mould which is not used continuously in a short period is coated with silicone grease to form a surface, so that rusting is avoided; when the mold is stored, the female mold and the male mold are closed, and dust and moisture are prevented;
h. trimming the product burrs with a file or sandpaper;
thus, the manufacture of the carbon fiber composite material storage box bracket is completed.
Further, the prepreg in the step one is a carbon fiber hot-melt prepreg with a single-layer thickness of 0.15mm, the volume content of the carbon fiber is (58 +/-2)%, and the mass per unit area is (305 +/-5) g/m2The content of volatile matters is less than or equal to 2 percent, and the gelling time (150 ℃) is (40 +/-5) min; the epoxy value of the epoxy resin in the carbon fiber hot-melt prepreg is more than or equal to 0.85; the bundle yarn tensile strength of the carbon fiber in the carbon fiber hot-melt prepreg is not less than 3000MPa, and the tensile modulus is not less than 330 Gpa.
Further, the tool used for cleaning the die in the third step is a copper sheet or an aluminum sheet, after the die is cleaned and the surface of the working surface is free from any residual impurities, the surface of the die is wiped clean by using industrial-grade acetone, then a layer of release agent is uniformly brushed by using a flat brush, and the die is kept for later use after being completely dried.
Compared with the prior art, the invention has the following effects:
1. the carbon fiber composite material storage box support has high structural efficiency and good reliability, completely meets the requirements of high performance and light weight of aerospace, ensures the smooth operation of series models, and promotes the application of the carbon fiber composite material series support in the aerospace aspect. The carbon fiber composite material storage tank bracket is in a triangle-like special shape, the section is in a T shape and a cross shape, the width is narrow, and the two carbon fiber composite material storage tank brackets simultaneously bear one storage tank. The overall structure of the carbon fiber composite material storage box bracket is overloaded by 11g in the axial direction and 4g in the lateral direction. The steel ladle belt is adopted to connect the carbon fiber composite material storage tank bracket and the storage tank, the prestress is increased, the integrity of the storage tank and the bracket during bearing is improved, all parts are integrally loaded during loading, and the design requirements are met by calculating the strength and the rigidity.
2. The method for manufacturing the carbon fiber composite material storage tank support solves the technical problem of integration of design and forming of the carbon fiber composite material storage tank support, the forming process adopts a hot-melt prepreg matched die compression molding method, and during laying design, the laying process needs to be considered to ensure fiber continuity during forming, and the laying angle reference is reasonable and easy to implement. The left and right rib plates and the web plate are formed separately and then are assembled into a whole, and the reinforcing area and the side wing plate are formed. The carbon fiber composite material storage tank bracket manufactured by the method has high structural efficiency and good reliability, and completely meets the requirements of high performance and light weight of spaceflight.
Drawings
FIG. 1 is a front view of a carbon fiber composite tank cradle of the present invention;
FIG. 2 is a right side view of the carbon fiber composite tank cradle of the present invention;
FIG. 3 is a top view of a carbon fiber composite tank cradle according to the present invention;
FIG. 4 is a ply coordinate system and a ply zoning map of the present invention;
FIG. 5 is a cloud graph of a preliminary analysis stress check value distribution;
FIG. 6 is a schematic view of a finite element analysis model of the tank cradle constraint and connection.
Detailed Description
The first embodiment is as follows: the embodiment is described by combining fig. 1 to fig. 3, the carbon fiber composite material storage tank bracket of the embodiment comprises a storage tank bracket shell and two metal support lugs 5, the storage tank bracket shell comprises a left rib plate 1, a right rib plate 2, a web plate 3 and a reinforcing plate 4, the web plate 3 is horizontally arranged, the middle part of the upper end surface of the web plate 3 is provided with an arc-shaped groove 31 matched with the excircle of the storage tank, two sides of the upper end surface of the web plate 3 are respectively provided with one metal support lug 5, the metal support lug 5 is provided with a steel belt connecting hole 51, the right rib plate 2 is vertically arranged at the lower part of the right side of the web plate 3, the upper end of the right rib plate 2 is connected with the right end of the web plate 3, the left rib plate 1 is obliquely arranged between the web plate 3 and the right rib plate 2, the upper end of the left rib plate 1 is connected with the left end of the web plate 3, the lower end of the left rib plate 1 is connected with the, the storage tank support frame body is hollow right triangle structure, and reinforcing plate 4 slope sets up inside storage tank support frame body, and the lower extreme and the 1 middle part of left floor of reinforcing plate 4 are connected, and the upper end of reinforcing plate 4 is connected with handing-over department of web 3 and right floor 2, and the outside limit of left floor 1, right floor 2 and web 3 all extends to both ends simultaneously has the pterygoid lamina, left floor 1, right floor 2, web 3 and reinforcing plate 4 formula structure as an organic whole.
