CN114103158A - Forming method of special-shaped composite skirt of solid rocket engine - Google Patents
Forming method of special-shaped composite skirt of solid rocket engine Download PDFInfo
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- CN114103158A CN114103158A CN202111239713.XA CN202111239713A CN114103158A CN 114103158 A CN114103158 A CN 114103158A CN 202111239713 A CN202111239713 A CN 202111239713A CN 114103158 A CN114103158 A CN 114103158A
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Classifications
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/30—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
- B29C70/345—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 using matched moulds
-
- 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
- B29C37/00—Component parts, details, accessories or auxiliary operations, not covered by group B29C33/00 or B29C35/00
- B29C37/02—Deburring or deflashing
-
- 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
- B29C69/00—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore
- B29C69/001—Combinations of shaping techniques not provided for in a single one of main groups B29C39/00 - B29C67/00, e.g. associations of moulding and joining techniques; Apparatus therefore a shaping technique combined with cutting, e.g. in parts or slices combined with rearranging and joining the cut parts
-
- 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
- B29C70/545—Perforating, cutting or machining during or after moulding
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Physics & Mathematics (AREA)
- Thermal Sciences (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a method for forming a special-shaped composite skirt of a solid rocket engine, which comprises the following steps: s1, assembling a forming tool and cleaning the surface, S2, pre-laminating and pre-pressing prepreg before die assembly, S3, laminating prepreg after die assembly and die assembly, S4, curing and forming, S5, machining, S6, demoulding and cleaning the surface. The special-shaped (T-shaped) composite skirt of the solid rocket engine, which has novel structure, stable performance and strong bearing capacity and meets the design requirements, is prepared by the forming method.
Description
Technical Field
The invention relates to the field of processing and forming of composite skirts, in particular to a method for forming a special-shaped composite skirt of a solid rocket engine.
Background
The solid rocket engine connecting skirt is used for connecting the shell and the shell or connecting the shell and other parts, and can be subjected to the action of various loads (such as internal pressure, shearing, axial pressure and the like) in the flying process, the stress condition is complex, and one of the keys for improving the performance of the solid rocket engine is how to improve the performance of the connecting skirt. Most of the existing solid rocket engines adopt metal skirts, and the metal skirts have large passive mass and are not beneficial to improving the mass ratio of the solid rocket engines. The connecting skirt made of the composite material can reduce the structural mass on the premise of meeting or even exceeding the performance of the metal skirt, the forming period is relatively short, the reliability is high, and the composite material connecting skirt is beneficial to improving the overall performance of the solid rocket engine.
The composite skirt molding method has various modes, wherein manual prepreg laying and autoclave curing are one of the most common molding methods of the composite skirt. The composite skirt forming mode mainly cuts unidirectional prepreg into required angles and sizes, then lays the prepreg with different angles and sizes on a composite skirt forming tool according to corresponding paving sequence, then transfers the composite skirt and the forming tool into an autoclave, heats to enable resin in the prepreg to have fluidity, slowly cures while filling the prepreg paving layers, and pressurizes to enable the resin in the prepreg to flow and compact between the paving layers in the curing process so as not to generate layering and pores. The composite skirt forming method has the advantages that the operation environment is relatively clean when the composite skirt is layered, the formed product has stable performance and strong bearing capacity, and the porosity of the product is small.
The composite skirt has various structures, wherein the most common is the composite skirt with an L-shaped structure, and the composite skirt with a T-shaped structure is less common.
Based on the situation, the invention provides a method for forming the special-shaped composite skirt of the solid rocket engine, which can effectively solve the problems.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a method for forming a special-shaped composite skirt of a solid rocket engine. The special-shaped (T-shaped) composite skirt of the solid rocket engine, which has novel structure, stable performance and strong bearing capacity and meets the design requirements, is prepared by the forming method
In order to solve the technical problems, the invention is realized by the following technical scheme:
in a first aspect, the invention provides a method for forming a special-shaped composite skirt of a solid rocket engine, which comprises the following steps:
s1, assembling a forming tool and cleaning the surface: disassembling an upper template and a lower template of a forming tool with a T-shaped forming surface in section and cleaning the surfaces of the upper template and the lower template;
s2, prepreg laying and prepressing before mold closing: respectively and completely covering the cut multilayer prepreg on the molding surfaces of an upper template and a lower template with L-shaped molding surfaces in cross section according to a design angle, and vacuumizing by adopting a vacuumizing device;
s3, die assembly and prepreg laying after die assembly: closing and pressing the upper and lower templates after laying by using a crane, and then laying prepreg on the inner circle of the composite skirt barrel section again until laying is finished;
s4, curing and forming: transferring the composite skirt with the vacuumizing device and the forming tool into an autoclave, curing the composite skirt at a designed temperature and pressure, and vacuumizing at the same time;
s5, machining: machining the inner circle of the composite skirt cylinder section to enable the size of the inner circle to meet the requirement;
s6, demolding and surface cleaning: separating an upper template, a lower template and the composite skirt of the composite skirt forming tool, and cleaning burrs and burrs on the surface of the composite skirt after the separation is finished, thereby finally obtaining the composite skirt with the T-shaped section.
