CN112318898B - Thermal protection cabin section, RTM (resin transfer molding) method and female die thereof - Google Patents
Thermal protection cabin section, RTM (resin transfer molding) method and female die thereof Download PDFInfo
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- CN112318898B CN112318898B CN202011073708.1A CN202011073708A CN112318898B CN 112318898 B CN112318898 B CN 112318898B CN 202011073708 A CN202011073708 A CN 202011073708A CN 112318898 B CN112318898 B CN 112318898B
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- female die
- sided adhesive
- forming cavity
- demolding cloth
- protection cabin
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B29—WORKING OF PLASTICS; WORKING OF SUBSTANCES IN A PLASTIC STATE IN GENERAL
- B29C—SHAPING OR JOINING OF PLASTICS; SHAPING OF MATERIAL IN A PLASTIC STATE, NOT OTHERWISE PROVIDED FOR; AFTER-TREATMENT OF THE SHAPED PRODUCTS, e.g. REPAIRING
- B29C70/00—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts
- B29C70/04—Shaping composites, i.e. plastics material comprising reinforcements, fillers or preformed parts, e.g. inserts comprising reinforcements only, e.g. self-reinforcing plastics
- B29C70/28—Shaping operations therefor
- B29C70/40—Shaping or impregnating by compression not applied
- B29C70/42—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles
- B29C70/46—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs
- B29C70/48—Shaping or impregnating by compression not applied for producing articles of definite length, i.e. discrete articles using matched moulds, e.g. for deforming sheet moulding compounds [SMC] or prepregs and impregnating the reinforcements in the closed mould, e.g. resin transfer moulding [RTM], e.g. by vacuum
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/30—Mounting, exchanging or centering
- B29C33/308—Adjustable moulds
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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
- B29C33/00—Moulds or cores; Details thereof or accessories therefor
- B29C33/56—Coatings, e.g. enameled or galvanised; Releasing, lubricating or separating agents
- B29C33/68—Release sheets
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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
- B29C70/54—Component parts, details or accessories; Auxiliary operations, e.g. feeding or storage of prepregs or SMC after impregnation or during ageing
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F42—AMMUNITION; BLASTING
- F42B—EXPLOSIVE CHARGES, e.g. FOR BLASTING, FIREWORKS, AMMUNITION
- F42B15/00—Self-propelled projectiles or missiles, e.g. rockets; Guided missiles
- F42B15/34—Protection against overheating or radiation, e.g. heat shields; Additional cooling arrangements
Abstract
The invention relates to the technical field of forming of lipid-based thermal protection materials, in particular to a thermal protection cabin section, an RTM forming method and a female die thereof. The RTM forming method is characterized in that the front end of a forming cavity of a female die is pre-occupied before a die filling step to obtain a heat protection cabin section, the external dimension of the front end of the heat protection cabin section to be butted is smaller than that of the rear end of the heat protection cabin section to be butted at the front side, the transition from the front end to the rear end is smooth through the reduced pre-occupied dimension, the occurrence of reverse airflow step difference at the butted part of the two heat protection cabin sections can be effectively avoided after butt joint installation, the process is simple, the cost is low, the implementation of the existing forming method is not influenced, the RTM forming method is beneficial to popularization and use, the pre-occupied dimension can be conveniently adjusted as required, and the universality is strong. The female die is simple in structure, can be obtained by changing on the basis of the existing female die, does not influence the use and the cooperation of other parts in a forming die, can effectively reduce cost, can adjust the pre-occupied size conveniently according to needs, and is high in universality.
Description
Technical Field
The invention relates to the technical field of forming of lipid-based thermal protection materials, in particular to a thermal protection cabin section, an RTM forming method and a female die thereof.
Background
The supersonic and hypersonic cruise missile heat protection technology is a key technology for ensuring that a spacecraft is not overheated and burnt under the external heating environment of an ascending section and a reentry section, and is also a key technology for ensuring that a missile normally works under a pneumatic heating environment and a rocket engine normally works under a serious internal heating environment. The purpose of thermal protection is to design absorption or dissipation pneumatic heating, and the key technology for realizing thermal protection is selection of various heat-proof structures and materials.
The thermal protective material can be classified into a rigid thermal protective material and a flexible thermal protective material according to the rigidity and flexibility of the thermal protective material. The textile rigid thermal protection material mainly refers to a high-performance fiber material used as a thermal protection layer of various structural members and non-structural members working under high-temperature conditions or a fiber composite material formed by combining the high-performance fiber material with high-performance resin.