The outer sides of the left rib plate 1, the right rib plate 2 and the web plate 3 of the embodiment simultaneously extend to two ends to form wing plates, and composite material reinforcing areas are designed and optimized at the joints of the supports and other structures and are integrally formed.
Second embodiment, referring to fig. 1, the embodiment is described, the included angle between the reinforcing plate 4 and the upper end face of the web 3 of the embodiment is α -40 °, the reinforcing plate 4 is designed and the position thereof is optimized in the process of designing the structure of the storage tank bracket, the overall dimension is guaranteed to be unchanged, and after the structure with the included angle from 0 ° to 180 ° is analyzed, the position of the included angle of 40 ° is determined to be optimal.
The third concrete implementation mode: the embodiment is described with reference to fig. 1 to 3, the metal lug 5 of the embodiment is made of titanium alloy TC4, the storage tank bracket shell is a carbon fiber reinforced epoxy resin matrix composite shell, and the carbon fiber is M40 material; the resin is an epoxy resin material. Other compositions and connections are the same as in the first or second embodiments.
The fourth concrete implementation mode: in the present embodiment, the length of the tank holder case of the present embodiment is L, where L is 435mm, and the height of the tank holder case is H, where H is 448mm, as described with reference to fig. 1. Other compositions and connection relationships are the same as in the first, second or third embodiment.
The fifth concrete implementation mode: the present embodiment is described with reference to fig. 1 to 3, and the present embodiment further includes four first bolts, two first screw holes 32 are respectively formed in two sides of the upper end surface of the web 3 along the vertical direction, and each metal lug 5 is connected to the web 3 through two first bolts. So arranged, the area of weakness is designed and optimized. The metal reinforcement is designed and optimized locally at the location of the bolts connecting the tanks. Other compositions and connection relationships are the same as those in the first, second, third or fourth embodiment.
The sixth specific implementation mode: referring to fig. 1 to 3, the present embodiment will be described, in which the lower end surface of the metal lug 5 of the present embodiment is fixed to the upper end surface of the web 3 by means of adhesive bonding, and J-133 adhesive is used as the adhesive. Other compositions and connection relationships are the same as in the first, second, third, fourth or fifth embodiment.
The seventh embodiment: the present embodiment is described with reference to fig. 1 to 3, and the present embodiment further includes four second bolts, two second screw holes 33 are respectively formed in upper portions of two ends of the web 3, and two ends of the web 3 are respectively connected to the outer cabin section through the two second bolts. Other compositions and connection relationships are the same as in the first, second, third, fourth, fifth or sixth embodiment.