Preferably, in step S1, the upper and lower templates are respectively provided with a plurality of inserts, and the molding surface of the lower template adjacent to the inserts is provided with a plurality of grooves.
Preferably, in step S1, the surface of the forming tool needs to be cleaned by non-woven paper and ethyl acetate, and then the forming surfaces of the upper and lower templates are attached with the release cloth.
Preferably, the step of laying up and pre-pressing the prepreg before mold clamping in step S2 includes:
s21, preheating the forming tool or brushing a layer of adhesive on the forming surface;
s22, carrying out first laying of the prepreg and ensuring complete compaction;
s23, after the first layering is finished, vacuumizing by using a vacuumizing device;
and S24, after the first pre-pressing is finished, removing the vacuum extractor, and carrying out secondary prepreg laying until the laying is finished.
Preferably, the step S2 of vacuumizing with a vacuumizing device includes the specific steps of: cutting the adhesive absorption cloth with the same size as the molding surfaces of the upper and lower templates to cover the surface of the prepreg, cutting the air felt with the same area to cover the surface of the adhesive absorption cloth, adhering vacuum bag sealing adhesive tapes along the upper and lower inner circles of the upper and lower templates, cutting a vacuum bag film, covering the air felt, adhering two ends of the vacuum bag film on the sealing adhesive tapes, compacting, reserving a polytetrafluoroethylene tube for vacuumizing at the same time, and vacuumizing and pre-pressing in a furnace.
More preferably, the furnace entering vacuumizing prepressing condition is that the temperature is set to be 50 +/-5 ℃, and the prepressing time is more than or equal to 4 hours.
Preferably, in step S3, after the mold is closed, the gap between the mold closing surfaces of the upper and lower mold plates is filled with a prepreg.
Preferably, in step S4, the curing conditions are: room temperature → 130 plus or minus 5 ℃/2h → 160 plus or minus 5 ℃/4h → 60 plus or minus 5 ℃, the pressure in the autoclave is 0.1 plus or minus 0.02MPa → 2.8 plus or minus 0.2MPa/11.5h → 0.1 plus or minus 0.02MPa, the pressure in the processes of temperature rise and heat preservation is 2.8 plus or minus 0.2MPa, the temperature rise rate is 0.5 ℃/min, the pressure rise rate is 0.05MPa/min, the temperature reduction rate is 0.6 ℃/min, and the pressure reduction rate is 0.025 MPa/min.
Preferably, in step S5, the upper template is separated from one end of the composite skirt by using a crane and a sling, and the other end of the composite skirt is separated from the lower template by using an insert on the lower template of the forming tool, so as to finally complete demolding of the composite skirt.
Preferably, the laying prepreg on the flange edges of the upper template and the lower template is evenly cut into small strips along the fiber direction by a putty knife, and then the prepreg on the molding surface of the flange edges of the upper template and the lower template is compacted by the putty knife.
Compared with the prior art, the invention has the following advantages and beneficial effects:
1. structurally, the composite skirt barrel section described in the invention is a bonding area (i.e. a bonding area with a shell body of a shell rocket engine), and a transition area (bearing area) also exists between the bonding area of the conventional composite skirt barrel section and a flange edge, so that structurally, the composite skirt described in the invention does not have the transition area, the overall quality of the composite skirt is greatly reduced, and the risk caused by the defects of the transition area is also reduced. The flange edge of the composite skirt is directly connected with the cylinder section bonding area, a transition area between the flange edge of the conventional composite skirt and the cylinder section bonding area is eliminated, the risk caused by instability of the transition area is avoided, and the stability of the T-shaped composite skirt is improved.