Resin Transfer Molding (RTM) is a process for injecting Resin into a closed mold to impregnate a reinforcing material and cure the Resin, and is a closed mold forming technique having characteristics of good appearance quality of the formed product, integral forming, low cost, and the like. The integral forming of the textile rigid thermal protection material can be realized by a resin transfer molding process, and the method is different from the defects of the traditional block forming, bonding, repairing and other processes, the inorganic phenolic aerogel thermal protection cabin section prepared by the forming method (see the Chinese invention patent with the publication number of CN110978568A and the name of 'a textile rigid thermal protection material and RTM forming method thereof') takes a low-density fiber prefabricated body as a reinforcement, phenolic resin as a matrix and a resin transfer molding technology as a forming process, the integrally formed thermal protection cabin section has low density and excellent heat insulation and heat resistance, shows specific performance stability to the changes of temperature, pressure and air current scouring, and is a new-generation thermal protection cabin section product.
For this new generation of thermal protection deck section products, the butt joints (butt end outer profiles) of the butted protection deck sections are theoretically uniform in size, but due to the curing shrinkage characteristics of the phenolic resin, the textile rigid thermal protection deck sections are deformed to different degrees after molding. After assembly, in the flight direction, if the external size of the rear end of the textile rigid heat protection cabin section positioned on the front side is smaller than the size of the front end of the textile rigid heat protection cabin section (the contraction quantity of the rear end of the front side heat protection cabin section is larger than that of the front end of the rear side heat protection cabin section), the butt joint of the two sections can generate an inverse airflow step difference, and the inverse airflow step difference can generate adverse effects on the flight of the supersonic speed and hypersonic speed cruise missile.
Disclosure of Invention
Technical problem to be solved
The invention aims to provide an RTM (resin transfer molding) method for a thermal protection cabin segment, the prepared thermal protection cabin segment can effectively avoid the occurrence of a reverse airflow step, the process is simple, the cost is lower, the implementation of the existing forming method is not influenced, the popularization and the use are facilitated, the pre-occupied size can be conveniently adjusted according to needs, and the universality is strong.
A second object of the present invention is to provide a thermal protection cabin section, the outer dimension of the front end of which is smaller than the theoretical value, and which can prevent the occurrence of a reverse airflow step when butt-jointed with the rear end of the thermal protection cabin section located at the front side (in the flight direction).
The third purpose of the invention is to provide a heat protection cabin section forming female die which is simple in structure, can be obtained by changing the existing female die, does not influence the use and the matching of other parts in a forming die, can effectively reduce the cost, can conveniently adjust the pre-occupied size according to the needs and has strong universality.
(II) technical scheme
In order to achieve the first object, in a first aspect, the present invention provides a method for RTM molding of a thermal protection cabin segment, including a mold filling step, a glue injection step, and a curing step, wherein before the assembling step, a pre-occupation treatment is performed on a front end of a molding cavity of a female mold, and the pre-occupation treatment includes the following steps:
preparing single-sided adhesive demolding cloth with corresponding quantity and size according to the radial size and the axial size pre-occupied by the molding cavity, wherein the size of each layer of single-sided adhesive demolding cloth in the axial direction of the molding cavity is different;
the method comprises the following steps of attaching a plurality of single-sided adhesive demolding cloth to the front end of a forming cavity of a female die in a layered manner, sequentially attaching the single-sided adhesive demolding cloth from small to large according to the size of the single-sided adhesive demolding cloth in the axial direction of the forming cavity when the single-sided adhesive demolding cloth is attached in the layered manner, after the attaching is completed, covering the front end of the forming cavity of the female die on the single-sided adhesive demolding cloth in the circumferential direction of the forming cavity of the female die, aligning the front end of each layer of the single-sided adhesive demolding cloth with the front end of the forming cavity of the female die, and increasing the extension degree of the rear end in the axial direction of the forming cavity layer by layer.
Preferably, before the single-sided release cloth with the adhesive is attached, the area of the forming cavity to which the single-sided release cloth with the adhesive is attached is subjected to sand blasting, and the non-sand blasting area of the forming cavity is subjected to shielding treatment.
Preferably, after the sandblasting is completed, the sandblasted area is cleaned of impurities with acetone or alcohol, and then the mask of the non-sandblasted area is removed.
Preferably, masking of the non-blasted area is performed with scotch tape.