The specific implementation mode is eight: the embodiment is described with reference to fig. 1 to 6, and the method for manufacturing the carbon fiber composite material tank bracket of the embodiment is realized by the following steps,
step one, prepreg retesting:
the environmental condition requirements of the prepreg reinspection are as follows: the environmental temperature is 10-35 ℃ and the relative humidity is less than or equal to 65 percent; preparing materials, tools and measuring tools required by rechecking, detecting the thickness, the volume content of carbon fibers, the mass per unit area, the volatile matter content and the gel time of the prepreg, rechecking the epoxy value of epoxy resin in the prepreg, and rechecking the strand tensile strength and the tensile modulus of carbon fibers in the prepreg;
step two, prepreg blanking:
the environmental condition requirement of prepreg blanking is as follows: the environmental temperature is 15-35 ℃ and the humidity is less than or equal to 65 percent; taking out the prepreg from the freezer, placing the prepreg for 2-4 hours at room temperature, and then using the prepreg, wherein the blanking angle is 0 degree on the basis of the datum line, blanking is carried out according to the directions of 0 degree, 90 degrees, +45 degrees and-45 degrees, and recording;
step three, preparing a forming die:
cleaning the mold by using a tool, and brushing a release agent on the surface of the mold;
step four, laying prepreg;
a. the storage box bracket shell is divided into four small pieces to be laid, namely a left rib plate 1, a right rib plate 2, a web plate 3 and a reinforcing plate 4, the four small pieces of surfaces are laid separately, the definition is that the direction parallel to the frame is 0 degree, the direction vertical to the frame is 90 degrees,
firstly, laying a left rib plate 1, laying according to the directions of 0 degree, 90 degrees, +45 degrees, -45 degrees, 0 degree and 90 degrees by taking a short straight edge as 0 degree, and recording; laying the long straight edge at 0 degree, laying according to the directions of 0 degree, 90 degrees, +45 degrees, -45 degrees, 0 degrees and 90 degrees, and recording; laying the materials according to the directions of 0 degree, 90 degrees, 0 degree and 90 degrees with the bent edge as 0 degree, and recording;
then, laying a right rib plate 2, wherein the specific steps of laying the right rib plate 2 are the same as those of laying the left rib plate 1;
then, laying a web 3, wherein the concrete steps of laying the web 3 are the same as those of laying the left rib plate 1;
finally, laying the reinforcing plate 4, wherein the concrete steps of laying the reinforcing plate 4 are the same as those of laying the left rib plate 1;
so far, the independent laying of the left rib plate 1, the right rib plate 2, the web plate 3 and the reinforcing plate 4 is completed;
b. combining all the small blocks, and then laying a reinforcement area layer;
c. after the reinforcing area is paved, prepressing, and paving layers after paving the combined small blocks;
step five, die assembly:
the method comprises the following steps of (1) pressurizing and closing the dies by adopting bolts, ensuring that the front and rear positions of the dies are aligned when the dies are closed, symmetrically fastening the pressurizing bolts when the dies are closed, so as to close the upper and lower dies, after the dies are closed, putting the dies into a curing furnace, heating the dies in the curing furnace for 3 hours at 100 ℃, taking out a product, and closing the dies to be in place with the die closing gap smaller than 0.1 mm;
step six, curing:
curing according to a curing system of (100 +/-5) ° c/(1 +/-10 min) h → (150 +/-5) ° c/(2 +/-10 min) h → (170 +/-5) ° c/(4 +/-10 min), raising the temperature at a constant speed, and storing curing curve data;
step seven, demolding and finishing:
d. taking out the solidified product and the mould from the solidifying furnace, naturally cooling to room temperature for demoulding,
e. all bolts are disassembled, the upper die, the lower die, the left die and the right die are removed, the blocks in the opening cover are removed in sequence, the product is taken out, and the molding surface of the die cannot be scratched during demolding;
f. cleaning the die, and cleaning the surface of the die by using a copper sheet or an aluminum sheet;
g. the mould which is not used continuously in a short period is coated with silicone grease to form a surface, so that rusting is avoided; when the mold is stored, the female mold and the male mold are closed, and dust and moisture are prevented;
h. trimming the product burrs with a file or sandpaper;
thus, the manufacture of the carbon fiber composite material storage box bracket is completed. Other compositions and connection relationships are the same as those of embodiment one, two, three, four, five, six or seven.
The performance data of the prepreg unidirectional plate should meet the index requirements specified in the technical requirements for manufacturing and acceptance of composite material supports. The TDE-85 epoxy resin can be used according to a prescription of a Q/HBY015-2002 epoxy resin in-factory re-inspection standard for re-inspecting the epoxy value, wherein the epoxy value is more than or equal to 0.85; the M40 carbon fiber can be used according to the fiber prescription that Q/HBY016-2002 carbon fiber in-factory retest standard retests the tensile strength and tensile modulus of the bundle yarn, the tensile strength of the bundle yarn is more than or equal to 3000MPa, and the tensile modulus is more than or equal to 330 GPa. The prepreg used for bracket production is subjected to a mechanical property test of the unidirectional board before the product is put into production, the test items and indexes are shown in table 1, and the detection method is carried out according to corresponding national standards or row standards.