2. The flange edge has a local thickened area (corresponding to the groove of the lower template), and allowance is reserved for subsequent processing, so that the subsequent assembly precision is ensured.
3. The molding mode is to perform curing molding on the composite skirt by using a prepreg paving layer and autoclave curing molding mode. The autoclave has the characteristics of uniform heating and pressurizing and high pressure, and the porosity and the probability of internal defects of the composite skirt are reduced by using the forming mode, so that the performance stability of the composite skirt is improved.
4. The special structural design has eliminated the section of thick bamboo transition region between flange limit and the section of thick bamboo bonding region, and the whole bearing capacity of compound skirt has directly been decided to transition region's bearing capacity, when compound skirt load, the transition region that is at first destroyed has eliminated this region, become the bearing capacity of flange limit R angle department and decide the whole bearing capacity of compound skirt, and R angle department bearing capacity is stronger than section of thick bamboo transition region's bearing (when having the corner box, when compound skirt follow-up and casing bonding, compound skirt all can have the corner box, R angle department bearing capacity is stronger than section of thick bamboo transition region's bearing).
5. Through the prepreg spread layer angle design, the angle distribution of the spread layer is reasonable, and the bearing capacity of each spread layer in the direction is improved, so that the bearing capacity of the composite skirt is high.
6. The mass of the barrel section transition area between the flange edge and the barrel section bonding area is released, and the mass of the barrel section transition area accounts for 1/3-2/3 of the mass of the whole composite skirt, so that the load capacity of the solid rocket engine is further improved.
Drawings
FIG. 1 is a schematic sectional view of a molding tool of the present invention after prepreg is laid and assembled;
FIG. 2 is a schematic view of the left side of FIG. 1;
FIG. 3 is a schematic structural view of a molding surface of the molding tool of the present invention without prepreg being laid;
FIG. 4 is a schematic view of the inner side structure of the upper mold plate in the forming tool of the present invention;
FIG. 5 is a schematic view of the inner side structure of the lower mold plate in the forming tool of the present invention.
Reference numerals: the composite skirt forming device comprises a forming tool 1, an upper template 11, a lower template 12, an insert 101, a groove 102, a composite skirt 2, a composite skirt barrel section 21 and a composite skirt flange 22.
Detailed Description
In order that those skilled in the art will better understand the technical solutions of the present invention, the following description of the preferred embodiments of the present invention is provided in conjunction with specific examples, but it should be understood that the drawings are for illustrative purposes only and should not be construed as limiting the patent; for the purpose of better illustrating the embodiments, certain features of the drawings may be omitted, enlarged or reduced, and do not represent the size of an actual product; it will be understood by those skilled in the art that certain well-known structures in the drawings and descriptions thereof may be omitted. The positional relationships depicted in the drawings are for illustrative purposes only and are not to be construed as limiting the present patent.
As shown in fig. 1 to 5, the invention provides a forming tool for preparing a special-shaped composite skirt of a solid rocket engine, wherein the forming tool 1 comprises an upper template 11 and a lower template 12 which are both in a hollow annular structure, the upper template 11 and the lower template 12 are provided with vertically symmetrical L-shaped forming surfaces, and the two L-shaped forming surfaces are combined to form a T-shaped forming surface. The prepreg is pre-pressed on a T-shaped molding surface through a laying layer to form a composite skirt 2 with a T-shaped section, and the composite skirt 2 comprises a composite skirt barrel section 21 with an annular structure and a composite skirt flange 22 formed on the outer side wall of the composite skirt barrel section 21.
Furthermore, the upper die plate and the lower die plate are respectively provided with a plurality of inserts 101, a plurality of grooves 102 are formed in the forming surface of the lower die plate adjacent to the inserts 101, the depth of each groove 102 is 1mm, the length of each groove is 280mm, the width of each groove is 90mm, and 8 grooves 102 are uniformly distributed and used for increasing the thickness of the flange edge of the bonding part of the metal corner box, so that the maximum load capable of being borne at the position can meet requirements, and the assembly precision requirements of subsequent metal corner boxes are also guaranteed.
The method for forming the composite skirt comprises the following specific implementation steps:
1. preparation of
(1)730 adhesive, spreading prepreg, polytetrafluoroethylene glass fiber tape, vacuum bag, adhesive absorption cloth, air permeable felt, black glue, ethyl acetate and non-fluff paper.
