阅读说明：本技术 基于碳纤维复合基材料的发射筒、制作方法 (Launch canister based on carbon fiber composite base material and manufacturing method ) 是由 高露露 仇亚萍 孟梦 陈明新 刘伟 于 2020-04-22 设计创作，主要内容包括：本发明公开了一种基于碳纤维复合基材料的发射筒、制作方法,所述发射筒包括发射筒体,所述的发射筒体包括自内向外依次设置的耐烧蚀预浸层、耐烧蚀层、第一阻燃增韧层和第二阻燃增韧层,在所述的耐烧蚀预浸层和所述耐烧蚀层之间还铺设有沿着发射筒体长度方向铺设的导向板。本发明的制作方法简单、易行,工艺可操作性强,充分利用不同型号碳纤维。通过采用本发明的方法,即便选用常见强度的碳纤维制作的发射筒的筒体依旧能够实现优异的力学性能,能够降低成本。同时所制作的发射筒的筒体,和现有的金属以及碳纤维、玻璃纤维等多种混合的多层结构相比,不仅能够降低重量,且具有界面连续性好,力学性能优异,满足轴向刚度和稳定性的需求。(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.)

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.

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.