Table 1 materials unidirectional sheet performance data
| Item | Unit of | M40/8485 Performance data |
| 0 degree tensile strength | MPa | ≥1050 |
| 0 degree tensile modulus | GPa | ≥200 |
| Tensile strength of 90 DEG | MPa | ≥19 |
| Tensile modulus at 90 ° | GPa | ≥8.2 |
| 0 degree compressive strength | MPa | ≥800 |
| Modulus of compression at 0 ° | GPa | ≥120 |
| 90 degree compressive strength | MPa | ≥92.9 |
| 90 degree compression modulus | GPa | ≥8.2 |
| Interlaminar shear strength | MPa | ≥40 |
| Shear modulus | GPa | ≥4.16 |
| Fiber volume content | ％ | 60±3 |
| Degree of curing | ％ | ≥92 |
The prepregs used for scaffold production should be the same batch of material. When the prepreg is rechecked, 10 layers of the prepreg are cut into small pieces and overlapped together, the pieces are compacted, the thickness of the pieces is measured by a digital vernier caliper, and the average value is divided by 10 to obtain the thickness of the single-layer prepreg.
The prepreg blanking environment in the step two is as follows: clean, dustless, constant temperature and humidity room.
The prepreg laying process in the fourth step has the specific requirements that: the resin film is applied to the mold, and the molding surface is required to be covered completely and uniformly. After each layer is laid, the layer is compacted by a putty knife, and bubbles are removed. And trimming the prepreg at the position of the closed edge to ensure that the edge is neat and the die assembly is smooth.
The specific implementation method nine: the present embodiment will be described with reference to fig. 1 to 6, wherein the prepreg in the first step of the present embodiment is a carbon fiber hot melt prepreg having a single layer thickness of 0.15mm, a carbon fiber volume content of (58 ± 2)%, and a mass per unit area of (305 ± 5) g/m2The content of volatile matters is less than or equal to 2 percent, and the gelling time (150 ℃) is (40 +/-5) min; the epoxy value of the epoxy resin in the carbon fiber hot-melt prepreg is more than or equal to 0.85; the bundle yarn tensile strength of the carbon fiber in the carbon fiber hot-melt prepreg is not less than 3000MPa, and the tensile modulus is not less than 330 Gpa. Other compositions and connection relationships are the same as those in the first, second, third, fourth, fifth, sixth, seventh or eighth embodiment.
The epoxy resin in the carbon fiber hot-melt prepreg in the step one is TDE-85, and the carbon fiber in the carbon fiber hot-melt prepreg is M40.
The detailed implementation mode is ten: referring to fig. 1 to 6, the present embodiment is described, the tool used for cleaning the mold in the third step of the present embodiment is a copper sheet or an aluminum sheet, which cannot damage the working surface (product surface) of the mold, after the mold is cleaned and the surface of the working surface has no residual impurities, the mold surface is wiped clean with industrial grade acetone, and then a layer of mold release agent is uniformly brushed with a flat brush, and the mold is kept after being completely dried. Other compositions and connections are the same as those of the first, second, third, fourth, fifth, sixth, seventh, eighth or ninth embodiments.
The release agent in step three was manufactured by CHEMLEASE manufacturer with model number PMR.
Principle of operation
The method for manufacturing the carbon fiber composite material storage tank bracket adopts a hot-melt prepreg matched die compression molding method, and during laying design, consideration needs to be given to ensuring fiber continuity during laying process molding, and reasonable and easy implementation of laying angle reference. Thus, four ply coordinate systems are defined, each ply coordinate system being 0 ° in parallel with the bracket wings and the stiffening ribs. The composite reservoir holder was then divided into 4 sections defining the ply angle, but the 4 section ply angles were coordinated because the ply angle of the continuous fibers was different at each section. FIG. 4 is a ply coordinate system and a ply zoning map with the direction of the arrow being the ply angle 0.
The bending rigidity of wing plates and rib plates is high as a result of finite element calculation, more 0-degree laying layers parallel to the wing plates and the rib plates are arranged at the side edge positions, 2-3 layers at the positions are designed to be continuous fibers during laying, other angles are included, and difficulty in die assembly of the continuous fibers when the concave and convex surfaces are more is reduced. Since the structure is also laterally overloaded, a 90 ° lay-up is required on the side flanges.
