CN113432486A - Barrel structure of hollow multi-cavity composite material launching barrel and forming method thereof - Google Patents
Barrel structure of hollow multi-cavity composite material launching barrel and forming method thereof Download PDFInfo
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- CN113432486A CN113432486A CN202110526508.5A CN202110526508A CN113432486A CN 113432486 A CN113432486 A CN 113432486A CN 202110526508 A CN202110526508 A CN 202110526508A CN 113432486 A CN113432486 A CN 113432486A
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- inner cylinder
- barrel
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F41—WEAPONS
- F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
- F41F1/00—Launching apparatus for projecting projectiles or missiles from barrels, e.g. cannons; Harpoon guns
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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
- B29C70/342—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 isostatic pressure
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Composite Materials (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Moulding By Coating Moulds (AREA)
Abstract
The invention discloses a barrel structure of a hollow multi-cavity composite material launching barrel and a forming method thereof, belonging to the technical field of launching barrel structures. The hollow multi-cavity composite material launching tube has a tube body structure, is made of composite materials and comprises an inner tube body, an outer tube body and longitudinal ribs; the inner cylinder is embedded in the outer cylinder, the axial direction of the outer peripheral surface of the inner cylinder is connected with the axial direction of the inner peripheral surface of the outer cylinder through longitudinal ribs, and a gas flue is formed between the outer peripheral surface of the inner cylinder and the inner peripheral surface of the outer cylinder. The technical problems that in the prior art, a solid-structure barrel cannot be applied to thermal emission, a launch barrel is made of metal materials, the weight is heavy, the processing difficulty is high, the forming precision is low, the assembly is complex, and the manufacturing cost is high are solved. The cylinder body is made of composite materials, the whole weight is reduced, the inner cylinder body and the outer cylinder body are connected through the longitudinal ribs to form a fuel gas flue, the processing and the assembly are convenient, and the fuel gas flue can be applied to heat emission.
Description
Technical Field
The invention relates to the technical field of launch canister structures, in particular to a canister structure of a hollow multi-cavity composite launch canister suitable for a thermal-launched missile and a forming method thereof.
Background
The launching tube is used as an important component of missile weapons, is a special cylindrical device for storing, transporting and launching missiles, and has a gradually increasing trend in domestic and foreign applications.
At present, the launching tube is mostly applied to cold-launched missiles, the tube body structure of the launching tube adopts an inner tube body and a ring rib structure, or adopts an interlayer structure of the inner tube body, foam and an outer tube body, and the tube body adopting the solid structure can not be applied to heat launching.
In addition, the launching tube for the missile is made of metal materials, the weight of the launching tube made of metal materials is heavy, the processing difficulty of the metal materials is high, the forming precision is low, the assembly process is complex, the manufacturing cost is high, and the use in the later period is inconvenient.
Disclosure of Invention
The invention aims to provide a barrel structure of a hollow multi-cavity composite material launching barrel, which aims to solve the technical problems that in the prior art, a barrel adopting a solid structure cannot be applied to thermal launching, and the launching barrel is made of a metal material, so that the weight is heavy, the processing difficulty is high, the forming precision is low, the assembly process is complex, and the manufacturing cost is high.
The invention provides a barrel structure of a hollow multi-cavity composite material launching barrel, which is made of composite materials and comprises an inner barrel, an outer barrel and longitudinal ribs;
the inner cylinder is embedded in the outer cylinder, the axial direction of the outer peripheral surface of the inner cylinder is connected with the axial direction of the inner peripheral surface of the outer cylinder through longitudinal ribs, and a gas flue is formed between the outer peripheral surface of the inner cylinder and the inner peripheral surface of the outer cylinder.
Furthermore, the number of the longitudinal ribs is at least two, and the number of the gas flues corresponds to the number of the longitudinal ribs.
Furthermore, the cross section of the longitudinal rib is in any one of an I shape, a U shape, a square shape and a trapezoid shape.
Furthermore, the cross section of the inner cylinder body is any one of circular, square, rectangular and special-shaped, and the cross section of the outer cylinder body corresponds to that of the inner cylinder body.
