CN214645113U - Special-shaped section composite material missile wing compression molding die for belt metal support lug - Google Patents
Special-shaped section composite material missile wing compression molding die for belt metal support lug Download PDFInfo
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- CN214645113U CN214645113U CN202120252510.3U CN202120252510U CN214645113U CN 214645113 U CN214645113 U CN 214645113U CN 202120252510 U CN202120252510 U CN 202120252510U CN 214645113 U CN214645113 U CN 214645113U
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- missile wing
- composite material
- metal support
- compression molding
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- 239000002184 metal Substances 0.000 title claims abstract description 51
- 239000002131 composite material Substances 0.000 title claims abstract description 45
- 238000000748 compression moulding Methods 0.000 title claims abstract description 28
- 239000000463 material Substances 0.000 claims abstract description 8
- 238000000465 moulding Methods 0.000 claims abstract description 5
- 229920001971 elastomer Polymers 0.000 claims description 4
- 239000005060 rubber Substances 0.000 claims description 4
- 229920002635 polyurethane Polymers 0.000 claims description 3
- 239000004814 polyurethane Substances 0.000 claims description 3
- VYPSYNLAJGMNEJ-UHFFFAOYSA-N Silicium dioxide Chemical compound O=[Si]=O VYPSYNLAJGMNEJ-UHFFFAOYSA-N 0.000 claims description 2
- 239000000741 silica gel Substances 0.000 claims description 2
- 229910002027 silica gel Inorganic materials 0.000 claims description 2
- 239000000835 fiber Substances 0.000 abstract description 4
- 238000003754 machining Methods 0.000 abstract description 4
- 206010066054 Dysmorphism Diseases 0.000 abstract description 2
- 230000009286 beneficial effect Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000004519 manufacturing process Methods 0.000 description 3
- 238000005299 abrasion Methods 0.000 description 2
- 238000004140 cleaning Methods 0.000 description 2
- 239000011347 resin Substances 0.000 description 2
- 229920005989 resin Polymers 0.000 description 2
- 239000011157 advanced composite material Substances 0.000 description 1
- 239000003795 chemical substances by application Substances 0.000 description 1
- 239000011162 core material Substances 0.000 description 1
- 238000001723 curing Methods 0.000 description 1
- 238000005520 cutting process Methods 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000005489 elastic deformation Effects 0.000 description 1
- 239000003292 glue Substances 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 239000007769 metal material Substances 0.000 description 1
- 229920001296 polysiloxane Polymers 0.000 description 1
- 238000003825 pressing Methods 0.000 description 1
- 238000005488 sandblasting Methods 0.000 description 1
- 239000012945 sealing adhesive Substances 0.000 description 1
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- Moulds For Moulding Plastics Or The Like (AREA)
- Casting Or Compression Moulding Of Plastics Or The Like (AREA)
Abstract
The utility model relates to a dysmorphism cross-section combined material missile wing compression molding mould for taking metal journal stirrup. This forming die includes: the upper die is provided with a first positioning hole and a first cavity for molding the composite material; the lower die is provided with a second positioning hole, a limiting groove for limiting the metal support lug and a second cavity for forming the composite material; the guide post is inserted into the first positioning hole and the second positioning hole; when the upper die and the lower die are closed, the first cavity, the second cavity and the limiting groove are formed together to form a cavity for forming the metal lug and the composite material into the missile wing. Through the technical scheme, the missile wing surface can be manufactured through one-time compression molding of the mold cavity formed by the upper mold and the lower mold, the molded surface precision and the surface quality of the missile wing can be guaranteed, machining is not needed, the fiber of the composite material wing surface is prevented from being cut off, and then the strength of the missile wing is guaranteed. And simple structure, convenient operation.
Description
Technical Field
The utility model relates to a combined material production facility field, concretely relates to dysmorphism cross-section combined material missile wing compression molding mould for taking metal journal stirrup.
Background
Lightening is an important trend in the development of advanced missile weapons. At present, the main measures for realizing the lightening are to apply a large amount of advanced composite materials and establish a missile key composite material design and manufacturing technical system.
The missile wing is a main bearing structural part of the missile body, the main function of the missile wing is to generate lift force, and therefore sufficient strength and rigidity of the missile wing must be ensured. The metal material missile wing meets the requirements of strength and rigidity, but has heavy weight. The composite material has the advantages of excellent specific strength, specific rigidity, fatigue resistance, rigidity designability and the like, and is widely applied to missile structural parts. Therefore, compared with a metal missile wing, the missile wing made of the composite material can reduce the weight by more than 40%, the weight of the on-hook missile can be greatly reduced, and the range and the effective load can be increased.
