Composite material launch tube and preparation method thereof

Abstract

A composite material launch tube includes a composite material barrel, a clamping ring and a mounting ring sleeved on the barrel, and a flange sleeved on the end of the barrel, characterized in that: a wire groove is provided on the inner wall of the barrel and penetrates the barrel axially, the wire groove protrudes radially outward along the barrel to form a protrusion corresponding to the wire groove on the outer wall of the barrel, and the number of wire grooves is at least two and is evenly distributed along the circumference of the barrel. The present invention improves the regularity and appearance quality of the barrel structure, improves the compatibility of the barrel and the launch projectile, improves the quality of the barrel, and has excellent sealing and structural strength; a wire groove is provided on the barrel to accommodate peripheral parts on the periphery of the launch projectile, avoids the overall expansion of the inner diameter of the barrel while ensuring the compatibility of the launch projectile and the barrel, reduces the preparation cost and weight of the barrel, and meets the design requirements of miniaturization and lightweight launch tubes. The present invention also provides a preparation method for a composite material launch tube.

Description

Technical Field

[0001] The invention relates to a composite material launch tube, belonging to the technical field of cold launch. Background Art

[0002] A cold launch is a method of launching a missile from a launch tube using auxiliary power, then igniting the main engine when the missile reaches a certain altitude. The missile and its launch equipment are unaffected by the high-temperature gases generated by the missile's main engine, hence the name cold launch. The launch tube is the primary equipment for cold launch, used to load and launch the missile. The launch tube is typically a steel load-bearing structure designed to withstand the loads of the loaded missile during storage, transportation, and launch.

[0003] Currently, all-metal launch tubes are no longer able to meet the lightweight requirements of modern warfare. The use of composite launch tubes can significantly reduce the negative mass of equipment. For example, CN112762759A discloses a new all-composite launch tube, which includes a launch tube body, an annular structural layer disposed on the outer wall of the launch tube body, an annular outer protective layer disposed on the outer wall of the annular structural layer, and a liquid colloid connecting the launch tube body, the annular structural layer, and the annular outer protective layer. An annular peripheral member is disposed on one side of the outer wall of the annular outer protective layer, and an annular peripheral member is disposed on the annular reinforcement layer. The launch tube body has a front flange disposed on one end of the outer wall, and a rear flange disposed on the end away from the front flange. CN116278039A discloses a composite material launch tube for cold launch and a preparation method thereof. The preparation method adopts a wet winding process to pre-embed the metal parts at both ends. The position of the metal parts is guaranteed by the core shaft of the core shaft mold and the positioning tooling, thereby ensuring the connection strength between the two metal parts and the composite material cylinder, and can effectively prevent the two metal parts from loosening and falling off; then the carbon fiber structural layer and the glass fiber layer are both wound. Compared with the prepreg paving process, the composite material cylinder formed by the winding process can effectively ensure the structural strength of the cylinder and meet the internal pressure strength. The composite launch tube in the above scheme is light in weight, simple in structure and low in cost, but the barrel of the composite launch tube in the above scheme is all cylindrical in shape. In the prior art, the outer periphery of the composite launch projectile has peripheral parts such as cable boxes and connection boxes. If the launch tube is in a straight cylindrical shape, the peripheral parts will be loaded into the launch tube together with the launch projectile, so that the inner diameter of the launch tube will be larger than the outer diameter of the projectile, which increases the manufacturing cost. At the same time, it is not conducive to the miniaturization and lightweight design requirements of the launch tube. If a space for accommodating peripheral parts is provided on the launch tube, the shape of the launch tube will be changed, making the launch tube an asymmetric eccentric structure, which is easy to cause deformation of the barrel during the molding process, affecting the structural performance of the launch tube and its compatibility with the launch projectile. Summary of the Invention

[0004] The composite launch tube provided by the present invention improves the regularity and appearance of the tube structure, enhances the compatibility of the tube with the projectile, and improves the quality of the tube. A wire slot is provided in the tube to accommodate peripheral components around the projectile. This ensures the projectile fits the tube without requiring an overall increase in the tube's inner diameter, thus reducing the production cost and weight of the tube and meeting the design requirements for a miniaturized and lightweight launch tube. The present invention also provides a method for preparing the composite launch tube.