The invention also provides a method for forming the barrel structure of the hollow multi-cavity composite material launching barrel, which comprises the following steps:
a. inner cylinder forming
Coating a release agent on the surface of an inner cylinder mould, respectively adopting high-temperature-resistant heat-proof functional prepreg and carbon fiber/epoxy structure prepreg, and winding and laying at 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design with the length direction of the inner cylinder mould as 0 degree direction, so that the value range of the forming thickness of the inner cylinder is between 5mm and 10 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mold, vacuumizing and compacting, then placing the inner cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature is between 120 and 180 ℃, the curing time is between 10 and 20 hours, and cleaning the surface auxiliary materials of the inner cylinder mold after curing;
b. longitudinal rib forming
Coating a release agent on the surface of a longitudinal rib mold, adopting carbon fiber/epoxy structure prepreg, taking the length direction of an inner cylinder body (100) as the 0-degree direction, and carrying out winding and laying at 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design to ensure that the value range of the forming thickness of the longitudinal rib is between 3mm and 10 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mould, vacuumizing and compacting, then placing the inner cylinder mould into a hot-pressing tank for heating, pressurizing and curing, wherein the value range of the curing temperature is 120-180 ℃, the value range of the curing time is 10-20 h, and cleaning the surface auxiliary materials of the longitudinal rib mould after curing;
c. shaping of gas flue
Coating a release agent on the surface of a gas flue mould, respectively adopting high-temperature-resistant heat-proof functional prepreg and carbon fiber/epoxy structure prepreg, and winding and laying at 0 degree, 90 degrees, 45 degrees and 45 degrees according to the product laying structure design with the length direction of an inner cylinder body as 0 degree direction, so that the value range of the flue forming thickness is between 1mm and 10 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mould, vacuumizing and compacting, then placing the inner cylinder mould into a hot-pressing tank for heating, pressurizing and curing, wherein the value range of the curing temperature is 120-180 ℃, the value range of the curing time is 10-20 h, and cleaning the surface auxiliary materials of the gas flue mould after curing;
d. mold assembly
Respectively positioning and bonding the longitudinal rib mold and the gas flue mold on the surface of the inner cylinder, and fastening and preventing the two ends of the inner cylinder mold from falling off;
e. outer barrel forming
Continuously adopting carbon fiber/epoxy structure prepreg to mold an outer cylinder on the outer surfaces of the assembled longitudinal ribs and the gas flue, wherein the length direction of the outer cylinder is 0 degree, winding and laying are carried out for 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design, the value range of the outer cylinder skin molding thickness is between 3mm and 20mm, reinforcing ring ribs are locally laid and wound according to the hoisting and stacking requirements, and the value range of the ring rib thickness is between 10mm and 50 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the outer cylinder mold, vacuumizing and compacting, then placing the outer cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature is between 120 and 180 ℃, the curing time is between 10 and 20 hours, and cleaning the surface auxiliary materials of the outer cylinder mold after curing;
f. demoulding and forming products
And (3) demolding the longitudinal rib and the gas flue mold in sequence along the end surface of the product by utilizing a demolding tool, and then demolding the inner cylinder mold to obtain the product of the launching cylinder.
Compared with the prior art, the barrel structure of the hollow multi-cavity composite material launching barrel has the following advantages:
the barrel structure of the invention is made of composite materials, the whole barrel has light weight and is convenient to process and assemble; the inner cylinder body is embedded in the outer cylinder body, and the connecting position of the inner cylinder body and the outer cylinder body is limited; the axial direction of the outer peripheral surface of the inner cylinder body is connected with the axial direction of the inner peripheral surface of the outer cylinder body through longitudinal ribs, so that the inner cylinder body and the outer cylinder body are fixedly connected in the axial direction through the longitudinal ribs, and the connection position is firm; a gas flue is formed between the outer peripheral surface of the inner cylinder and the inner peripheral surface of the outer cylinder, so that a hollow structure is formed inside the cylinder structure, heat dissipation is facilitated, and the gas flue is better applied to heat emission of the emission cylinder.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is a schematic cross-sectional view of a tubular structure of a hollow multi-cavity composite launch canister according to an embodiment of the present invention;
FIG. 2 is an enlarged view of portion A of FIG. 1;
fig. 3 is a flowchart of a method for forming a tubular structure of a hollow multi-cavity composite launch canister according to an embodiment of the present invention.
Description of reference numerals:
100-an inner cylinder; 200-outer cylinder;
300-longitudinal ribs; 101-gas flue.
Detailed Description
It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict.
In the description of the present invention, it is to be understood that the terms "center", "longitudinal", "lateral", "up", "down", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", and the like, indicate orientations or positional relationships based on those shown in the drawings, and are used only for convenience in describing the present invention and for simplicity in description, and do not indicate or imply that the referenced devices or elements must have a particular orientation, be constructed and operated in a particular orientation, and thus, are not to be construed as limiting the present invention. Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. Thus, a feature defined as "first," "second," etc. may explicitly or implicitly include one or more of that feature. In the description of the present invention, "a plurality" means two or more unless otherwise specified.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meaning of the above terms in the present invention can be understood by those of ordinary skill in the art through specific situations.
