CN111442693A - Launch canister based on carbon fiber composite base material and manufacturing method - Google Patents
Launch canister based on carbon fiber composite base material and manufacturing method Download PDFInfo
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- CN111442693A CN111442693A CN202010321749.1A CN202010321749A CN111442693A CN 111442693 A CN111442693 A CN 111442693A CN 202010321749 A CN202010321749 A CN 202010321749A CN 111442693 A CN111442693 A CN 111442693A
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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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Abstract
The invention discloses a carbon fiber composite-based material-based launch barrel and a manufacturing method thereof, wherein the launch barrel comprises a launch barrel body, the launch barrel body comprises an ablation-resistant prepreg layer, an ablation-resistant layer, a first flame-retardant toughening layer and a second flame-retardant toughening layer which are sequentially arranged from inside to outside, and a guide plate laid along the length direction of the launch barrel body is also laid between the ablation-resistant prepreg layer and the ablation-resistant layer. The manufacturing method is simple and easy to implement, the process operability is strong, and different types of carbon fibers are fully utilized. By adopting the method, the barrel body of the launching barrel made of the carbon fiber with common strength can still realize excellent mechanical property, and the cost can be reduced. Compared with the existing multilayer structure of various mixtures of metal, carbon fiber, glass fiber and the like, the barrel body of the launch barrel can reduce the weight, has good interface continuity and excellent mechanical property, and meets the requirements on axial rigidity and stability.
Description
Technical Field
The invention belongs to the field of manufacturing of launch canister, and particularly relates to a launch canister based on a carbon fiber composite base material and a manufacturing method thereof.
Background
The lightweight airborne equipment has important value in the aspect of energy conservation, the existing airborne equipment is mostly made of aluminum alloy, the weight of the product is larger, the manufacturing cost is higher, and the storage life is low. Compared with other materials, the carbon fiber composite material has the characteristics of light weight, high specific strength and specific modulus, corrosion resistance, fatigue resistance, good environment resistance and the like, and is widely applied to various fields. Therefore, the composite material launching tube can be produced.
At the present stage, the barrel structure of the composite material launch barrel usually adopts a multilayer structure formed by mixing multiple materials such as carbon fiber, glass fiber and erosion-resistant rubber, the structure is complex, the process implementation is complicated, the production efficiency is low, the manufacturing and material properties are discontinuous, and interface layering is easily caused.
Disclosure of Invention
Aiming at the problems, the invention provides a launching tube based on a carbon fiber composite base material and a manufacturing method thereof.
The technical purpose is achieved, the technical effect is achieved, and the invention is realized through the following technical scheme:
the utility model provides a launch barrel based on carbon fiber composite based material, includes the launch barrel, the launch barrel include from inside to outside resistant ablation preimpregnation layer, resistant ablation layer, first fire-retardant toughening layer and the fire-retardant toughening layer of second that set gradually the resistant ablation preimpregnation layer with still laid the deflector that sets up along launch barrel length direction between the ablation resistant layer. The ablation-resistant pre-impregnated layer and the ablation-resistant layer which are positioned inside the launch barrel and made by the method are made of the carbon fiber composite material of the ablation-resistant resin matrix, so that the launch barrel can meet the use requirement of erosion resistance of high-temperature gas flow, and the two flame-retardant toughening layers positioned outside can meet the flame-retardant requirement and simultaneously can ensure the strength and the rigidity of the barrel body by adopting the carbon fiber composite material of the flame-retardant toughening resin matrix.
As a further improvement of the invention, the launching barrel also comprises an accessory structure unit, wherein the accessory structure unit comprises front end metal ring connecting pieces and tail end metal ring connecting pieces which are arranged at two ends of the launching barrel, and a plurality of metal fixing rings arranged in the middle of the launching barrel.