Because the whole appearance of the missile wing is the pneumatic profile, the pneumatic profile of the missile wing cannot be ensured by adopting a single-side profile die. In order to solve the problem, a more reasonable technical scheme is required to be provided, so that the missile wing made of the composite material can be effectively molded.
SUMMERY OF THE UTILITY MODEL
The utility model provides a special-shaped cross-section combined material missile wing compression molding mould for taking metal journal stirrup, shedder have the use inconvenient, and damage the problem of mandrel easily.
In order to realize the above effect, the utility model discloses a technical scheme does:
a special-shaped section composite material missile wing compression molding mould for taking metal journal stirrup includes:
the upper die is provided with a first positioning hole and a first cavity for molding the composite material;
the lower die is provided with a second positioning hole matched with the first positioning hole, a limiting groove used for limiting the metal support lug and a second cavity used for forming the composite material; and
the guide post is inserted into the first positioning hole and the second positioning hole;
when the upper die and the lower die are closed, the first cavity, the second cavity and the limiting groove are formed into a cavity for forming the metal lug and the composite material into the missile wing.
In a possible design, the metal support lug structure further comprises a positioning shaft inserted into the through hole of the metal support lug, and the positioning shaft is movably connected with the lower die so as to be close to or far away from the limiting groove.
In one possible design, the lower die is provided with a positioning seat, the upper die is provided with an avoiding groove for avoiding the positioning seat, and the positioning shaft is movably connected to the positioning seat.
In one possible design, the lower die comprises a base and a die holder, the die holder is located between the base and the upper die, the limiting groove and the second cavity are arranged on the die holder, the length of the base is larger than that of the die holder, and the part of the base, which exceeds the die holder, is provided with the second positioning hole.
In a possible design, a first guide sleeve is arranged in the first positioning hole, a second guide sleeve is arranged in the second positioning hole, and the guide column is embedded in the second guide sleeve.
In one possible embodiment, the material of the first guide sleeve and the second guide sleeve is rubber, polyurethane or silicone.
In one possible design, the forming die further comprises a screw;
the upper die is provided with a screw hole, and the screw is arranged in the screw hole so as to push the upper die away from the lower die when the screw is screwed down.
In a possible design, the screw holes are configured in a plurality and are arranged at intervals on the upper die, and the screws are configured in a number matched with the screw holes.
Compared with the prior art, the beneficial effects of the utility model are that:
through the technical scheme, the missile wing surface can be manufactured through one-time compression molding of the mold cavity formed by the upper mold and the lower mold, the profile precision and the surface quality of the missile wing can be guaranteed, machining is not needed, the fiber of the composite material wing surface (formed by multiple layers of composite materials) is prevented from being cut off, and then the strength of the missile wing is guaranteed. And simple structure, convenient operation.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present invention, the drawings required to be used in the embodiments will be briefly described below, it should be understood that the following drawings only show some embodiments of the present invention, and therefore should not be considered as limiting the scope, and for those skilled in the art, other related drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a perspective view of a profiled cross-section composite missile wing compression molding mold provided by the disclosure and used for a metal lug in one embodiment;
FIG. 2 is a perspective view of a profiled cross-section composite missile wing compression molding die for a metal lug provided by the present disclosure in one embodiment with the upper die removed to reveal internal structure;
FIG. 3 is a top view of a profiled cross-section composite missile wing compression molding mold provided by the disclosure for a metal lug in one embodiment;
FIG. 4 is a top view of a profiled cross-section composite missile wing compression molding die for a metal lug provided by the present disclosure in one embodiment with the upper die removed to reveal internal structure;
FIG. 5 is a front view of a profiled cross-section composite missile wing compression molding die for a metal lug provided by the present disclosure in one embodiment;
FIG. 6 is a front view in cross section of a profiled composite missile wing compression molding die for a metal lug provided by the disclosure in one embodiment;
FIG. 7 is a side view cross-section of a profiled composite missile wing compression molding die for a metal lug provided by the disclosure in one embodiment.