Preferably, the thickness of each layer of single-sided adhesive release cloth is 0.1 mm.
Preferably, the extension lengths of the rear ends of the adjacent layers of the single-sided adhesive-carrying demolding cloth in the axial direction of the forming cavity are different by 8-10 mm.
In order to achieve the second object, in a second aspect, the invention provides a thermal protection cabin section, which is manufactured by adopting an RTM (resin transfer molding) method of any one thermal protection cabin section.
In order to achieve the third object of the present invention, in a third aspect, the present invention provides a female die for forming a thermal protection cabin section, wherein a pre-occupying part is arranged at a front end of a forming cavity of the female die, the pre-occupying part includes a plurality of layers of single-sided tape stripping cloth, a front end of each layer of single-sided tape stripping cloth is aligned with a front end of the forming cavity, an extending dimension of a rear end of each layer of single-sided tape stripping cloth in an axial direction of the forming cavity is different, and the extending dimension increases from an inner layer to an outer layer.
Preferably, the female die comprises a plurality of female die modules, and the front end of the inner wall of each female die module is provided with a pre-occupying part module;
when the female die modules are assembled around the central axis of the female die to form a forming cavity matched with the outer profile of the heat protection cabin section, the pre-occupying part modules are assembled to form a pre-occupying part.
Preferably, the thickness of each layer of single-sided adhesive release cloth is 0.1 mm; and/or
The extension length difference of the rear end of the single-sided adhesive-carrying demolding cloth of the adjacent layer in the axial direction of the forming cavity is 8-10 mm.
(III) advantageous effects
The technical scheme of the invention has the following advantages: according to the RTM forming method for the thermal protection cabin section, provided by the invention, the front end of the forming cavity of the female die is pre-occupied before the die filling step to obtain the thermal protection cabin section, the external dimension of the front end of the thermal protection cabin section to be butted is smaller than that of the rear end of the thermal protection cabin section to be butted, the front end and the rear end are smoothly transited by the reduced dimension of the pre-occupied position, the occurrence of reverse airflow step difference at the butted part of the two thermal protection cabin sections can be effectively avoided after the butt joint installation, the process is simple, the cost is lower, the implementation of the existing forming method is not influenced, the RTM forming method is beneficial to popularization and use, the pre-occupied dimension can be conveniently adjusted according to needs, and the universality is strong.
The heat protection cabin section forming female die provided by the invention has the advantages that the front end of the forming cavity of the female die is provided with the pre-occupying part, the pre-occupying part comprises a plurality of layers of single-sided adhesive demolding cloth, the front end of each layer of single-sided adhesive demolding cloth is aligned with the front end of the forming cavity, the extension sizes of the rear ends of the single-sided adhesive demolding cloth in the axial direction of the forming cavity are different and are increased layer by layer from the inner layer to the outer layer, the external size of the front end of the heat protection cabin section formed by the female die is smaller than the external size of the rear end of the heat protection cabin section to be butted at the front side, the reduced size of the pre-occupying part is smooth in transition from the front end to the rear end, the butt joint of the two sections of heat protection cabin sections can be effectively prevented from generating reverse airflow step difference after the butt joint installation, the structure is simple, the pre-occupying part can be obtained by changing on the basis of the existing female die, the use and the matching of other parts in the forming die are not influenced, the cost can be effectively reduced, and the pre-occupying size can be conveniently adjusted according to the needs, the universality is strong.
The external size of the front end of the thermal protection cabin section provided by the invention is smaller than a theoretical value, and when the thermal protection cabin section is butted with the rear end of the thermal protection cabin section positioned on the front side (in the flight direction), the reverse airflow step difference can be avoided.
Drawings
The drawings of the present invention are provided for illustrative purposes only, and the proportion and the number of the components in the drawings do not necessarily correspond to those of an actual product.
FIG. 1 is a schematic half-section view of a female mold in accordance with one embodiment of the present invention;
FIG. 2 is an enlarged schematic view of section A of FIG. 1;
FIG. 3 is a front end schematic view of another cavity block in accordance with an embodiment of the invention;
FIG. 4 is a schematic structural view of a heat shield section according to one embodiment of the present invention;
fig. 5 is an enlarged schematic view of a portion B of fig. 4.
In the figure: 1: a female die; 11: an upper female die block; 12: a lower female die block; 13: a left female die block; 14: a right female die block;
2: a pre-occupation part; 21: an upper pre-occupation part module; 22: a lower pre-occupation part module; 23: a left pre-occupation part module; 24: and the right pre-occupation part module.