[0005] In order to achieve the above object, the technical solution adopted by the present invention is:

[0006] The composite material launching tube includes a composite material tube body, a clamping ring and a mounting ring are sleeved on the tube body, and a flange is sleeved on the end of the tube body. It is characterized in that a wire groove is provided on the inner wall of the tube body and penetrates the tube body axially. The wire groove protrudes radially outward along the tube body to form a protrusion corresponding to the wire groove on the outer wall of the tube body. There are at least two wire grooves and they are evenly distributed along the circumference of the tube body.

[0007] Preferably, the cylinder consists of a sealing layer and a structural layer formed on the sealing layer.

[0008] Preferably, the bottom surface of the wire groove is an arc surface concentric with the inner wall of the cylinder, the depth of the wire groove does not exceed one-fifth of the inner diameter of the cylinder, and the corners of the wire groove and the protrusion are transitioned through rounded corners.

[0009] Preferably, the sealing layer is a glass fiber composite material, a carbon fiber composite material or a film, the structural layer is a glass fiber composite material and / or a carbon fiber composite material, the sealing layer is filled with wedge-shaped block-shaped filling foam to form a rounded transition support for the raised corners, and the filling foam is PET foam, PVC foam or PU foam.

[0010] The method for preparing the composite material launch tube described above is characterized by comprising the following steps:

[0011] S1: prepare a core mold with an outer surface consistent with the inner surface of the cylinder, so that the outer surface of the core mold has a boss corresponding to the wire groove one by one, first chrome-plated on the surface of the core mold so that the surface roughness is not greater than 0.8, and then evenly apply a release agent on the core mold;

[0012] S2: forming a cylindrical blank on the core mold by laying prepreg and winding composite materials;

[0013] S3: solidifying the cylinder blank, demoulding, grinding and sandblasting to obtain the cylinder after solidification;

[0014] S4: Fasten the clamping ring, mounting ring and flange on the cylinder.

[0015] Preferably, step S2 specifically refers to forming a sealing layer on the core mold by using a prepreg layer laying process, and forming a structural layer on the sealing layer by using a winding process.

[0016] Preferably, “forming a sealing layer on the core mold by a prepreg lamination process” means:

[0017] First, prepreg is evenly laid on the core mold, with an overlap of 2-5mm between adjacent prepregs and a thickness of 1.0-1.5mm. It is then sealed with vacuum bag film and vacuumed and pressure maintained for 2-3 hours.

[0018] Then, apply structural adhesive to the filling foam and stick it to the corners on both sides of the boss, and then lay a layer of prepreg on the core mold to position the filling foam.

[0019] Preferably, “forming the structural layer on the sealing layer by a winding process” means: impregnating the reinforcing fibers with resin and winding them onto the sealing layer according to a designed winding procedure to form the structural layer.

[0020] Preferably, "curing the preformed cylinder" in step S3 means hanging the preformed cylinder into a rotary curing furnace and rotary curing it at 120°C for 5-7 hours.

[0021] Preferably, step S4 specifically refers to first selecting a flange, a clamping ring and a mounting ring that can be loosely fitted into the cylinder, spraying and cleaning the inner walls of the flange, the clamping ring and the mounting ring, and then brushing structural adhesive on the parts of the cylinder corresponding to the flange, the clamping ring and the mounting ring, and then using a bonding tool to support the flange, the clamping ring and the mounting ring and insert the flange, the clamping ring and the mounting ring into the corresponding positions of the cylinder, and then hoisting the cylinder into a curing oven and curing it at 80°C for 4 hours.

[0022] The beneficial effects of the present invention are:

[0023] The composite material launch tube of the present invention has a wire groove on the inner wall of the tube body, which protrudes outward to form a protrusion on the outer wall of the tube body. There are at least two wire grooves and they are evenly distributed along the circumference of the tube body, so that the protrusions are evenly distributed on the outer wall of the tube body, forming a tube body with a central symmetrical structure, avoiding the formation of an asymmetric eccentric structure in the tube body due to the opening of the wire groove. The central symmetrical structure is used to improve the regularity and appearance quality of the tube body structure, and the compatibility rate between the tube body and the launch projectile is improved, thereby improving the quality of the tube body. The wire groove is provided on the tube body to accommodate peripheral parts on the periphery of the launch projectile, and the overall expansion of the inner diameter of the tube body is avoided on the basis of ensuring the compatibility between the launch projectile and the tube body, thereby reducing the preparation cost and weight of the tube body, and meeting the design requirements of miniaturization and lightweight of the launch tube. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 It is a schematic diagram of the composite material launch tube of the present invention.