In the above drawings, the meaning of each reference numeral is:
1-an upper die, 21-a base, 22-a die holder, 3-a guide column, 4-a positioning shaft, 51-a first guide sleeve, 52-a second guide sleeve, 6-a screw, 7-a composite material airfoil and 8-a metal support lug.
Detailed Description
The present invention will be further explained with reference to the drawings and the embodiments.
It should be noted that the description of the embodiments is provided to help understanding of the present invention, but the present invention is not limited thereto. Specific structural and functional details disclosed herein are merely illustrative of example embodiments of the invention. The present invention may, however, be embodied in many alternate forms and should not be construed as limited to the embodiments set forth herein.
The terminology used herein is for the purpose of describing particular embodiments only and is not intended to be limiting of example embodiments of the invention. As used herein, the singular forms "a", "an" and "the" are intended to include the plural forms as well, unless the context clearly indicates otherwise. It will be further understood that the terms "comprises," "comprising," "includes," and/or "including," when used herein, specify the presence of stated features, integers, steps, operations, elements, and/or components, but do not preclude the presence or addition of one or more other features, numbers, steps, operations, elements, components, and/or groups thereof.
It should also be noted that, in some alternative implementations, the functions/acts noted may occur out of the order noted in the figures. For example, two figures shown in succession may, in fact, be executed substantially concurrently, or the figures may sometimes be executed in the reverse order, depending upon the functionality/acts involved.
In the following description, specific details are provided to facilitate a thorough understanding of example embodiments. However, it will be understood by those of ordinary skill in the art that the example embodiments may be practiced without these specific details. For example, systems may be shown in block diagrams in order not to obscure the examples in unnecessary detail. In other instances, well-known processes, structures and techniques may be shown without unnecessary detail in order to avoid obscuring example embodiments.
According to the embodiment of the disclosure, a compression molding die for the profiled-section composite missile wing with the metal support lug is provided, and the compression molding die can combine the composite material with the metal support lug 8 to form the missile wing. Fig. 1 to 7 show one specific embodiment thereof.
Referring to fig. 1 to 7, the compression molding mold for the composite material missile wing with the special-shaped section and the metal support lug comprises an upper mold 1, a lower mold and a guide post 3. The upper die 1 is provided with a first positioning hole and a first cavity for molding the composite material. And the lower die is provided with a second positioning hole matched with the first positioning hole, a limiting groove used for limiting the metal support lug 8 and a second cavity used for forming the composite material. And the guide post 3 is used for being inserted into the first positioning hole and the second positioning hole. Thus, when the upper die 1 and the lower die are closed, the first cavity, the second cavity and the limiting groove are jointly formed into a cavity for forming the metal lug 8 and the composite material into the missile wing.
The specific working process is as follows: 1. cleaning, namely cleaning the upper die 1, the lower die and the guide column 3 and constructing a release agent; 2. preparing materials, namely cutting a composite material (namely resin-based fiber reinforced prepreg) to obtain a layer with a specific outline; numerical control machining is carried out to obtain an elastic wing metal lug 8 part; and (4) carrying out sand blasting treatment on the contact part of the metal support lug 8 part and the composite material airfoil 7. 3. Laying, namely laying prepreg layers layer by layer in a cavity formed by the lower die and the lower die, and vacuumizing and compacting the core material and the prepreg layer blank after the first layer and the subsequent every three layers of laying are laid, so that bubbles and gaps between the laid layers are reduced, and the bonding quality between the laid layers is improved; in the vacuumizing and pre-compacting process, a nonporous isolating film, a breathable felt and the like are sequentially covered on the surface of the blank, and finally the vacuum system is implemented after the vacuum bag and the rubber sealing adhesive tape are sealed. 4. Arranging a metal support lug 8, embedding the metal support lug 8 into the surface of the composite material airfoil part, and paving a glue film; after the prepreg below the metal support lug 8 is completely laid, fixing the metal support lug 8 on the lower die, and continuing to lay the prepreg until all the prepreg is completely laid; 5. assembling, namely after the blank body is laid, positioning the upper die 1 by using the guide columns 3, and closing the die, so that the accuracy of the die closing position is ensured; 6. curing, namely putting the die into a hot press, applying pressure, heating, and curing according to curing parameters of the resin; 7. and (5) demolding, namely separating the upper mold 1 from the lower mold, and taking out the molded missile wing to obtain the required finished part.