3. A thermal protection bay section;
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. All other embodiments, which can be obtained by a person skilled in the art without any inventive step based on the embodiments of the present invention, are within the scope of the present invention.
The front end in the invention refers to the end located at the front side in flight, and the heat protection cabin section located at the front side refers to the heat protection cabin section located at the front side in flight.
Example one
Referring to fig. 1 to 3, in a female mold 1 of a thermal protection cabin section forming mold according to an embodiment of the present invention, a pre-positioning portion 2 is provided at a front end of a forming cavity of the female mold 1, the pre-positioning portion 2 includes a plurality of layers of single-sided tape stripping cloth, for example, two layers, three layers, four layers, five layers, six layers, seven layers, eight layers, nine layers, and the like, a front end of each layer of single-sided tape stripping cloth is aligned with a front end of the cavity, and extension dimensions of a rear end of each layer of single-sided tape stripping cloth in an axial direction of the cavity are different and increase from an inner layer to an outer layer.
When the female die 1 is used, the contour dimension of the outer surface of the area covered by the front-end pre-occupation part 2 of the formed thermal protection cabin section is smaller than a theoretical value so as to offset butt joint reverse airflow tolerance generated by deformation of the front-side thermal protection cabin section butted with the front end of the thermal protection cabin section, and when the front end of the thermal protection cabin section formed by the female die 1 is butted with the rear end of the thermal protection cabin section positioned on the front side (in the flight direction), the outer diameter of the front end of the rear-side thermal protection cabin section is smaller than the outer diameter of the rear end of the front-side thermal protection cabin section, so that reverse airflow step difference at the butted part of the two thermal protection cabin sections is avoided.
In some preferred embodiments, the female mold 1 comprises a plurality of female mold modules, and the front end of the inner wall of each female mold module is provided with a pre-occupying part module. When a plurality of female die modules are assembled around the central axis of the female die 1 to form a cavity matched with the outer profile of the heat protection cabin section, a plurality of pre-occupying part modules are assembled to form a pre-occupying part 2.
In a particular embodiment, seen in fig. 3, the female mould 1 comprises four female mould blocks, respectively an upper female mould block 11, a lower female mould block 12, a left female mould block 13 and a right female mould block 14, the inner walls of the upper female die module 11, the lower female die module 12, the left female die module 13 and the right female die module 14 are correspondingly coated with a pre-occupying part module, which is an upper pre-occupying part module 21, a lower pre-occupying part module 22, a left pre-occupying part module 23 and a right pre-occupying part module 24 respectively, after the assembly is finished, the upper female die module 11, the lower female die module 12, the left female die module 13 and the right female die module 14 form a female die in a conical cylinder shape around the central axis of the female die, the inner side of the female die is provided with a forming cavity matched with the outer profile of the heat protection cabin section, meanwhile, the upper preempt section module 21, the lower preempt section module 22, the left preempt section module 23, and the right preempt section module 24 are assembled into the preempt section 2. The mode of piecemeal equipment, the installation of convenient pre-occupation portion is pasted and is covered, also makes the dismantlement of the installation of bed die when the shaping simultaneously.
In a preferred embodiment, the thickness of each layer of single-sided adhesive release cloth is 0.1mm, so that a plurality of layers of overlapping smooth transition arrangement is facilitated, and the smooth transition forming of the front-end outer molded surface of the thermal protection cabin section is facilitated.
In a preferred embodiment, the pre-occupation part 2 has eight layers of single-sided adhesive release cloth, the thickness of each layer of single-sided adhesive release cloth is 0.1mm, that is, the pre-occupation size of the cavity in the radial direction is 0.8mm, and the external size of the front end of the heat protection cabin section positioned at the rear side can be still smaller than the external size of the front end of the deformed front-side heat protection cabin section in consideration of the shrinkage deformation of the front-side heat protection cabin section, so that the reverse airflow step difference at the butt joint part is avoided.
In a preferable embodiment, the extension lengths of the rear ends of the adjacent layers of the single-sided adhesive demolding cloth in the axial direction of the forming cavity are different by 8-10 mm, so that smooth transition forming of the front-end outer profile of the thermal protection cabin section is facilitated, and further reverse airflow step difference at the butt joint is avoided.