(2) Self-made compound skirt shaping frock, vacuum pump.
(3) All systems of the equipment operate normally, and the whole composite layering process needs to ensure that the environmental temperature is 25 +/-10 ℃ and the relative humidity is less than or equal to 75 percent.
(4) And (4) working environment.
2. Prepreg inspection
And taking the cut laying carbon fiber prepreg out of a refrigerator, checking the grade and the using date of the laying carbon fiber prepreg, and if the using requirement is met, airing the laying carbon fiber prepreg at room temperature for 4 hours or more.
3. Inspection and cleaning of tooling
(1) And the surface of the composite skirt forming tool is inspected by visual inspection to have no obvious defects such as collision, scratch, deformation and the like.
(2) Checking the number of parts of the tool: the die comprises 1 lower die plate, 1 upper die plate, 16 inserts, 2 positioning pins, 32M 8 screws, 24M 24 screws and nuts respectively, and 4M 36 screws.
(3) Oil stains are not allowed to exist on the surface of the composite skirt forming tool, and if the oil stains exist, the composite skirt forming tool needs to be cleaned up by using non-woollen paper and ethyl acetate. The composite skirt forming is completed each time, after the composite skirt is demoulded, the resin and the polytetrafluoroethylene glass fiber adhesive tape on the composite skirt forming tool need to be cleaned, and the next composite skirt can be manufactured after the composite skirt is cleaned.
4. Assembly of inserts
And (3) respectively assembling 16 inserts into the upper template and the lower template, and fastening the inserts on the upper template and the lower template by using M8 screws.
5. Sticking of polytetrafluoroethylene glass fiber adhesive tape
The polytetrafluoroethylene glass fiber adhesive tape is pasted on the molding surface of the composite skirt molding tool, the surface is flat and free of protrusions after pasting, and wrinkles and pasting leakage cannot occur.
6. First prepreg ply
(1) Preheating a forming tool: preheating the molding tool at 50 ℃/3h or brushing a layer 730 of adhesive to increase the initial viscosity of the first layer of prepreg;
(2) firstly, carrying out 0-degree prepreg paving of a first layer, completely covering molding surfaces of an upper die and a lower die, then carrying out three-layer reinforced prepreg paving at a groove 102 of a lower die plate, sequentially carrying out 45-degree, 0-degree, 45-degree and 90-degree prepreg paving of an upper die and a lower die after the lower die is reinforced, wherein the paving position of each layer can be determined by a laser projector and a steel plate ruler, firstly removing silicone oil paper on the prepreg during paving, reserving a plastic film, then pasting one surface with the silicone oil paper removed on molding surfaces of the upper die plate and the lower die plate, compacting by hand, tearing off the plastic film on the compacted prepreg paving layer, uniformly scribing the paving layer at the flange edge into small strips along the fiber direction by using a putty knife, and compacting the prepreg on the molding surfaces of the flange edges of the upper die plate and the lower die plate by using the putty knife, the prepreg at the corner of the R angle needs to be completely compacted, layering cannot exist, and excess materials are required to be ensured after flanging.
(3) Checking whether the prepreg is compacted or not, and if the prepreg is compacted, cutting the prepreg at the bubble position along the fiber direction by using a putty knife, and removing the bubbles by using a plastic scraping plate or a putty knife; if wrinkles exist, slightly uncovering the prepreg, removing the wrinkles, and compacting; if the prepreg is locally disordered and cannot be guaranteed to be flat, removing the prepreg and re-adhering. If gaps exist at the splicing positions of the prepregs, the prepregs can be used for filling.
(4) After each layer of the skirt is laid, the angle of the laid layer and the surface state of the skirt are confirmed, and no surplus objects such as plastic films and the like are left on the surface.
7. Vacuumizing bag (first prepressing)
(1) After the first laying is finished, cutting the glue absorption cloth with the same size as the molding surface of the upper die and the lower die to cover the surface of the laid prepreg, and covering the air-permeable felt with the same cutting area on the surface of the glue absorption cloth.
(2) And sticking vacuum bag sealing rubber strips along the upper inner circle and the lower inner circle of the upper die and the lower die.
(3) Cutting the vacuum bag film, covering the air-permeable felt, adhering two ends of the vacuum bag film to the sealing adhesive tape, compacting, and reserving a polytetrafluoroethylene tube for vacuumizing.