During the design of the die, the left rib plate, the right rib plate and the web plate are formed in a split mode, and then the left rib plate, the right rib plate and the web plate are assembled into a whole to form a reinforcing area and a side wing plate. Aiming at the structural characteristics of a product, through repeated design and change, the design of the die adopts a multi-split design and is divided into an upper part, a lower part and a side pressurizing part, the upper substrate and the lower substrate of the three parts are taken as references, the independent parts are positioned and fastened on the substrate after being laid and molded, the side wing plates are continuously molded, the side pressurizing plates are used for pressurizing the wing plates, and meanwhile, the substrate provides a slide way for pressurizing the wing plates.
The precision of the structure size of the precision composite material is ensured:
the dimensional accuracy requirement of the carbon fiber composite material storage box support is very strict, firstly, every two supports are combined into one group, the perpendicularity of the support reference surfaces of the same group is required to be ensured to be consistent, the processing amount is reserved on the reference surfaces in the laying process, the support is positioned by a design tool, the reference surfaces are finely processed by a numerical control milling machine, and the perpendicularity of the reference surfaces is ensured to be consistent. Meanwhile, the size precision of the bonded wrapping tape support lug is consistent with that of the reference mounting hole, and the overall bonding tool is designed, is in charge of processing the reference hole, and plays a role in overall bonding.
Designing and realizing a complex bracket destruction and identification test scheme:
a110 kg cylinder is adopted to simulate an engine storage tank, a hydraulic actuating cylinder is used for pressurizing the engine storage tank to realize the loading of all levels of actual working conditions, the loading is controlled by a computer step by step, and meanwhile, a strain gauge is adopted to measure displacement. The product began to have a gradual cracking sound when the load was applied to about 2360kg, and the loading system was automatically unloaded when the load was applied to 2715kg, and the test was terminated. The corresponding failure load at this time is about 22 nd order load (about 24.2g), which is much greater than the design load. Subsequent careful observation revealed no visible damage to the surface of the product. The experimental results are matched with the design calculation results.
The structural design technology of the carbon fiber composite material storage tank bracket comprises the following steps:
the carbon fiber composite material storage tank bracket is in a triangle-like special shape, the section is in a T shape and a cross shape, the width is narrow, and the two carbon fiber composite material storage tank brackets simultaneously bear one storage tank. The overall structure of the carbon fiber composite material storage box bracket is overloaded by 11g in the axial direction and 4g in the lateral direction. The maximum displacement of the carbon fiber composite material storage box support is 11.8mm and the maximum value of the stress failure criterion is 1.3 according to the result of preliminary analysis of finite element software, and the strength of the overall structure of the flexible connection cannot meet the requirement through finite element calculation analysis, so that the support structure is damaged. In order to ensure the stability and safety of the support structure, a connecting support rod is designed between the two supports. But not adopted due to installation problems. Finally, the steel ladle belt is adopted to connect the carbon fiber composite material storage tank bracket and the storage tank, and the prestress is increased, so that the integrity of the storage tank and the bracket during bearing is improved, and each component is integrally loaded during loading, and the design requirements are met by calculating the strength and the rigidity.
The simulation analysis technology of the carbon fiber composite material storage tank bracket comprises the following steps:
the maximum deformation of the composite storage tank bracket is calculated to be 0.635mm through analysis. The storage box bracket is calibrated by adopting a Chua-Wu standard, the maximum value is 0.493, and the structural strength and rigidity of the composite storage box bracket meet the design requirements. Through real and effective finite element simulation calculation, the time and the cost are saved for the development work of the composite material storage box bracket project. The composite material storage tank bracket is tested, the failure load calculation result is 22.3g, the failure load test result is 24g, the deviation is 7%, and the analysis and prediction failure position are the same as the test. The calculated results are compared with the test results in table 2.
TABLE 2 comparison of the calculated results with the test results
Claims (10)
1. The utility model provides a carbon-fibre composite storage tank support which characterized in that: the novel storage tank comprises a storage tank support shell and two metal support lugs (5), wherein the storage tank support shell comprises a left rib plate (1), a right rib plate (2), a web plate (3) and a reinforcing plate (4), the web plate (3) is horizontally arranged, a circular arc-shaped groove (31) matched with the excircle of the storage tank is formed in the middle of the upper end face of the web plate (3), the metal support lugs (5) are respectively arranged on two sides of the upper end face of the web plate (3), a steel belt connecting hole (51) is formed in each metal support lug (5), the right rib plate (2) is vertically arranged on the lower portion of the right side of the web plate (3), the upper end of the right rib plate (2) is connected with the right end of the web plate (3), the left rib plate (1) is obliquely arranged between the web plate (3) and the right rib plate (2), the upper end of the left rib plate (1) is connected with the left end of the web plate (3), the lower end, Right rib board (2) and web (3) end to end in proper order form storage tank support framework, storage tank support framework is hollow right triangle structure, reinforcing plate (4) slope sets up inside storage tank support framework, the lower extreme and the left rib board (1) middle part of reinforcing plate (4) are connected, the upper end and the handing-over department of web (3) and right rib board (2) of reinforcing plate (4) are connected, left rib board (1), the outside limit of right rib board (2) and web (3) all extends to both ends simultaneously has the pterygoid lamina, left rib board (1), right rib board (2), web (3) and reinforcing plate (4) formula structure as an organic whole.
