CN212963028U - Composite material missile launching tube structure - Google Patents
Composite material missile launching tube structure Download PDFInfo
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- CN212963028U CN212963028U CN202021711438.8U CN202021711438U CN212963028U CN 212963028 U CN212963028 U CN 212963028U CN 202021711438 U CN202021711438 U CN 202021711438U CN 212963028 U CN212963028 U CN 212963028U
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Abstract
The utility model discloses a combined material guided missile launching tube structure, including inner tube ablation layer, the inner tube structural layer is established to the periphery cover on inner tube ablation layer, and the periphery of inner tube structural layer has a plurality of muscle of indulging along its circumference equipartition, and the inner tube structural layer has the muscle package structural layer of indulging with indulging muscle periphery cladding, and the periphery cladding of indulging muscle package structural layer has the muscle fire prevention ablation layer of indulging, and it is equipped with the urceolus inoxidizing coating to indulge muscle fire prevention ablation layer periphery cover, and the urceolus structural layer is established to the periphery cover of urceolus inoxidizing coating, the utility model discloses a multilayer structure cooperation is indulged the muscle and is formed interior outer tube structure, and the cavity region between the.
Description
Technical Field
The utility model relates to a launch canister, in particular to missile launch canister.
Background
The launching cylinder device supports and protects the missile before launching, and inert gas is filled inside the launching cylinder device to protect the missile. Therefore, the emission tube needs to have good air tightness in a storage state so as to ensure that the inert gas in the tube does not leak.
The launching tube also needs to have certain structural strength, and the missile can be effectively protected in the transferring and hoisting process.
When the fuel gas is emitted, high-temperature fuel gas is discharged from the fuel gas discharge channel through the inner cylinder, so that all materials and structures in contact with the fuel gas area need to be resistant to ablation; the inner cylinder is required to have higher finish so as to reduce the friction force of the missile during filling and discharging; the high-speed metal oxide fuel gas flow has stronger ablation and scouring to the inner cylinder and the fuel gas discharge channel, so the launching operating condition is very severe.
At present, the metal concentric tube has large density and overweight, so the use requirement cannot be met, and the inner tube of the metal launching tube is formed by machining and influenced by a forming process, so the straightness is large, and if the tube body is locally deformed, the missile discharging is influenced. In addition, at the moment of missile launching, the temperature of the barrel body reaches over 1000 ℃, seawater enters the barrel body, and the barrel body is cooled violently and is easy to deform. The density of the composite material launch canister body is between 1.6 and 1.9g/cm3, is much less than that of stainless steel 7.8 g/cm3, the density is 1/4 of steel, and the composite material launch canister body has absolute advantages in weight reduction, reduces the load carrying during combat, and also reduces the cost of the launch canister.
SUMMERY OF THE UTILITY MODEL
The utility model aims at providing a combined material guided missile launching tube structure, its structure is lighter, and intensity is higher.
The purpose of the utility model is realized like this: the utility model provides a combined material missile launching tube structure, includes inner tube ablation layer, the inner tube structural layer is established to the periphery cover on inner tube ablation layer, the periphery of inner tube structural layer has a plurality of muscle of indulging along its circumference equipartition, the inner tube structural layer has the muscle package structural layer of indulging with indulging muscle periphery cladding, the periphery cladding of indulging muscle package structural layer has the muscle fire ablation layer of indulging, it is equipped with the urceolus inoxidizing coating to indulge muscle fire ablation layer periphery cover, urceolus structural layer is established to the periphery cover of urceolus inoxidi.
As a further limitation of the present invention, the inner barrel ablation layer is made of glass fiber/phenolic resin compounded prepreg.
As a further limitation of the present invention, the inner cylinder structure layer is made of carbon fiber/epoxy prepreg.
As the utility model discloses a further inject, indulge the muscle and be square pipe, and indulge the muscle and be provided with four, just it bonds in inner tube structure layer periphery to indulge the muscle.
As a further limitation of the present invention, the longitudinal bar-wrapped structure layer is made of carbon fiber/epoxy resin prepreg.
As the utility model discloses a further inject, the muscle fire prevention ablation layer that indulges adopts glass fiber/phenolic resin preimpregnation material to make.
As a further limitation of the present invention, the outer barrel protective layer is made of glass fiber/phenolic resin prepreg.
As a further limitation of the present invention, the outer cylinder structure layer is made of carbon fiber/epoxy prepreg.
As a further limitation of the utility model, the outer cylinder structure layer is additionally provided with a ring rib.
Compared with the prior art, the beneficial effects of the utility model reside in that: the utility model forms an inner and outer cylinder structure by matching the multilayer structure with the longitudinal ribs, and the cavity area between the inner and outer cylinders forms a gas discharge and guide channel, thereby enhancing the structural strength; meanwhile, the inner surface of the inner cylinder and the gas discharge and guide channel adopt glass fiber/phenolic resin prepreg, so that the fireproof and ablation-resistant performance is improved; the utility model discloses still further strengthen overall structure intensity through install the ring muscle additional in urceolus structural layer periphery.
Drawings
Fig. 1 is a cross-sectional view of the present invention.
The fireproof ablation structure comprises an inner cylinder ablation layer 1, an inner cylinder structural layer 2, longitudinal ribs 3, a longitudinal rib wrapping structural layer 4, a longitudinal rib fireproof ablation layer 5, an outer cylinder protective layer 6, an outer cylinder structural layer 7 and ring ribs 8.