[0025] Figure 2 Schematic diagram of the cross section of the cylinder.

[0026] Figure 3 Schematic diagram of the core mold.

[0027] Figure 4 Schematic diagram of forming a sealing layer and a structural layer on a core mold. DETAILED DESCRIPTION

[0028] The following combination Figures 1 to 4 The embodiments of the present invention are described in detail.

[0029] The composite material launch tube includes a composite material barrel 1, a clamping ring 2 and a mounting ring 3 are sleeved on the barrel 1, and a flange 4 is sleeved on the end of the barrel 1. It is characterized in that a wire groove 5 is provided on the inner wall of the barrel 1 and penetrates the barrel 1 axially. The wire groove 5 protrudes radially outward along the barrel 1 to form a protrusion 6 corresponding to the wire groove 5 on the outer wall of the barrel 1. The number of the wire grooves 5 is at least two and is evenly distributed along the circumference of the barrel 1.

[0030] The composite material launch tube described above has a wire groove 2 on the inner wall of the barrel 1, and the wire groove 2 protrudes outward to form a protrusion 6 on the outer wall of the barrel 2. There are at least two wire grooves 5 and they are evenly distributed along the circumference of the barrel 1, so that the protrusions 6 are evenly distributed on the outer wall of the barrel 1, forming a barrel with a centrally symmetrical structure, avoiding the formation of an asymmetric eccentric structure due to the opening of the wire groove in the barrel 1, and utilizing the characteristics of the centrally symmetrical structure that the barrel body is uniformly stressed and not easily deformed during the preparation process and has good molding stability, thereby improving the regularity and appearance quality of the barrel structure, and improving the compatibility between the barrel 1 and the launch projectile, thereby improving the quality of the barrel 1; the wire groove 5 is opened on the barrel 1 to accommodate peripheral parts on the periphery of the launch projectile, avoiding the overall expansion of the inner diameter of the barrel on the basis of ensuring the adaptation of the launch projectile to the barrel, reducing the preparation cost and weight of the barrel, and meeting the design requirements of miniaturization and lightweight of the launch tube.

[0031] The cylinder 1 is composed of a sealing layer 11 and a structural layer 12 formed on the sealing layer 11. The sealing layer 11 ensures the sealing performance of the cylinder, and the structural layer 12 cooperates with the sealing layer 11 to ensure the structural strength of the cylinder 1, so that the rigidity and pressure resistance of the cylinder 1 meet the design requirements.

[0032] The bottom surface of the wire groove 5 is an arc surface concentric with the inner wall of the cylinder 1. The depth of the wire groove 5 does not exceed one-fifth of the inner diameter of the cylinder 1. The corners of the wire groove 5 and the corners of the protrusion 6 are both rounded, which improves the appearance quality of the cylinder and ensures the structural strength of the cylinder 1.

[0033] The sealing layer 11 is a glass fiber composite material, a carbon fiber composite material or an adhesive film, and the structural layer 12 is a glass fiber composite material and / or a carbon fiber composite material. The sealing layer 12 is filled with wedge-shaped block-shaped filling foam 13 to form a rounded corner transition support for the corners of the protrusion 6. The filling foam 13 is PET foam, PVC foam or PU foam. The filling foam 13 is filled in the corners of the protrusion 6 in the sealing layer 11 to support the corners of the protrusion 6 in the sealing layer 11, thereby avoiding the occurrence of hollowness in the inner layer of the cylinder 1, making the structural layer 12 and the sealing layer 11 effectively fit, ensuring the density of the cylinder 1 and improving the structural strength of the cylinder 1. The structural layer 12 is formed on the sealing layer 11, and due to the support and filling of the filling foam 13, a rounded corner transition is formed at the corners of the protrusion 6.