As a further improvement of the invention, the surface of the launching cylinder is provided with a fixing ring limiting part protruding outwards at a position corresponding to the metal fixing ring, and a cylinder front end reinforcing part protruding outwards is arranged at a position corresponding to the front end metal ring connecting piece; the position where the tail end metal ring connecting piece is correspondingly arranged is provided with an installation platform reinforcing part protruding outwards; the section of the fixing ring limiting part is concave, the section of the barrel front end reinforcing part is in a platform shape, and the section of the mounting platform reinforcing part is in a right trapezoid shape.
As a further improvement of the invention, a sealing ring is arranged between the two ends of the launching cylinder and the contact end surface of the front end metal ring connecting piece.
As a further improvement of the invention, the ends of the front metal ring connecting piece and the tail metal ring connecting piece exceed the end of the launching cylinder, and the exceeding parts have mutually matched thread structures.
As a further improvement of the invention, the wall of the emission cylinder is also provided with a detection port which is communicated with the interior of the cylinder.
As a further improvement of the invention, a carbon fiber plain weave is arranged between the first flame-retardant toughening layer and the second flame-retardant toughening layer in the peripheral area of the position corresponding to the detection port.
As a further improvement of the invention, the thickness of the ablation resistant prepreg layer is 0.1-0.3mm, the thickness of the ablation resistant layer is 0.2-0.5mm, the thickness of the first flame retardant toughening layer is 30-50% of the thickness of the barrel body, the thickness of the second flame retardant toughening layer is 50-70% of the thickness of the barrel body, carbon fibers in the ablation resistant prepreg layer, the ablation resistant layer or the first flame retardant toughening layer are spirally wound at +/-20 DEG to +/-30 DEG, and carbon fibers in the second flame retardant toughening layer are spirally wound at +/-20 DEG to +/-30 DEG and are annularly wound at 89-89.9 deg.
The invention also provides a method for manufacturing the launch canister, which comprises the following steps:
adopting phenolic resin prepreg to lay an ablation-resistant prepreg layer of the cylinder;
paving a strip-shaped guide plate on the outer side of the ablation-resistant prepreg layer along the length direction of the cylinder by adopting phenolic resin prepreg;
the method comprises the steps of sequentially manufacturing an ablation-resistant layer, a first flame-retardant toughening layer and a second flame-retardant toughening layer on the outer surface of the ablation-resistant prepreg layer by adopting a carbon fiber wet winding method, paving and pasting a carbon fiber plain woven fabric between the first flame-retardant toughening layer and the second flame-retardant toughening layer, and manufacturing a fixing ring limiting part, a barrel front end reinforcing part and a mounting platform reinforcing part on the surface of the second flame-retardant toughening layer.
As a further improvement of the invention, carbon fibers pre-impregnated with phenolic resin are spirally wound at an angle of +/-23 degrees to manufacture an ablation-resistant layer with the thickness of 0.3-0.8 mm;
spirally winding carbon fibers pre-impregnated with flame-retardant toughened epoxy resin at an angle of +/-23 degrees to manufacture a first flame-retardant toughened layer with the thickness of 30-50% of the thickness of the cylinder body;
paving and pasting a carbon fiber plain weave fabric on the surface of the first flame-retardant toughening layer corresponding to the position where the detection port is arranged;
adopting carbon fiber pre-impregnated with flame-retardant toughened epoxy resin, firstly carrying out spiral winding at an angle of +/-23 degrees, and then carrying out annular winding at an angle of +/-89.4 degrees to manufacture a second flame-retardant toughened layer with the thickness of 50-70 percent of the barrel body thickness;
adopting carbon fiber pre-impregnated with flame-retardant toughened epoxy resin to perform annular winding according to an angle of +/-89.4 degrees to manufacture a fixing ring limiting part and a barrel front end reinforcing part; and (3) performing annular winding on the carbon fiber preimpregnated with the flame-retardant toughened epoxy resin according to an angle of +/-89.4 degrees, and paving and pasting plain weave fabric to manufacture the reinforcing part of the mounting platform. The manufacturing of the launching tube body mainly adopts a winding process, and the process has the advantages of low cost, high and stable product quality and high production efficiency. In the manufacturing process, the rigidity of the manufactured launch barrel along the axial direction of the barrel is ensured by using a wet winding method and controlling the winding angle, and the axial deformation requirement can be met, so that the internal pressure bearing capacity of the barrel is improved.