Detailed Description
As shown in fig. 1, a composite material missile launching tube structure comprises an inner tube ablation layer 1, wherein the inner tube ablation layer 1 is made of prepreg matched with glass fiber/phenolic resin, an inner tube structure layer 2 is sleeved on the periphery of the inner tube ablation layer 1, the inner tube structure layer 2 is made of carbon fiber/epoxy resin prepreg, four longitudinal ribs 3 are uniformly distributed on the periphery of the inner tube structure layer 2 along the circumferential direction, the longitudinal ribs 3 are square tubes, the longitudinal ribs 3 are adhered to the periphery of the inner tube structure layer 2, longitudinal rib wrapping structure layers 4 are wrapped on the peripheries of the inner tube structure layer 2 and the longitudinal ribs 3, the longitudinal rib wrapping structure layers 4 are made of carbon fiber/epoxy resin prepreg, a longitudinal rib fireproof ablation layer 5 is wrapped on the periphery of the longitudinal rib wrapping structure layer 4, the longitudinal rib fireproof ablation layer 5 is made of prepreg made of glass fiber/phenolic resin, and an outer tube protective layer 6 is sleeved on the periphery, the outer cylinder protective layer 6 is made of glass fiber/phenolic resin prepreg, an outer cylinder structural layer 7 is sleeved on the outer periphery of the outer cylinder protective layer 6, the outer cylinder structural layer 7 is made of carbon fiber/epoxy resin prepreg, and a ring rib 8 is additionally arranged on the outer periphery of the outer cylinder structural layer 7.
The utility model forms an inner and outer cylinder structure by matching the multilayer structure with the longitudinal ribs 3, and the cavity area between the inner and outer cylinders forms a gas discharge and guide channel, thereby enhancing the structural strength; meanwhile, the inner surface of the inner cylinder and the gas discharge and guide channel adopt glass fiber/phenolic resin prepreg, so that the fireproof and ablation-resistant performance is improved; the utility model discloses still further strengthen overall structure intensity through installing ring muscle 8 additional in 7 peripheries on urceolus structural layer.
The present invention is not limited to the above embodiments, and based on the technical solutions disclosed in the present invention, those skilled in the art can make some replacements and transformations for some technical features without creative labor according to the disclosed technical contents, and these replacements and transformations are all within the protection scope of the present invention.
Claims (3)
1. The utility model provides a combined material missile launching tube structure, a serial communication port, including inner tube ablation layer, the inner tube structural layer is established to the periphery cover on inner tube ablation layer, the periphery of inner tube structural layer has a plurality of muscle of indulging along its circumference equipartition, the inner tube structural layer with indulge muscle periphery cladding and have a muscle package structural layer of indulging, the periphery cladding of indulging muscle package structural layer has and indulges muscle fire prevention ablation layer, it is equipped with the urceolus inoxidizing coating to indulge muscle fire prevention ablation layer periphery cover, the urceolus structural layer is established to the periphery cover of urc.
2. The composite material missile launcher structure of claim 1, wherein the longitudinal ribs are square tubes, four longitudinal ribs are provided, and the longitudinal ribs are bonded to the outer periphery of the inner barrel structure layer.
3. The composite material missile launcher structure of claim 1, wherein a ring rib is additionally arranged on the outer circumference of the outer barrel structure layer.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021711438.8U CN212963028U (en) | 2020-08-17 | 2020-08-17 | Composite material missile launching tube structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202021711438.8U CN212963028U (en) | 2020-08-17 | 2020-08-17 | Composite material missile launching tube structure |
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| Publication Number | Publication Date |
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| CN212963028U true CN212963028U (en) | 2021-04-13 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202021711438.8U Active CN212963028U (en) | 2020-08-17 | 2020-08-17 | Composite material missile launching tube structure |
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| CN (1) | CN212963028U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113188368A (en) * | 2021-05-14 | 2021-07-30 | 天津爱思达新材料科技有限公司 | Composite material concentric cylinder structure |
| CN113432486A (en) * | 2021-06-16 | 2021-09-24 | 天津爱思达新材料科技有限公司 | Barrel structure of hollow multi-cavity composite material launching barrel and forming method thereof |
| CN115507698A (en) * | 2022-09-30 | 2022-12-23 | 北京星航机电装备有限公司 | Launch canister and forming method thereof |
-
2020
- 2020-08-17 CN CN202021711438.8U patent/CN212963028U/en active Active
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113188368A (en) * | 2021-05-14 | 2021-07-30 | 天津爱思达新材料科技有限公司 | Composite material concentric cylinder structure |
| CN113432486A (en) * | 2021-06-16 | 2021-09-24 | 天津爱思达新材料科技有限公司 | Barrel structure of hollow multi-cavity composite material launching barrel and forming method thereof |
| CN113432486B (en) * | 2021-06-16 | 2023-01-17 | 天津爱思达新材料科技有限公司 | Barrel structure of hollow multi-cavity composite material launching barrel and forming method thereof |
| CN115507698A (en) * | 2022-09-30 | 2022-12-23 | 北京星航机电装备有限公司 | Launch canister and forming method thereof |
| CN115507698B (en) * | 2022-09-30 | 2024-04-12 | 北京星航机电装备有限公司 | Transmitting tube and forming method thereof |
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