The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1-2, the tubular structure of the hollow multi-cavity composite material launch tube provided by the invention is made of composite materials, and comprises an inner tubular body 100, an outer tubular body 200 and longitudinal ribs 300;
the inner cylinder 100 is embedded in the outer cylinder 200, the axial direction of the outer circumferential surface of the inner cylinder 100 is connected with the axial direction of the inner circumferential surface of the outer cylinder 200 by longitudinal ribs 300, and a gas flue 101 is formed between the outer circumferential surface of the inner cylinder 100 and the inner circumferential surface of the outer cylinder 200.
In an embodiment of the present invention, as shown in fig. 1, the cylinder structure is made of a composite material, the reinforcement of the composite material cylinder is made of glass fiber, high silica fiber or carbon fiber, and the like, the resin matrix is made of ceramic resin, phenolic resin, bismaleimide resin or epoxy resin, and the like, and the corresponding materials can be selected to ensure the reinforcement according to requirements of different performances. The structure of the composite material cylinder can reduce the weight of the whole cylinder.
The inner cylinder 100 is embedded in the outer cylinder 200, the axial direction of the outer peripheral surface of the inner cylinder 100 is fixedly connected with the axial direction of the inner peripheral surface of the outer cylinder 200 through the longitudinal ribs 300, so that the gas flue 101 is arranged along the axial direction of the inner cylinder 100 and the axial direction of the outer cylinder 200, a hollow structure is formed between the inner cylinder 100 and the outer cylinder 200, and the requirement of the gas flue 101 on adapting to the use condition of a heat-emitting missile is met.
Further, the number of the longitudinal ribs 300 is at least two, and the number of the gas flues 101 corresponds to the number of the longitudinal ribs 300.
In an embodiment of the present invention, as shown in fig. 1, the number of the longitudinal ribs 300 is set to be four, four gas flues 101 with the same area are correspondingly formed between the inner cylinder 100 and the outer cylinder 200, and the four gas flues 101 are used to uniformly distribute the hollow structure between the inner cylinder 100 and the outer cylinder 200, so as to ensure that the gas flues 101 meet the requirement of the working condition.
In other embodiments of the present invention, the number of the longitudinal ribs 300 may be set to other numbers, and the number of the corresponding gas flues 101 corresponds to the number of the longitudinal ribs 300.
Further, the cross-sectional shape of the longitudinal rib 300 is any one of an i-shape, a U-shape, a square-shape, and a trapezoid.
In this embodiment, as shown in fig. 2, the cross-sectional shape of the longitudinal ribs 300 is square, but in actual use, other shapes may be adopted as long as the longitudinal ribs 300 can be connected between the inner cylinder 100 and the outer cylinder 200.
Further, the sectional shape of the inner cylinder 100 is any one of circular, square, rectangular, and irregular, and the sectional shape of the outer cylinder 200 corresponds to the sectional shape of the inner cylinder 100.
In the present embodiment, as shown in fig. 2, both the cross-sectional shape of the inner cylinder 100 and the cross-sectional shape of the outer cylinder 200 are circular. In other embodiments, the cross-sectional shape of the inner cylinder 100 and the cross-sectional shape of the outer cylinder 200 may be other shapes as described above to better accommodate missile launching.
As shown in fig. 3, the present invention further provides a method for forming a tubular structure of a hollow multi-cavity composite launch canister, comprising the following steps:
a. inner cylinder forming
Coating a release agent on the surface of an inner cylinder mould, respectively adopting high-temperature-resistant heat-proof functional prepreg and carbon fiber/epoxy structure prepreg, and winding and laying at 0 degree, 90 degrees, 45 degrees and 45 degrees according to the product laying structure design with the length direction of the inner cylinder mould as 0 degree direction to ensure that the value range of the forming thickness of the inner cylinder 100 is between 5mm and 10 mm; in this embodiment, the molding thickness of the inner cylinder 100 is 6 mm.
After the laying is finished, placing a vacuum auxiliary material on the surface of the inner cylinder mold, vacuumizing and compacting, then placing the inner cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature ranges from 120 ℃ to 180 ℃, the curing time ranges from 10h to 20h, in the embodiment, the curing temperature ranges from 150 ℃, the curing time ranges from 15h, and after curing, cleaning the surface auxiliary material of the inner cylinder mold;
b. longitudinal rib forming
Coating a release agent on the surface of a longitudinal rib mold, adopting a carbon fiber/epoxy structure prepreg, winding and laying layers of 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design by taking the length direction of an inner cylinder body 100 as the 0 degree direction, and enabling the value range of the forming thickness of a longitudinal rib 300 to be between 3mm and 10 mm; in this embodiment, the molding thickness of the longitudinal rib 300 is 5 mm.