(4) Vacuumizing and pre-pressing in a furnace, wherein the temperature is set to be 50 ℃, and the pre-pressing time is more than or equal to 4 hours.
8. Second prepreg lay-up
(1) And after the first pre-pressing is finished, removing the vacuum bag film, the breathable felt and the adhesive absorption cloth, and performing second pre-dipping laying.
(2) And (3) carrying out prepreg paving on the 8 th layer, the 9 th layer, the 90 th layer, the 10 th layer, the 45 th layer, the 11 th layer, the 0 th layer, the 12 th-45 th layer, the 13 th layer, the 0 th layer, the 14 th layer and the 15 th layer at 0 degree, wherein the paving method and requirements can refer to the first prepreg paving.
9. Upper and lower die assembly
(1) And after the second prepreg laying is finished, closing the upper and lower templates, positioning by using the positioning pin, and fastening the closed upper and lower templates by using the screw.
(2) Gaps at the die assembling surfaces of the upper die and the lower die are filled and filled by using prepreg, so that no obvious pits are generated during subsequent heating and curing.
10. Third prepreg ply
And (3) carrying out die assembly on the 16 th-45-degree prepreg laying layer and the 17 th 0-degree prepreg laying layer. Starting from the initial point of the upper template laying, finishing the initial point of the lower template laying, and carrying out 16 th and 17 th layers of prepreg laying.
11. Vacuumizing bag for vacuumizing
(1) After the third laying is finished, cutting the glue absorption cloth with the same size as the molding surface of the upper die and the lower die to cover the surface of the laid prepreg, and covering the air-permeable felt with the same cutting area on the surface of the glue absorption cloth.
(2) And sticking vacuum bag sealing rubber strips along the upper inner circle and the lower inner circle of the upper die and the lower die.
(3) Cutting the vacuum bag film, covering the air-permeable felt, adhering two ends of the vacuum bag film to the sealing adhesive tape, compacting, and reserving a polytetrafluoroethylene tube for vacuumizing.
12. Heating and pressurizing in autoclave for curing
And (3) transferring the laminated composite skirt and the composite skirt forming tool into an autoclave, connecting a vacuumizing suction nozzle with a reserved vacuum tube, opening a vacuum pump to vacuumize, closing an autoclave sealing door, and heating and boosting to cure. The curing system is as follows: room temperature → 130 ℃/2h → 160 ℃/4h → 60 ℃, the pressure in the autoclave is 0.1MPa → 2.8MPa/11.5h → 0.1MPa, the pressure in the processes of temperature rise and heat preservation is 2.8MPa, the temperature rise rate is 0.5 ℃/min, the pressure rise rate is 0.05MPa/min, the temperature drop rate is 0.6 ℃/min, and the pressure drop rate is 0.025 MPa/min.
13. Composite skirt machining machine
And (4) machining the cured composite skirt forming tool of the composite skirt band on a vertical lathe to enable the inner diameter size of the composite skirt to meet the design requirement.
14. Demoulding of composite skirt
Transferring the composite skirt and the composite skirt forming tool after machining to a demoulding area, symmetrically assembling four lifting rings in hole positions corresponding to an upper template, assembling hanging straps in the lifting rings after screwing, taking down screws for fastening the upper template and the lower template by the composite skirt forming tool, separating the upper template of the forming tool from one end of the composite skirt by using a crane and the hanging straps, reversely jacking and inserting the screws, separating the other end of the composite skirt from the lower template by using inserts on the lower template of the forming tool, finally completing demoulding of the composite skirt, and cleaning the existing burrs and the like by using abrasive paper.
The above is only a preferred embodiment of the present invention, and it should be noted that the above preferred embodiment should not be considered as limiting the present invention, and the protection scope of the present invention should be subject to the scope defined by the claims. It will be apparent to those skilled in the art that various modifications and adaptations can be made without departing from the spirit and scope of the invention, and these modifications and adaptations should be considered within the scope of the invention.