The invention has the beneficial effects that: the manufacturing method is simple and easy to implement, the process operability is strong, and different types of carbon fibers are fully utilized. By adopting the method, the barrel body of the launching barrel made of the carbon fiber with common strength can still realize excellent mechanical property, and the cost can be reduced. Compared with the existing multilayer structure of various mixtures of metal, carbon fiber, glass fiber and the like, the barrel body of the launch barrel can reduce the weight, has good interface continuity and excellent mechanical property, and meets the requirements on axial rigidity and stability.
Drawings
FIG. 1 is a schematic perspective view of the present invention;
FIG. 2 is a schematic cross-sectional view of the present invention;
FIG. 3 is a schematic view of a layer of a launching cylinder structure and a schematic view of connection of the front end and the rear end of the launching cylinder structure;
FIG. 4 is a schematic illustration of a guide plate area layup;
FIG. 5 is a cross-sectional view of a detection port area;
FIG. 6 is a cross-sectional ply area view of a uniform thickness area of a launching barrel;
wherein: the method comprises the following steps of 1-launching a barrel, 2-front end metal ring connecting piece, 3-tail end metal ring connecting piece, 4-metal fixing ring, 5-equal-thickness area, 6-rectangular protrusion, 7-circular protrusion, 8-screw, 9-fixing ring limiting part, 11-barrel front end reinforcing part, 12-mounting platform reinforcing part, 13-sealing ring, 14-ablation-resistant prepreg layer, 15-guide plate, 16-ablation-resistant layer, 17-first flame retardant toughening layer and 18-second flame retardant toughening layer.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention is further described in detail with reference to the following embodiments. It should be understood that the specific embodiments described herein are merely illustrative of the invention and are not intended to limit the invention.
The following detailed description of the principles of the invention is provided in connection with the accompanying drawings.
Example 1, as shown in fig. 1 to 6, the main structure of the launch barrel 1 of the launch barrel manufactured by the present invention includes an ablation-resistant prepreg layer 14, an ablation-resistant layer 16, a first flame-retardant toughening layer 17 and a second flame-retardant toughening layer 18, which are sequentially disposed from inside to outside, and a guide plate 15 laid along the length direction of the launch barrel 1 is further disposed between the ablation-resistant prepreg layer 14 and the ablation-resistant layer 16.
The ablation-resistant prepreg layer 14 is a phenolic resin prepreg layer, the ablation-resistant layer 16, the first flame-retardant toughening layer 17 and the second flame-retardant toughening layer 18 are manufactured by a carbon fiber wet winding method, the ablation-resistant layer 16 and the first flame-retardant toughening layer 17 are spirally wound at an angle of +/-23 degrees, in addition, the inside of the second flame-retardant toughening layer 18 is also spirally wound at an angle of +/-23 degrees, and the outside of the second flame-retardant toughening layer 18 is annularly wound at an angle of +/-89.4 degrees. In other embodiments, the winding angle may be adjusted as needed, and is not limited to the angle in the present embodiment.
The accessory structure unit comprises a front end metal ring connecting piece 2 and a tail end metal ring connecting piece 3 which are arranged at two ends of a launching cylinder body 1 and a plurality of metal fixing rings 4 which are arranged in the middle of the launching cylinder body 1. The surface of the launching cylinder 1 is provided with a fixing ring limiting part 9 protruding outwards at a position corresponding to the metal fixing ring 4, and a cylinder front end reinforcing part 11 protruding outwards is arranged at a position corresponding to the front end metal ring connecting piece 2; an outwards protruding installation platform reinforcing part 12 is arranged at the position corresponding to the tail end metal ring connecting piece 3; the section of the fixing ring limiting part 9 is concave, the section of the cylinder front end reinforcing part 11 is in a platform shape, and the section of the mounting platform reinforcing part 12 is in a right trapezoid shape.