[0034] The present invention also protects a method for preparing the composite material launch tube as described above, which is characterized by comprising the following steps:

[0035] S1: Prepare a core mold 7 whose outer surface is consistent with the inner surface of the cylinder, so that the outer surface of the core mold 7 has a boss 71 corresponding to the wire groove one by one, first chrome-plated on the surface of the core mold so that the surface roughness is not greater than 0.8, and then evenly apply a release agent on the core mold;

[0036] S2: forming a cylindrical blank on the core mold by laying prepreg and winding composite materials;

[0037] S3: solidifying the cylinder blank, demoulding, grinding and sandblasting to obtain the cylinder after solidification;

[0038] S4: Fasten the clamping ring, mounting ring and flange on the cylinder.

[0039] The preparation method of the composite material launch tube described above uses the boss 71 on the core mold 7 to form the wire groove 5. The preparation method is simple and low-cost. The prepreg laying and composite material winding process are used to form the initial blank of the tube, thereby improving the structural strength of the tube while ensuring the lightweight level of the tube.

[0040] Specifically, step S2 involves forming a sealing layer 11 on the core mold 1 using a prepreg layup process, and forming a structural layer 12 on the sealing layer 12 using a winding process. The sealing layer 11 is first formed on the core mold 1 to ensure the sealing performance of the cylinder 1, and then the structural layer 12 is formed on the sealing layer 11. The structural layer 12 cooperates with the sealing layer 11 to ensure the structural strength of the cylinder 1, so that the rigidity and pressure resistance of the cylinder 1 meet the design requirements.

[0041] Among them, “forming a sealing layer 11 on the core mold 7 by a prepreg layer laying process” means:

[0042] First, prepreg is evenly laid on the core mold 7, with the overlap of adjacent prepregs being 2-5mm and the thickness being 1.0-1.5mm, and then sealed with vacuum bag film and vacuumed and pressure maintained for 2-3 hours;

[0043] Then, the filling foam 13 is coated with structural adhesive and adhered to the corners on both sides of the boss 71, and then a layer of prepreg is laid on the core mold to position the filling foam.

[0044] First, prepreg is laid on the core mold 7, and then the filling foam 13 is pasted on the corners on both sides of the boss 71, and then a layer of prepreg is laid on the entire circle to position the filling foam. Since the corners of the protrusion 6 of the supporting cylinder 1 of the filling foam will form a rounded transition, the setting of the filling foam avoids the formation of hollowness in the sealing layer 11, so that the structural layer 12 formed on the sealing layer 11 is effectively fitted with the sealing layer 11, ensuring the density of the cylinder 1, improving the structural strength of the cylinder 1, avoiding the reduction of the structural strength of the cylinder due to the setting of the wire groove, and further improving the quality of the cylinder 1.

[0045] Here, "forming a structural layer on the sealing layer 11 using a winding process" means impregnating the reinforcing fibers with resin and winding them onto the sealing layer 11 according to a designed winding procedure to form the structural layer 12. The structural layer 12 is formed through the winding process, and a certain winding tension is used to ensure the strength of the structural layer 12, thereby ensuring the structural strength of the formed cylinder, and ensuring that the rigidity and pressure resistance of the cylinder 1 meet the design requirements.

[0046] In step S3, "curing the preformed cylinder" means hoisting the preformed cylinder into a rotary curing furnace and rotating and curing it at 120°C for 5-7 hours. This allows the layers on the core mold 7 to be effectively cured and bonded together to form a cylinder 1 with good structural strength and light weight.

[0047] Specifically, step S4 involves first selecting a flange 4, a clamping ring 2, and a mounting ring 3 that can be loosely fitted onto the cylinder 1, spraying and cleaning the inner walls of the flange 4, clamping ring 2, and mounting ring 3, and then applying structural adhesive to the corresponding portions of the cylinder 1 corresponding to the flange 4, clamping ring 2, and mounting ring 3. Adhesive fixtures are then used to support the flange 4, clamping ring 2, and mounting ring 3, and the flange 4, clamping ring 2, and mounting ring 3 are then inserted into the corresponding portions of the cylinder. The cylinder 1 is then hoisted into a curing oven and cured at 80°C for 4 hours. The flange 4, clamping ring 2, and mounting ring 3 are all secured to the cylinder 1 by adhesive curing, making assembly simple and easy to implement, while ensuring the reliability of the assembly structure between the cylinder 1, the flange 4, clamping ring 2, and mounting ring 3.