After the laying is finished, placing a vacuum auxiliary material on the surface of the inner cylinder mould, vacuumizing and compacting, then placing the inner cylinder mould into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature is between 120 and 180 ℃, the curing time is between 10 and 20 hours, in the embodiment, the curing temperature is 150 ℃, the curing time is 15 hours, and after curing, cleaning the surface auxiliary material of the longitudinal rib mould;
c. shaping of gas flue
Coating a release agent on the surface of a gas flue mould, respectively adopting a high-temperature-resistant heat-proof function prepreg and a carbon fiber/epoxy structure prepreg, and winding and laying at 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design with the length direction of an inner cylinder body 100 as 0 degree direction, so that the value range of the flue forming thickness is between 1mm and 10 mm; in this embodiment, the thickness of the flue is 5 mm.
After the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mold, vacuumizing and compacting, then placing the inner cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature ranges from 120 ℃ to 180 ℃, the curing time ranges from 10h to 20h, in the embodiment, the curing temperature ranges from 150 ℃, the curing time ranges from 15h, and after curing, cleaning the surface auxiliary materials of the gas flue mold;
d. mold assembly
Respectively positioning and bonding the longitudinal rib mold and the gas flue mold on the surface of the inner cylinder 100, and fastening and preventing the two ends of the inner cylinder mold from falling off;
e. outer barrel forming
Continuously adopting carbon fiber/epoxy structure prepreg to mold an outer cylinder body on the outer surfaces of the assembled longitudinal ribs and the gas flue, wherein the length direction of the outer cylinder body 200 is 0 degree, winding and laying are carried out for 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design, the value range of the outer cylinder body skin molding thickness is between 3mm and 20mm, reinforcing annular ribs are locally laid and wound according to the hoisting and stacking requirements, and the value range of the annular rib thickness is between 10mm and 50 mm; in this embodiment, the thickness of the outer cylinder skin is 10mm, and the thickness of the ring rib is 30 mm.
After the laying is finished, placing a vacuum auxiliary material on the surface of the outer cylinder mold, vacuumizing and compacting, then placing the outer cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature ranges from 120 ℃ to 180 ℃, the curing time ranges from 10h to 20h, in the embodiment, the curing temperature ranges from 150 ℃, the curing time ranges from 15h, and after curing, cleaning the surface auxiliary material of the outer cylinder mold;
f. demoulding and forming products
And (3) demolding the longitudinal rib 300 and the gas flue mold in sequence along the end surface of the product by using a demolding tool, and then demolding the inner cylinder mold to obtain the product of the launching cylinder.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (5)
1. The barrel structure of the hollow multi-cavity composite material launching barrel is characterized in that the barrel structure is made of composite materials and comprises an inner barrel (100), an outer barrel (200) and longitudinal ribs (300);
the inner cylinder (100) is embedded in the outer cylinder (200), the axial direction of the outer peripheral surface of the inner cylinder (100) is connected with the axial direction of the inner peripheral surface of the outer cylinder (200) through the longitudinal ribs (300), and a gas flue (101) is formed between the outer peripheral surface of the inner cylinder (100) and the inner peripheral surface of the outer cylinder (200).
2. The tubular structure of the hollow multi-cavity composite material launch tube according to claim 1, characterized in that the number of the longitudinal ribs (300) is at least two, and the number of the gas flues (101) corresponds to the number of the longitudinal ribs (300).
3. The tubular structure of the hollow multi-cavity composite material launch canister according to claim 1, characterized in that the cross-sectional shape of the longitudinal ribs (300) is any one of i-shaped, U-shaped, square, and trapezoidal.
4. The tubular structure of the hollow multi-cavity composite material launch barrel according to claim 1, characterized in that the cross-sectional shape of the inner barrel (100) is any one of circular, square, rectangular and special-shaped, and the cross-sectional shape of the outer barrel (200) corresponds to the cross-sectional shape of the inner barrel (100).