And a sealing ring 13 is arranged between the two ends of the emission cylinder 1 and the contact end surface of the front end metal ring connecting piece 2.
The end parts of the front end metal ring connecting piece 2 and the tail end metal ring connecting piece 3 exceed the end part of the launching barrel body 1, and the exceeding parts are provided with thread structures matched with each other and can be used for connecting a plurality of independent launching barrels.
The wall of the emission barrel 1 is also provided with a detection port communicated into the barrel, and the surface of the detection port is provided with a metal cover. And a carbon fiber plain weave fabric is arranged in the launcher tube between the first flame-retardant toughening layer 17 and the second flame-retardant toughening layer 18 and in the peripheral area of the position corresponding to the detection port.
The thickness of the wall of the emission cylinder body except the wall of the emission cylinder body provided with the accessory structural unit is provided with a convex area, the other areas are equal-thickness areas 5, the thickness of the ablation-resistant prepreg layer 14 is 0.15mm, the thickness of the ablation-resistant layer 16 is 0.25mm, the thickness of the first flame-retardant toughening layer 17 is 1.25mm, and the thickness of the second flame-retardant toughening layer 18 is 1.75 mm.
Making launch canister
Firstly, preparing raw materials
In order to reduce the cost, the raw materials for preparing the invention are mainly selected from materials produced by Jiangsu Hengshen GmbH, and the properties of the materials are shown in tables 1 and 2.
Table 1: composite Material Performance parameters
Table 2: comparison of the Properties of carbon fiber Material
| Dongli fibre brand | Hengshen company brand | Tensile Strength (MPa) | Modulus (GPa) |
| T300 | HF10 | 3530～4000 | 221～242 |
| T700 | HF20 | 4000～4600 | 226～242 |
| T700S | HF30S | 4600～5100 | 240～270 |
| T800 | HF40S | 5100～5600 | 284～304 |
Second, the manufacturing process
The first step is as follows: the ablation-resistant prepreg layer 14 which is positioned on the innermost layer of the cylinder body is made of TF1726/HFW196PA-D6/50 phenolic prepreg of Jiangsu Hengshen GmbH. After pre-compacting, the guide plate 15 was laid out in the longitudinal direction of the cylinder using a phenol prepreg TF1726/HFW196 PA-D6/50. And then forming the ablation resistant layer 16 of the cylinder body by a carbon fiber wet winding technology, wherein the resin is TF1726 type phenolic resin of Jiangsu Hengshen GmbH, the carbon fiber is HF30S type (equivalent to Dongli T700S) fiber of Jiangsu Hengshen GmbH, the winding angle is +/-23 degrees, 3 layers are wound, and the thickness of the ablation resistant layer 16 is 0.4 mm. The parametric properties of the above-mentioned starting materials used are shown in tables 1 and 2.
The second step is that: the first flame-retardant toughening layer 17 of 10 layers of +/-23-degree carbon fiber forming barrel bodies is spirally wound by a carbon fiber wet winding technology, HF30S type fibers are selected as carbon fibers, TF1725 type flame-retardant toughening epoxy resin of Jiangsu Hengshen GmbH is selected as resin, and the winding thickness is 1.25 mm.
The third step: the method comprises the steps of spirally winding 10 layers of +/-23-degree reinforced carbon fibers by using a carbon fiber wet winding technology, then annularly winding 2 layers of +/-89.4-degree reinforced carbon fibers, forming a second flame-retardant toughening layer 18 structure layer of a cylinder body, selecting TF1725 type flame-retardant toughening epoxy resin as the resin, using HF40S type fibers of Jiangsu Hengshen GmbH, and winding the fibers to the thickness of 1.75 mm. The regions 14-18 form a cylinder body equal-thickness region 5, and after winding is completed, the total thickness of the region 5 is 3.4mm, the ablation-resistant layer 16 is 0.4mm, and the structure layer is 3 mm.