Through the technical scheme, the missile wing surface can be manufactured through one-time compression molding of the mold cavity formed by the upper mold 1 and the lower mold, the profile precision and the surface quality of the missile wing can be guaranteed, machining is not needed, the situation that fibers of the composite material wing surface 7 (formed by multiple layers of composite materials) are cut off is avoided, and then the strength of the missile wing is guaranteed. And simple structure, convenient operation.
In a possible design, referring to fig. 1 and 2, the compression molding die further includes a positioning shaft 4 inserted into the through hole of the metal support lug 8, and the positioning shaft 4 is movably connected with the lower die so as to be capable of approaching or departing from the limiting groove. Therefore, the position of the metal support lug 8 can be limited through the positioning shaft 4, and then the metal support lug 8 can be accurately positioned, so that the coaxiality requirement of the plurality of metal support lugs 8 is ensured. In this disclosure, the number of the metal support lugs 8 is 3, and therefore, 3 limiting grooves are provided to meet the production requirement. Therefore, the number of the limiting grooves and the length of the positioning shaft 4 can be flexibly set by a person skilled in the art according to the specification of the missile wing.
As an option, be equipped with the positioning seat on the lower mould, be equipped with on last mould 1 and be used for dodging the groove of dodging of positioning seat, location axle 4 movably connect in the positioning seat to can be close to the spacing groove and insert and locate in the through-hole of metal journal stirrup 8, realize then that the finished product quality to guaranteeing the missile wing is of value to the location and the limiting displacement of metal journal stirrup 8. Alternatively, one positioning shaft 4 may be directly inserted into the through holes of the plurality of metal lugs 8 without providing a positioning seat, which is not limited.
In an exemplary embodiment provided by the present disclosure, referring to fig. 2 and 4, the lower die includes a base 21 and a die holder 22, the die holder 22 is located between the base 21 and the upper die 1, the limiting groove and the second cavity are both disposed on the die holder 22, the length of the base 21 is greater than that of the die holder 22, and the portion of the base 21 beyond the die holder 22 is provided with the second positioning hole. In this way, the die holder 22 can be removed to facilitate demolding of the missile wing.
In one embodiment, referring to fig. 6, a first guide sleeve 51 may be disposed in the first positioning hole, a second guide sleeve 52 is disposed in the second positioning hole, and the guide post 3 is embedded in the second guide sleeve 52. In this way, the guide post 3 can be inserted into the first guide sleeve during mold clamping.
The second guide bush 52 is beneficial to keeping the position of the guide post 3 relative to the lower die, preventing the guide post 3 from inclining, playing a good role in positioning and guiding, and being beneficial to matching the upper die 1 and the lower die. In addition, the guide column 3 can be prevented from directly contacting with the lower die, and abrasion between the guide column and the lower die is reduced. Similarly, the arrangement of the first bushing can also reduce the abrasion between the guide column 3 and the upper die 1.
Specifically, the first guide sleeve 51 and the second guide sleeve 52 are made of rubber, polyurethane or silica gel. Thus, the guide post 3 can be firmly coupled to the upper mold 1 or the lower mold by elastic deformation of the first guide bush 51 and the second guide bush 52.
In one embodiment provided by the present disclosure, referring to fig. 1 to 7, the forming mold further includes a screw 6. The upper die 1 is provided with a screw hole, and the screw 6 is arranged in the screw hole so as to push the upper die 1 away from the lower die when the screw 6 is screwed down. Specifically, can twist into the screw that mould 1 corresponds with screw 6, and the lower terminal surface of screw 6 supports top lower mould upper surface this moment, continues to twist into screw 6 and can open up last mould 1, and all dismantlements of screw 6 afterwards can follow and take out the missile wing on the lower mould to the convenient drawing of patterns.
Further, the screw holes may be disposed in a plurality and spaced apart from each other in the upper mold 1. The screws 6 are arranged in a number corresponding to the screw holes. This increases the number of force application points, which is beneficial for smoothly pushing the upper mold 1 against the lower mold.
In the present disclosure, referring to fig. 1 and 3, four screw holes are provided and are respectively provided at corners of the upper mold 1. The screw 6 is the screw 6 with the specification of M12 x 80. In other embodiments, the number of the screw holes may be any suitable number, such as 2, 6, or 8, and the specification of the screw 6 may also be flexibly selected according to the specification of the upper die 1, which is not limited in this disclosure.