In a specific embodiment, the pre-occupied part 2 comprises eight layers of single-sided adhesive release cloth, the pre-occupied size of the pre-occupied part 2 in the axial direction of the forming cavity of the female die 1 is 80mm, the eight layers of single-sided adhesive release cloth are adopted, the size of the pre-occupied part 2 in the axial direction of the forming cavity is 10mm, 20mm, 30mm, 40mm, 50mm, 60mm, 70mm and 80mm sequentially from the inner layer to the outer layer, and the thickness of each layer of single-sided adhesive release cloth is 0.1 mm. The front ends of the eight layers of single-sided adhesive-carrying demolding cloth are aligned with the front end of the female die 1, and the rear ends of the eight layers of single-sided adhesive-carrying demolding cloth start from the second layer from inside to outside, and each layer is 10mm more than the previous layer.
In another specific embodiment, referring to fig. 2, the pre-occupied part 2 comprises four layers of single-sided adhesive release cloth, the pre-occupied size of the pre-occupied part 2 in the axial direction of the forming cavity of the female die 1 is 37mm, the four layers of single-sided adhesive release cloth are adopted, the size of the pre-occupied part 2 in the axial direction of the forming cavity is 10mm, 19mm, 28mm and 37mm sequentially from the inner layer to the outer layer, and the thickness of each layer of single-sided adhesive release cloth is 0.1 mm. The front ends of the four layers of single-sided adhesive release cloth are aligned with the front end of the female die 1, and the rear ends of the four layers of single-sided adhesive release cloth start from the second layer from inside to outside, and each layer is 9mm more than the previous layer.
In the embodiment having a plurality of female mold blocks, each of which is coated with a single-sided adhesive release fabric, for example, if the single-sided adhesive release fabric of the pre-seating portion 2 has five layers with lengths of 15mm, 23mm, 31mm, 39mm, and 47mm in the axial direction, and the female mold 1 is composed of four female mold blocks, 20 pieces of single-sided adhesive release fabric are required, four pieces each having axial dimensions of 15mm, 23mm, 31mm, 39mm, and 47mm are required.
It should be noted that other structures of the thermal protection cabin section forming mold, such as a male mold, may be implemented by using the prior art, and are not described herein again.
Example two
The RTM method for forming a thermal protection cabin segment according to the second embodiment includes a mold filling step, a glue injection step, and a curing step, and performs pre-occupying treatment on a front end of a forming cavity of a female mold before the assembling step, where the pre-occupying treatment includes the following steps:
preparing single-sided adhesive demolding cloth with corresponding quantity and size according to the radial size and the axial size pre-occupied in the molding cavity as required, wherein the axial size of each layer of single-sided adhesive demolding cloth in the molding cavity is different.
The method comprises the following steps of attaching a plurality of single-sided adhesive demolding cloth to the front end of a forming cavity of a female die in a layered manner, sequentially attaching the single-sided adhesive demolding cloth from small to large according to the size of the single-sided adhesive demolding cloth in the axial direction of the forming cavity when the single-sided adhesive demolding cloth is attached in the layered manner, after the attaching is completed, covering the front end of the forming cavity of the female die on the single-sided adhesive demolding cloth in the circumferential direction of the forming cavity of the female die, aligning the front end of each layer of the single-sided adhesive demolding cloth with the front end of the forming cavity of the female die, and increasing the extension degree of the rear end in the axial direction of the forming cavity layer by layer. When the heat protection cabin section prepared by the method is assembled, the front end of the heat protection cabin section is butted with the rear end of the front side heat protection cabin section, and the outer diameter of the front end of the rear side heat protection cabin section is smaller than that of the rear end of the front side heat protection cabin section, so that reverse airflow step difference at the butted position of the two heat protection cabin sections is avoided.
In some preferred embodiments, before the single-sided adhesive release cloth is applied, the molding cavity area to be applied with the single-sided adhesive release cloth is subjected to sand blasting treatment, and the non-sand blasting area of the molding cavity is subjected to shielding treatment, so that the single-sided adhesive release cloth can be applied more firmly.
In some preferred embodiments, after the sand blasting is completed, the impurities in the sand blasting area are cleaned by acetone or alcohol, and then the shielding of the non-sand blasting area is removed, so that the impurities generated by the sand blasting can be effectively removed, and the sticking firmness of the single-sided adhesive release cloth is further improved.
In some preferred embodiments, the non-blasted area of the negative mold is masked with scotch tape.