The fourth step: according to the position of the detection port, HFW196PA-D6-1/1-1000 carbon fiber plain fabric of Jiangsu Hengshen GmbH of +/-45 degrees is locally paved on the area where the detection port is arranged. And after the next step is finished, the position of the carbon fiber plain weave fabric is raised. According to the requirements, the invention is provided with two types of bulges, namely the rectangular bulge 6 and the circular bulge 7, and the total thicknesses of the finally formed emission cylinder body 1 corresponding to the two bulge positions are respectively 14mm and 12 mm.
The fifth step: make barrel front end and middle zone through carbon fiber wet process winding technique, adopt carbon fiber wet process winding method preparation to glue even base, the resin chooses for use the fire-retardant epoxy of TF1725 model toughening resin, and HF40S fibre is chosen to the carbon fiber, and the winding angle is winding thickening for 89.4. After winding, the total thickness of the highest point of the fixing ring limiting part 9 is 9mm, the total thickness of the lowest point is 7mm, and the total thickness of the area 11 of the barrel front end reinforcing part 11 is 5 mm.
And a sixth step: HF30S fiber/TF 1725 resin is alternately wound at the +/-89.4-degree hoop direction at the tail end of the cylinder body, and +/-45-degree HFW196PA-D6-1/1-1000 carbon fiber plain weave is used for paving and molding, and the mounting platform reinforcing part 12 with the total thickness of 8mm is manufactured.
The seventh step: the positions of the rectangular protrusion 6, the circular protrusion 7 and the mounting platform reinforcing part 12 on the carbon fiber cylinder are processed into required shapes. A round or rectangular boss and a plurality of holes can be machined in the position where the detection port is formed by using a lathe and the like, then the round port cover is installed, and the internal equipment can be opened and installed or detected as required. The mounting platform reinforcement 12 may be machined with a lathe or the like to form a mounting plane and a plurality of holes for mounting internal devices. The mounting hole can be a through hole or a blind hole, a threaded metal bolt threaded sleeve can be embedded by cementing, and the long-term effectiveness of the thread is ensured.
Eighth step: after the front end of the emission cylinder body 1 is embedded into the sealing ring 13, the emission cylinder body is glued with the front end metal ring connecting piece 2, and the wet installation screw 8 is mechanically connected and reinforced.
The ninth step: the launching cylinder body 1 and the tail end metal ring connecting piece 3 are glued, the tail end metal ring connecting piece 3 is glued with the launching cylinder body 1 through three equal petals, and then threads are turned on the outer surface of the protruding end face portion.
The tenth step: the launching cylinder 1 and the metal fixing ring 4 are completed by the same method as the installation of the tail end metal ring connecting piece 3.
Example 2:
the present embodiment is different from embodiment 1 in that: the spiral winding angle of the cylinder body is increased, so that the spiral winding thickness proportion is reduced, the weight is unchanged, the strength of the cylinder body is enhanced, and the capacity of resisting internal pressure is increased.
A method of making a launch canister comprising the steps of:
the first step is as follows: the ablation-resistant prepreg layer 14 which is positioned on the innermost layer of the cylinder body is made of TF1726/HFW196PA-D6/50 phenolic prepreg of Jiangsu Hengshen GmbH. After pre-compacting, the guide plate 15 was laid out in the longitudinal direction of the cylinder using a phenol prepreg TF1726/HFW196 PA-D6/50. And then forming the ablation resistant layer 16 of the cylinder body by a carbon fiber wet winding technology, wherein the resin is TF1726 type phenolic resin of Jiangsu Hengshen GmbH, the carbon fiber is HF30S type (equivalent to Dongli T700S) fiber of the Jiangsu Hengshen GmbH, the winding angle is +/-30 degrees, 4 layers are wound, and the thickness of the ablation resistant layer 16 is 0.5 mm. The parametric properties of the above-mentioned starting materials used are shown in tables 1 and 2.
The second step is that: the first flame-retardant toughening layer 17 of the 8-layer +/-30-degree carbon fiber forming barrel body is spirally wound by a carbon fiber wet winding technology, HF30S type fibers are selected as carbon fibers, TF1725 type flame-retardant toughening epoxy resin of Jiangsu Hengshen GmbH is selected as resin, and the winding thickness is 1 mm.