2. The carbon fiber composite material storage tank bracket as claimed in claim 1, wherein the angle between the reinforcing plate (4) and the upper end face of the web plate (3) is α -40 degrees.
3. A carbon fiber composite tank cradle as set forth in claim 2, wherein: the metal support lug (5) is made of titanium alloy TC4, the storage box support shell is a carbon fiber reinforced epoxy resin matrix composite shell, and the carbon fiber is an M40 material; the resin is an epoxy resin material.
4. A carbon fiber composite tank cradle as set forth in claim 3, wherein: the length of the tank support housing is L, 435mm, and the height of the tank support housing is H, 448 mm.
5. The carbon fiber composite tank cradle according to claim 4, wherein: the novel metal support lug structure is characterized by further comprising four first bolts, two first screw holes 32 are formed in two sides of the upper end face of the web plate (3) in the vertical direction respectively, and each metal support lug (5) is connected with the web plate (3) through the two first bolts.
6. The carbon fiber composite tank cradle according to claim 5, wherein: the lower end face of the metal support lug (5) is fixedly connected with the upper end face of the web plate (3) in a gluing mode, and the adhesive is J-133 adhesive.
7. The carbon fiber composite tank cradle according to claim 6, wherein: the novel aircraft engine further comprises four second bolts, two second screw holes 33 are formed in the upper portions of the two ends of the web plate (3) respectively, and the two ends of the web plate (3) are connected with the external cabin section through the two second bolts respectively.
8. A molding method for manufacturing the carbon fiber composite material tank bracket as defined in any one of claims 1 to 7, characterized in that: the method is realized by the following steps,
step one, prepreg retesting:
the environmental condition requirements of the prepreg reinspection are as follows: the environmental temperature is 10-35 ℃ and the relative humidity is less than or equal to 65 percent; preparing materials, tools and measuring tools required by rechecking, detecting the thickness, the volume content of carbon fibers, the mass per unit area, the volatile matter content and the gel time of the prepreg, rechecking the epoxy value of epoxy resin in the prepreg, and rechecking the strand tensile strength and the tensile modulus of carbon fibers in the prepreg;
step two, prepreg blanking:
the environmental condition requirement of prepreg blanking is as follows: the environmental temperature is 15-35 ℃ and the humidity is less than or equal to 65 percent; taking out the prepreg from the freezer, placing the prepreg for 2-4 hours at room temperature, and then using the prepreg, wherein the blanking angle is 0 degree on the basis of the datum line, blanking is carried out according to the directions of 0 degree, 90 degrees, +45 degrees and-45 degrees, and recording;
step three, preparing a forming die:
cleaning the mold by using a tool, and brushing a release agent on the surface of the mold;
step four, laying prepreg;
a. the storage box support shell is divided into four small pieces to be laid, namely a left rib plate (1), a right rib plate (2), a web plate (3) and a reinforcing plate (4), the four small pieces of surfaces are laid independently, the definition is that the direction parallel to the frame is 0 degree, the direction perpendicular to the frame is 90 degrees,
firstly, laying a left rib plate (1) with a short straight edge as 0 degree, laying according to the directions of 0 degree, 90 degrees, +45 degrees, -45 degrees, 0 degree and 90 degrees, and recording; laying the long straight edge at 0 degree, laying according to the directions of 0 degree, 90 degrees, +45 degrees, -45 degrees, 0 degrees and 90 degrees, and recording; laying the materials according to the directions of 0 degree, 90 degrees, 0 degree and 90 degrees with the bent edge as 0 degree, and recording;
then, laying the right rib plate (2), wherein the concrete steps of laying the right rib plate (2) are the same as those of laying the left rib plate (1);
then, laying a web plate (3), wherein the concrete steps of laying the web plate (3) are the same as those of laying the left rib plate (1);