In a specific embodiment, the method comprises the steps of:
a. carrying out sand blasting treatment on a 72mm area of the front end surface of the cabin section forming female die, and sticking a transparent adhesive tape on a non-sand blasting area for protection in the sand blasting process;
b. cutting single-sided adhesive-carrying demoulding cloth according to areas of 10mm, 19mm, 28mm, 37mm, 46mm, 55mm, 64mm and 73mm at the front end of the female die forming cavity, wherein the thickness of each layer of single-sided adhesive-carrying demoulding cloth is 0.1 mm;
c. cleaning a sand blasting area with the front end surface of 80mm by using acetone or alcohol;
d. and adhering the cut single-side adhesive-carrying demolding cloth to the front end face of the female die molding cavity, wherein the single-side adhesive-carrying demolding cloth with the width of 10mm, 19mm, 28mm, 37mm, 46mm, 55mm, 64mm and 73mm is adhered in sequence, and the front end of each single-side adhesive-carrying demolding cloth is aligned with the edge of the front end face of the female die molding cavity.
After the pre-occupied part is attached, the steps of mold filling, glue injection, curing and the like are performed, and it should be noted that the steps of mold filling, glue injection, curing and the like of the thermal protection cabin section are all the prior art and are not described herein again.
In some preferred embodiments, the pre-occupation treatment is performed, eight layers of single-sided adhesive release cloth are attached, the thickness of each layer of single-sided adhesive release cloth is 0.1mm, namely the pre-occupation size of the cavity in the radial direction is 0.8mm, and the external dimension of the front end of the heat protection cabin section positioned on the rear side can be still smaller than the external dimension of the front end of the deformed front side heat protection cabin section in consideration of the condition that the front side heat protection cabin section shrinks and deforms, so that reverse airflow step difference at the butt joint part is avoided.
Preferably, the extension length difference of the rear ends of the adjacent layers of the surface adhesive demolding cloth in the axial direction of the molding cavity is 8-10 mm, so that smooth transition molding of the front-end outer molding surface of the thermal protection cabin section is facilitated, and further counter-current step difference at the butt joint is avoided.
EXAMPLE III
Referring to fig. 4 and 5, the thermal protection deck section 3 provided in the third embodiment can be manufactured by using any one of the forming methods in the second embodiment, and the thermal protection deck section 3 includes a fiber preform in a cone-cylinder shape and a resin material compounded with the fiber preform. Preferably, the fiber preform is a multi-layer composite structure composed of fiber braided fabric, and the composite method can be any one of needle punching, lamination sewing and fine knitting puncturing. More preferably, the fiber woven fabric may be made of a quartz fiber woven fabric or a glass fiber woven fabric.
Referring to fig. 4 and 5, the dotted line is the theoretical location of the leading outer profile.
In summary, the forming method pre-occupies the front end of the female die, and the compressible characteristic of the fiber material is utilized to obtain the thermal protection cabin section, the external dimension of the front end of the thermal protection cabin section to be butted is smaller than the external dimension of the rear end of the thermal protection cabin section to be butted, the reduced dimension of the pre-occupied position is smoothly transited from the front end to the rear end, the occurrence of reverse airflow step difference at the butted part of the two thermal protection cabin sections can be effectively avoided after the thermal protection cabin section is butted and installed, the forming method is simple in process, the existing process is slightly changed, the implementation of the existing forming method is not influenced, the forming method is beneficial to popularization and use, the pre-occupied size can be conveniently adjusted as required, and the universality is strong. The female die is simple in structure, can be obtained by changing on the basis of the existing female die, does not influence the use and the cooperation of other parts in a forming die, can effectively reduce cost, can adjust the pre-occupied size conveniently according to needs, and is high in universality.
Finally, it should be noted that: the above examples are only intended to illustrate the technical solution of the present invention, but not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it will be understood by those of ordinary skill in the art that: each embodiment does not include only one independent technical solution, and in the case of no conflict between the solutions, the technical features mentioned in the respective embodiments can be combined in any way to form other embodiments which can be understood by those skilled in the art.
Furthermore, modifications may be made to the technical solutions described in the foregoing embodiments, or equivalents may be substituted for some of the technical features thereof, without departing from the scope of the present invention, and the essence of the corresponding technical solutions does not depart from the spirit and scope of the technical solutions of the embodiments of the present invention.