The third step: 8 layers of plus or minus 30-degree reinforced carbon fibers are spirally wound by a carbon fiber wet winding technology, then 6 layers of plus or minus 89.9-degree reinforced carbon fibers are annularly wound, a second flame-retardant toughening layer 18 structure layer of the forming cylinder body is made of TF1725 type flame-retardant toughening epoxy resin, HF40S type fibers of Jiangsu Hengshen GmbH are used as the fibers, and the winding thickness is 1.75 mm. The regions 14-18 form a cylinder body equal-thickness region 5, and after winding is completed, the total thickness of the region 5 is 3.4mm, the ablation-resistant layer 16 is 0.5mm, and the structure layer is 2.9 mm.
The fourth to ninth steps are the same as those of example 1 and will not be described here.
The foregoing shows and describes the general principles and broad features of the present invention and advantages thereof. It will be understood by those skilled in the art that the present invention is not limited to the embodiments described above, which are described in the specification and illustrated only to illustrate the principle of the present invention, but that various changes and modifications may be made therein without departing from the spirit and scope of the present invention, which fall within the scope of the invention as claimed. The scope of the invention is defined by the appended claims and equivalents thereof.
Claims (10)
1. The utility model provides a launch canister based on carbon fiber composite base material which characterized in that: the anti-ablation fire-retardant emission barrel comprises an emission barrel body, wherein the emission barrel body comprises an ablation-resistant prepreg layer, an ablation-resistant layer, a first fire-retardant toughening layer and a second fire-retardant toughening layer which are sequentially arranged from inside to outside, and a guide plate arranged along the length direction of the emission barrel body is further paved between the ablation-resistant prepreg layer and the ablation-resistant layer.
2. The launch canister based on carbon fiber composite-based material according to claim 1, wherein: still include annex constitutional unit, annex constitutional unit is including setting up front end becket connecting piece, the tail end becket connecting piece at the transmission barrel both ends and setting up at the solid fixed ring of a plurality of metal of transmission barrel intermediate position.
3. The launch canister based on carbon fiber composite-based material according to claim 2, characterized in that: the surface of the emission cylinder is provided with a fixing ring limiting part protruding outwards at a position corresponding to the metal fixing ring, and a cylinder front end reinforcing part protruding outwards is arranged at a position corresponding to the front end metal ring connecting piece; the position where the tail end metal ring connecting piece is correspondingly arranged is provided with an installation platform reinforcing part protruding outwards; the section of the fixing ring limiting part is concave, the section of the barrel front end reinforcing part is in a platform shape, and the section of the mounting platform reinforcing part is in a right trapezoid shape.
4. The launch canister based on carbon fiber composite-based material according to claim 2, characterized in that: and sealing rings are arranged between the two ends of the emission cylinder and the contact end surfaces of the front-end metal ring connecting pieces.
5. The launch canister based on carbon fiber composite-based material according to claim 2, characterized in that: the ends of the front end metal ring connecting piece and the tail end metal ring connecting piece exceed the end of the launching cylinder, and the exceeding parts are provided with mutually matched thread structures.
6. The launch canister based on carbon fiber composite-based material according to claim 1, wherein: and a detection port which is communicated into the barrel is also formed in the barrel wall of the emission barrel.
7. The launch canister based on carbon fiber composite-based material according to claim 6, wherein: and a carbon fiber plain weave fabric is arranged in the peripheral area of the position corresponding to the detection port between the first flame-retardant toughening layer and the second flame-retardant toughening layer.
8. The launch canister based on carbon fiber composite-based material according to claim 1, wherein: the thickness of the ablation-resistant prepreg layer is 0.1-0.3mm, the thickness of the ablation-resistant layer is 0.2-0.5mm, the thickness of the first flame-retardant toughening layer is 30-50% of the thickness of the cylinder body, the thickness of the second flame-retardant toughening layer is 50-70% of the thickness of the cylinder body, carbon fibers in the ablation-resistant prepreg layer, the ablation-resistant layer or the first flame-retardant toughening layer are spirally wound according to +/-20 degrees to +/-30 degrees, and the carbon fibers in the second flame-retardant toughening layer are spirally wound according to +/-20 degrees to +/-30 degrees and are annularly wound according to 89-89.9 degrees.