finally, laying the reinforcing plate (4), wherein the concrete steps of laying the reinforcing plate (4) are the same as those of laying the left rib plate (1);
so far, the independent laying of the left rib plate (1), the right rib plate (2), the web plate (3) and the reinforcing plate (4) is completed;
b. combining all the small blocks, and then laying a reinforcement area layer;
c. after the reinforcing area is paved, prepressing, and paving layers after paving the combined small blocks;
step five, die assembly:
the method comprises the following steps of (1) pressurizing and closing the dies by adopting bolts, ensuring that the front and rear positions of the dies are aligned when the dies are closed, symmetrically fastening the pressurizing bolts when the dies are closed, so as to close the upper and lower dies, after the dies are closed, putting the dies into a curing furnace, heating the dies in the curing furnace for 3 hours at 100 ℃, taking out a product, and closing the dies to be in place with the die closing gap smaller than 0.1 mm;
step six, curing:
curing according to a curing system of (100 +/-5) ° c/(1 +/-10 min) h → (150 +/-5) ° c/(2 +/-10 min) h → (170 +/-5) ° c/(4 +/-10 min), raising the temperature at a constant speed, and storing curing curve data;
step seven, demolding and finishing:
d. taking out the solidified product and the mould from the solidifying furnace, naturally cooling to room temperature for demoulding,
e. all bolts are disassembled, the upper die, the lower die, the left die and the right die are removed, the blocks in the opening cover are removed in sequence, the product is taken out, and the molding surface of the die cannot be scratched during demolding;
f. cleaning the die, and cleaning the surface of the die by using a copper sheet or an aluminum sheet;
g. the mould which is not used continuously in a short period is coated with silicone grease to form a surface, so that rusting is avoided; when the mold is stored, the female mold and the male mold are closed, and dust and moisture are prevented;
h. trimming the product burrs with a file or sandpaper;
thus, the manufacture of the carbon fiber composite material storage box bracket is completed.
9. A method of manufacturing a carbon fibre composite tank cradle as claimed in claim 8, wherein: the prepreg in the step one is a carbon fiber hot-melt prepreg with a single-layer thickness of 0.15mm, the volume content of carbon fibers is (58 +/-2)%, and the mass per unit area is (305 +/-5) g/m2The content of volatile matters is less than or equal to 2 percent, and the gelling time (150 ℃) is (40 +/-5) min; the epoxy value of the epoxy resin in the carbon fiber hot-melt prepreg is more than or equal to 0.85; the bundle yarn tensile strength of the carbon fiber in the carbon fiber hot-melt prepreg is not less than 3000MPa, and the tensile modulus is not less than 330 Gpa.
10. A method of manufacturing a carbon fibre composite tank cradle as claimed in claim 9, wherein: and in the third step, the tool used for cleaning the die is a copper sheet or an aluminum sheet, after the die is cleaned and the surface of the working surface is free from any residual impurities, the surface of the die is wiped clean by using industrial-grade acetone, then a layer of release agent is uniformly brushed by using a flat brush, and the die is dried completely for later use.
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114347445A (en) * | 2022-01-13 | 2022-04-15 | 长春长光宇航复合材料有限公司 | Preparation method of carbon fiber composite material low-expansion truss round rod |
| CN114683587A (en) * | 2022-04-13 | 2022-07-01 | 华东交通大学 | Carbon fiber composite material T-shaped joint and manufacturing method and repairing method thereof |
-
2020
- 2020-04-20 CN CN202010314083.7A patent/CN111365143A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114347445A (en) * | 2022-01-13 | 2022-04-15 | 长春长光宇航复合材料有限公司 | Preparation method of carbon fiber composite material low-expansion truss round rod |
| CN114347445B (en) * | 2022-01-13 | 2023-11-28 | 长春长光宇航复合材料有限公司 | Preparation method of carbon fiber composite material low-expansion truss round bar |
| CN114683587A (en) * | 2022-04-13 | 2022-07-01 | 华东交通大学 | Carbon fiber composite material T-shaped joint and manufacturing method and repairing method thereof |
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