The above embodiments are just examples of the present invention, but the present invention is not limited to the above alternative embodiments, and those skilled in the art can obtain other various embodiments by arbitrarily combining the above embodiments, and any one can obtain other various embodiments by the teaching of the present invention. The above detailed description should not be taken as limiting the scope of the invention, which is defined in the following claims, and which can be used to interpret the claims.
Claims (8)
1. The utility model provides a special-shaped cross-section combined material missile wing compression molding mould for taking metal journal stirrup which characterized in that includes:
the upper die (1) is provided with a first positioning hole and a first cavity for molding the composite material;
the lower die is provided with a second positioning hole matched with the first positioning hole, a limiting groove used for limiting the metal support lug (8) and a second cavity used for forming the composite material; and
the guide post (3) is inserted into the first positioning hole and the second positioning hole;
when the upper die (1) and the lower die are closed, the first cavity, the second cavity and the limiting groove are formed into a die cavity for forming the metal support lug (8) and the composite material into the missile wing.
2. The compression molding die for the special-shaped section composite material missile wing with the metal support lug as claimed in claim 1, further comprising a positioning shaft (4) inserted into the through hole of the metal support lug (8), wherein the positioning shaft (4) is movably connected with the lower die so as to be close to or far away from the limiting groove.
3. The compression molding die for the special-shaped section composite material missile wing with the metal support lug as claimed in claim 2, wherein the lower die is provided with a positioning seat, the upper die (1) is provided with an avoidance groove for avoiding the positioning seat, and the positioning shaft (4) is movably connected to the positioning seat.
4. The compression molding die for the special-shaped section composite material missile wing with the metal support lug as claimed in claim 1, wherein the lower die comprises a base (21) and a die holder (22), the die holder (22) is located between the base (21) and the upper die (1), the limit groove and the second cavity are both arranged on the die holder (22), the length of the base (21) is greater than that of the die holder (22), and the part of the base (21) exceeding the die holder (22) is provided with the second positioning hole.
5. The compression molding die for the composite missile wing with the special-shaped section and the metal support lug as claimed in claim 1, wherein a first guide sleeve (51) is arranged in the first positioning hole, a second guide sleeve (52) is arranged in the second positioning hole, and the guide column (3) is embedded in the second guide sleeve (52).
6. The compression molding die for the profiled-section composite missile wing with the metal support lug as claimed in claim 5, wherein the material of the first guide sleeve (51) and the second guide sleeve (52) is rubber, polyurethane or silica gel.
7. The compression molding die for the profiled-section composite missile wing with the metal support lug as claimed in claim 1, wherein the molding die further comprises a screw (6);
the upper die (1) is provided with a screw hole, and the screw (6) is arranged in the screw hole so as to push the upper die (1) away from the lower die when the screw (6) is screwed down.
8. The compression molding die for the composite material missile wing with the special-shaped section and the metal support lug as claimed in claim 7, wherein the screw holes are configured to be multiple and arranged at intervals on the upper die (1), and the screws (6) are configured to be matched with the screw holes in number.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120252510.3U CN214645113U (en) | 2021-01-28 | 2021-01-28 | Special-shaped section composite material missile wing compression molding die for belt metal support lug |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202120252510.3U CN214645113U (en) | 2021-01-28 | 2021-01-28 | Special-shaped section composite material missile wing compression molding die for belt metal support lug |
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| Publication Number | Publication Date |
|---|---|
| CN214645113U true CN214645113U (en) | 2021-11-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202120252510.3U Active CN214645113U (en) | 2021-01-28 | 2021-01-28 | Special-shaped section composite material missile wing compression molding die for belt metal support lug |
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| CN (1) | CN214645113U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116945427A (en) * | 2023-09-20 | 2023-10-27 | 北京卓翼智能科技有限公司 | Carbon fiber missile wing compression molding die |
-
2021
- 2021-01-28 CN CN202120252510.3U patent/CN214645113U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116945427A (en) * | 2023-09-20 | 2023-10-27 | 北京卓翼智能科技有限公司 | Carbon fiber missile wing compression molding die |
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231022 Address after: No.1109, 11th floor, building 8, no.388, north section of Yizhou Avenue, hi tech Zone, Chengdu, Sichuan 610000 Patentee after: Chengdu Henghang Technology Co.,Ltd. Address before: Floor 1, 66 Fuqiang street, Tianfu New District, Chengdu, Sichuan 610000 Patentee before: Chengdu compound Valley Technology Co.,Ltd. |
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| TR01 | Transfer of patent right |