[0048] The above fully describes the technical solutions of the embodiments of the present invention in conjunction with the accompanying drawings. It should be noted that the embodiments described are only part of the embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without making creative efforts are within the scope of protection of the present invention.

Claims

1. A method for preparing a composite material launch tube, characterized in that: The following steps are involved: S1: prepare a core mold with an outer surface consistent with the inner surface of the cylinder, so that the outer surface of the core mold has a boss corresponding to the wire groove one by one, first chrome-plated on the surface of the core mold so that the surface roughness is not greater than 0.8, and then evenly apply a release agent on the core mold; S2: forming a cylindrical blank on the core mold by laying prepreg and winding composite materials; S3: solidifying the cylinder blank, demolding, grinding and sandblasting the cylinder after solidification, and forming a cylinder, a wire groove extending axially through the cylinder on the inner wall of the cylinder, the wire groove protruding radially outward from the cylinder to form a protrusion on the outer wall of the cylinder corresponding to the wire groove, and the number of the wire grooves is at least two and evenly distributed along the circumference of the cylinder; S4: Sleeve the clamping ring, mounting ring and flange on the cylinder; Step S2 specifically refers to forming a sealing layer on the core mold using a prepreg layer laying process, and forming a structural layer on the sealing layer using a winding process; "Using prepreg lamination technology to form a sealing layer on the core mold" means: First, prepreg is evenly laid on the core mold, with an overlap of 2-5mm between adjacent prepregs and a thickness of 1.0-1.5mm. It is then sealed with vacuum bag film and vacuumed and pressure maintained for 2-3 hours. Then, apply structural adhesive to the filling foam and stick it to the corners on both sides of the boss, and then lay a layer of prepreg on the core mold to position the filling foam; “Forming the structural layer on the sealing layer by a winding process” means: impregnating the reinforcing fibers with resin and winding them onto the sealing layer according to a designed winding procedure to form the structural layer.

2. The method for preparing a composite material launch tube according to claim 1, characterized in that: The "curing of the preformed cylinder" in step S3 refers to hanging the preformed cylinder into a rotary curing furnace and rotary curing it at 120°C for 5-7 hours.

3. The method for preparing a composite material launch tube according to claim 1, characterized in that: Step S4 specifically refers to first selecting a flange, a clamping ring and a mounting ring that can be loosely fitted into the cylinder, spraying and cleaning the inner walls of the flange, clamping ring and mounting ring respectively, and then brushing structural adhesive on the parts of the cylinder corresponding to the flange, clamping ring and mounting ring, and then using a bonding tool to support the flange, clamping ring and mounting ring and insert the flange, clamping ring and mounting ring into the corresponding positions of the cylinder, and then hoisting the cylinder into a curing oven and curing it at 80°C for 4 hours.

4. A composite material launching tube obtained by the method for preparing a composite material launching tube according to any one of claims 1 to 3, comprising a composite material tube body, a clamping ring and a mounting ring sleeved on the tube body, and a flange sleeved on the end of the tube body, characterized in that: The inner wall of the cylinder is provided with a wire groove which penetrates the cylinder axially. The wire groove protrudes radially outward along the cylinder to form a protrusion corresponding to the wire groove on the outer wall of the cylinder. There are at least two wire grooves which are evenly distributed along the circumference of the cylinder.

5. The composite material launch tube according to claim 4, characterized in that: The cylinder body consists of a sealing layer and a structural layer formed on the sealing layer.

6. The composite material launch tube according to claim 4, characterized in that: The bottom surface of the wire groove is an arc surface concentric with the inner wall of the cylinder. The depth of the wire groove does not exceed one-fifth of the inner diameter of the cylinder. The edges and corners of the wire groove and the raised edges are transitioned through rounded corners.

7. The composite material launch tube according to claim 6, characterized in that: The sealing layer is made of glass fiber composite material, carbon fiber composite material or adhesive film, the structural layer is made of glass fiber composite material and / or carbon fiber composite material, the sealing layer is filled with wedge-shaped block filling foam to form a rounded transition support for the raised corners, and the filling foam is PET foam, PVC foam or PU foam.

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