5. A method for forming a barrel structure of a hollow multi-cavity composite material launching barrel is characterized by comprising the following steps:
a. inner cylinder forming
Coating a release agent on the surface of an inner cylinder mould, respectively adopting high-temperature-resistant heat-proof functional prepreg and carbon fiber/epoxy structure prepreg, and winding and laying at 0 degree, 90 degrees, 45 degrees and 45 degrees according to the product laying structure design with the length direction of the inner cylinder mould as 0 degree direction to ensure that the value range of the forming thickness of the inner cylinder (100) is between 5mm and 10 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mold, vacuumizing and compacting, then placing the inner cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature is between 120 and 180 ℃, the curing time is between 10 and 20 hours, and cleaning the surface auxiliary materials of the inner cylinder mold after curing;
b. longitudinal rib forming
Coating a release agent on the surface of a longitudinal rib mold, adopting carbon fiber/epoxy structure prepreg, taking the length direction of an inner cylinder body (100) as 0 degree direction, and winding and laying the longitudinal rib mold according to the product laying structure design of 0 degree, 90 degrees, 45 degrees and the like to ensure that the value range of the molding thickness of the longitudinal rib (300) is between 3mm and 10 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mould, vacuumizing and compacting, then placing the inner cylinder mould into a hot-pressing tank for heating, pressurizing and curing, wherein the value range of the curing temperature is 120-180 ℃, the value range of the curing time is 10-20 h, and cleaning the surface auxiliary materials of the longitudinal rib mould after curing;
c. shaping of gas flue
Coating a release agent on the surface of a gas flue mould, respectively adopting high-temperature-resistant heat-proof functional prepreg and carbon fiber/epoxy structural prepreg, taking the length direction of an inner cylinder (100) as 0 degree direction, and carrying out winding and laying at 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design, so that the value range of the flue forming thickness is between 1mm and 10 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the inner cylinder mould, vacuumizing and compacting, then placing the inner cylinder mould into a hot-pressing tank for heating, pressurizing and curing, wherein the value range of the curing temperature is 120-180 ℃, the value range of the curing time is 10-20 h, and cleaning the surface auxiliary materials of the gas flue mould after curing;
d. mold assembly
Respectively positioning and bonding the longitudinal rib mold and the gas flue mold on the surface of the inner cylinder (100), and fastening and preventing the two ends of the inner cylinder mold from falling off;
e. outer barrel forming
Continuously adopting carbon fiber/epoxy structure prepreg to mold an outer cylinder body on the outer surfaces of the assembled longitudinal ribs and the gas flue, wherein the length direction of the outer cylinder body (200) is 0 degree, winding and laying are carried out for 0 degree, 90 degrees, 45 degrees and the like according to the product laying structure design, the value range of the outer cylinder body skin molding thickness is between 3mm and 20mm, reinforcing ring ribs are locally laid and wound according to the hoisting and stacking requirements, and the value range of the ring rib thickness is between 10mm and 50 mm;
after the laying is finished, placing vacuum auxiliary materials on the surface of the outer cylinder mold, vacuumizing and compacting, then placing the outer cylinder mold into a hot-pressing tank for heating, pressurizing and curing, wherein the curing temperature is between 120 and 180 ℃, the curing time is between 10 and 20 hours, and cleaning the surface auxiliary materials of the outer cylinder mold after curing;
f. demoulding and forming products
And (3) demolding the longitudinal rib (300) and the gas flue mold in sequence along the end surface of the product by using a demolding tool, and then demolding the inner cylinder mold to obtain the product of the launching cylinder.
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| CN202110526508.5A CN113432486B (en) | 2021-06-16 | 2021-06-16 | Barrel structure of hollow multi-cavity composite material launching barrel and forming method thereof |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016150653A1 (en) * | 2015-03-23 | 2016-09-29 | Thyssenkrupp Marine Systems Gmbh | Weapon ejection device comprising a push chain |
| CN111023894A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Missile launching canister and preparation method thereof |
| CN111186144A (en) * | 2019-12-26 | 2020-05-22 | 天津爱思达新材料科技有限公司 | Ablation-resistant composite material launching tube body structure and forming method thereof |
| CN212963028U (en) * | 2020-08-17 | 2021-04-13 | 江苏新扬新材料股份有限公司 | Composite material missile launching tube structure |
-
2021
- 2021-06-16 CN CN202110526508.5A patent/CN113432486B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2016150653A1 (en) * | 2015-03-23 | 2016-09-29 | Thyssenkrupp Marine Systems Gmbh | Weapon ejection device comprising a push chain |
| CN111023894A (en) * | 2019-12-04 | 2020-04-17 | 天津爱思达新材料科技有限公司 | Missile launching canister and preparation method thereof |
| CN111186144A (en) * | 2019-12-26 | 2020-05-22 | 天津爱思达新材料科技有限公司 | Ablation-resistant composite material launching tube body structure and forming method thereof |
| CN212963028U (en) * | 2020-08-17 | 2021-04-13 | 江苏新扬新材料股份有限公司 | Composite material missile launching tube structure |
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| CN113432486B (en) | 2023-01-17 |
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