Claims (10)
1. The RTM forming method of the thermal protection cabin comprises a die filling step, a glue injection step and a curing step, and is characterized in that: before the assembling step, carrying out pre-occupation treatment on the front end of a forming cavity of a female die, wherein the pre-occupation treatment comprises the following steps:
preparing single-sided adhesive demolding cloth with corresponding quantity and size according to the radial size and the axial size pre-occupied by the forming cavity, wherein the size of each layer of single-sided adhesive demolding cloth in the axial direction of the forming cavity is different;
the method comprises the steps of adhering a plurality of single-side adhesive demolding cloth at the front end of a forming cavity of a female die in a layering manner, adhering the single-side adhesive demolding cloth at the front end of the forming cavity of the female die in sequence from small to large according to the size of the single-side adhesive demolding cloth in the axial direction of the forming cavity, and after adhering is completed, covering the front end of the forming cavity of the female die by the single-side adhesive demolding cloth in the circumferential direction of the forming cavity of the female die, aligning the front end of the single-side adhesive demolding cloth with the front end of the forming cavity of the female die in each layer, and increasing the extension degree of the forming cavity in the axial direction layer by layer at the rear end.
2. The RTM molding method according to claim 1, wherein: before the single-sided adhesive demolding cloth is attached, sand blasting is carried out on a molding cavity area needing to be attached with the single-sided adhesive demolding cloth, and shielding treatment is carried out on a non-sand blasting area of the molding cavity.
3. The RTM molding method according to claim 2, wherein: after the sand blasting is finished, cleaning the impurity of the sand blasting area by using acetone or alcohol, and then removing the shielding of the non-sand blasting area.
4. RTM molding method according to claim 2 or 3, characterized in that: and shielding the non-sandblasting area by using a transparent adhesive tape.
5. The RTM molding method according to claim 1, wherein: the thickness of each layer of the single-sided adhesive demolding cloth is 0.1 mm.
6. The RTM molding method according to claim 1, wherein: and the extension length difference of the rear ends of the adjacent layers of the single-sided adhesive demolding cloth in the axial direction of the molding cavity is 8-10 mm.
7. A heat protection capsule segment, characterized in that it is obtained by means of RTM-forming according to any of claims 1 to 6.
8. A female die for forming a thermal protection cabin section based on a RTM forming method is characterized in that: the front end of a forming cavity of the female die is provided with a pre-occupying part, the pre-occupying part comprises a plurality of layers of single-sided adhesive demolding cloth, the front end of each layer of single-sided adhesive demolding cloth is aligned with the front end of the female die, the extending sizes of the rear ends of the single-sided adhesive demolding cloth in the axial direction of the forming cavity are different, and the single-sided adhesive demolding cloth is gradually increased from the inner layer to the outer layer.
9. The negative mold as claimed in claim 8, wherein: the front end of the inner wall of each female die module is provided with a pre-occupying part module;
when the female die modules are assembled around the central axis of the female die to form a forming cavity matched with the outer profile of the heat protection cabin section, the pre-occupying part modules are assembled to form a pre-occupying part.
10. The negative mold as claimed in claim 8 or 9, wherein: the thickness of each layer of the single-sided adhesive demolding cloth is 0.1 mm; and/or
The extension length of the rear end of the single-side adhesive-carrying demolding cloth of the adjacent layer in the axial direction of the forming cavity is different from 8-10 mm.
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| CN202011073708.1A CN112318898B (en) | 2020-09-30 | 2020-09-30 | Thermal protection cabin section, RTM (resin transfer molding) method and female die thereof |
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| CN202011073708.1A CN112318898B (en) | 2020-09-30 | 2020-09-30 | Thermal protection cabin section, RTM (resin transfer molding) method and female die thereof |
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| CA2403251C (en) * | 2000-03-14 | 2011-04-26 | Ossur Hf | Composite elastic material |
| EP2047971B1 (en) * | 2007-10-09 | 2013-12-04 | Saab Ab | Method for manufacturing beams of fiber-reinforced composite material |
| ATE494129T1 (en) * | 2008-10-24 | 2011-01-15 | Faurecia Innenraum Sys Gmbh | METHOD FOR PRODUCING MOLDED SKIN |
| CN102873884B (en) * | 2012-09-13 | 2014-10-15 | 沈阳飞机工业（集团）有限公司 | Composite material combined core mold compensation pad process |
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| CN110524915A (en) * | 2019-09-05 | 2019-12-03 | 航天特种材料及工艺技术研究所 | A kind of socket forming frock and socket forming method |
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