9. A method of making the launch canister of any of claims 1-8, comprising the steps of:
adopting phenolic resin prepreg to lay an ablation-resistant prepreg layer of the cylinder;
paving a strip-shaped guide plate on the outer side of the ablation-resistant prepreg layer along the length direction of the cylinder by adopting phenolic resin prepreg;
the method comprises the steps of sequentially manufacturing an ablation-resistant layer, a first flame-retardant toughening layer and a second flame-retardant toughening layer on the outer surface of the ablation-resistant prepreg layer by adopting a carbon fiber wet winding method, paving and pasting a carbon fiber plain woven fabric between the first flame-retardant toughening layer and the second flame-retardant toughening layer, and manufacturing a fixing ring limiting part, a barrel front end reinforcing part and a mounting platform reinforcing part on the surface of the second flame-retardant toughening layer.
10. The method of launching a cartridge of claim 9, wherein:
adopting carbon fiber pre-impregnated with phenolic resin, spirally winding at an angle of +/-20 degrees to +/-30 degrees, and manufacturing an ablation-resistant layer with the thickness of 0.3mm to 0.8 mm;
adopting carbon fiber pre-impregnated with flame-retardant toughened epoxy resin to carry out spiral winding according to an angle of +/-20 degrees to +/-30 degrees to manufacture a first flame-retardant toughened layer with the thickness of 30-50 percent of the thickness of the cylinder body;
paving and pasting a carbon fiber plain weave fabric on the surface of the first flame-retardant toughening layer corresponding to the position where the detection port is arranged;
adopting carbon fiber pre-impregnated with flame-retardant toughened epoxy resin, firstly carrying out spiral winding according to an angle of +/-20 degrees to +/-30 degrees, and then carrying out annular winding according to an angle of +/-89 degrees to 89.9 degrees to manufacture a second flame-retardant toughened layer with the thickness of 50 percent to 70 percent of the thickness of the cylinder body;
adopting carbon fiber preimpregnated with flame-retardant toughened epoxy resin to perform annular winding according to an angle of +/-89-89.9 degrees, and manufacturing a fixing ring limiting part and a barrel front end reinforcing part; and (3) annularly winding the carbon fiber preimpregnated with the flame-retardant toughened epoxy resin at an angle of +/-89-89.9 degrees, and paving and pasting plain woven fabric to manufacture the reinforcing part of the mounting platform.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010321749.1A CN111442693A (en) | 2020-04-22 | 2020-04-22 | Launch canister based on carbon fiber composite base material and manufacturing method |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010321749.1A CN111442693A (en) | 2020-04-22 | 2020-04-22 | Launch canister based on carbon fiber composite base material and manufacturing method |
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| CN111442693A true CN111442693A (en) | 2020-07-24 |
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| CN202010321749.1A Pending CN111442693A (en) | 2020-04-22 | 2020-04-22 | Launch canister based on carbon fiber composite base material and manufacturing method |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112026199A (en) * | 2020-08-17 | 2020-12-04 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
| CN112761793A (en) * | 2021-02-03 | 2021-05-07 | 中南大学 | Wall surface heat insulation/explosion-proof integrated thermal protection structure of combustion chamber of rotary detonation engine |
-
2020
- 2020-04-22 CN CN202010321749.1A patent/CN111442693A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112026199A (en) * | 2020-08-17 | 2020-12-04 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
| CN112026199B (en) * | 2020-08-17 | 2021-07-06 | 江苏新扬新材料股份有限公司 | Method for forming composite material concentric launching tube |
| CN112761793A (en) * | 2021-02-03 | 2021-05-07 | 中南大学 | Wall surface heat insulation/explosion-proof integrated thermal protection structure of combustion chamber of rotary detonation engine |
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