Claims (10)
1. A method for forming a special-shaped composite skirt of a solid rocket engine is characterized by comprising the following steps:
s1, assembling a forming tool and cleaning the surface: disassembling an upper template and a lower template of a forming tool with a T-shaped forming surface in section and cleaning the surfaces of the upper template and the lower template;
s2, prepreg laying and prepressing before mold closing: respectively and completely covering the cut multilayer prepreg on the molding surfaces of an upper template and a lower template with L-shaped molding surfaces in cross section according to a design angle, and vacuumizing by adopting a vacuumizing device;
s3, die assembly and prepreg laying after die assembly: closing and pressing the upper and lower templates after laying by using a crane, and then laying prepreg on the inner circle of the composite skirt barrel section again until laying is finished;
s4, curing and forming: transferring the composite skirt with the vacuumizing device and the forming tool into an autoclave, curing the composite skirt at a designed temperature and pressure, and vacuumizing at the same time;
s5, machining: machining the inner circle of the composite skirt cylinder section to enable the size of the inner circle to meet the requirement;
s6, demolding and surface cleaning: separating an upper template, a lower template and the composite skirt of the composite skirt forming tool, and cleaning burrs and burrs on the surface of the composite skirt after the separation is finished, thereby finally obtaining the composite skirt with the T-shaped section.
2. The method for forming a shaped composite skirt of a solid rocket engine as recited in claim 1, wherein in said step S1, a plurality of inserts are assembled in each of the upper and lower templates, and a plurality of grooves are formed on the forming surface of the lower template adjacent to the inserts.
3. The method of claim 1, wherein in step S1, the surface of the forming tool is cleaned with a piece of non-woven paper and ethyl acetate, and then the forming surfaces of the upper and lower forms are attached with a piece of release fabric.
4. The method for molding the shaped composite skirt of the solid rocket engine according to claim 1, wherein the pre-prepreg laying and pre-pressing step before mold clamping in step S2 comprises:
s21, preheating the forming tool or brushing a layer of adhesive on the forming surface;
s22, carrying out first laying of the prepreg and ensuring complete compaction;
s23, after the first layering is finished, vacuumizing by using a vacuumizing device;
and S24, after the first pre-pressing is finished, removing the vacuum extractor, and carrying out secondary prepreg laying until the laying is finished.
5. The method for forming the shaped composite skirt of the solid rocket engine according to claim 1, wherein the step S2 of evacuating with an evacuating device comprises the following steps: cutting the adhesive absorption cloth with the same size as the molding surfaces of the upper and lower templates to cover the surface of the prepreg, cutting the air felt with the same area to cover the surface of the adhesive absorption cloth, adhering vacuum bag sealing adhesive tapes along the upper and lower inner circles of the upper and lower templates, cutting a vacuum bag film, covering the air felt, adhering two ends of the vacuum bag film on the sealing adhesive tapes, compacting, reserving a polytetrafluoroethylene tube for vacuumizing at the same time, and vacuumizing and pre-pressing in a furnace.
6. The method for forming the shaped composite skirt of the solid rocket engine according to claim 5, wherein the temperature of the furnace is set to 50 ± 5 ℃ and the pre-pressing time is not less than 4 h.
7. The method for molding a solid rocket engine profiled composite skirt according to claim 1, wherein in step S3, the gap between the upper and lower mold plates at the joint surface is filled with prepreg after the mold is closed.
8. The method for forming a shaped composite skirt for a solid rocket engine as recited in claim 1, wherein in said step S4, the curing conditions are as follows: room temperature → 130 plus or minus 5 ℃/2h → 160 plus or minus 5 ℃/4h → 60 plus or minus 5 ℃, the pressure in the autoclave is 0.1 plus or minus 0.02MPa → 2.8 plus or minus 0.2MPa/11.5h → 0.1 plus or minus 0.02MPa, the pressure in the processes of temperature rise and heat preservation is 2.8 plus or minus 0.2MPa, the temperature rise rate is 0.5 ℃/min, the pressure rise rate is 0.05MPa/min, the temperature reduction rate is 0.6 ℃/min, and the pressure reduction rate is 0.025 MPa/min.
9. The method for forming the special-shaped composite skirt of the solid rocket engine according to claim 1, wherein in step S5, the upper template is separated from one end of the composite skirt by a crane and a sling, and the other end of the composite skirt is separated from the lower template by an insert on the lower template of a forming tool, so as to finally complete the demolding of the composite skirt.
10. The method for forming the irregular composite skirt of the solid rocket engine according to claim 1, wherein the prepreg laid on the flange edges of the upper and lower templates is evenly cut into small strips along the fiber direction by a putty knife, and the prepreg on the forming surfaces of the flange edges of the upper and lower templates is compacted by the putty knife.
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