Thin-wall composite material launch canister and preparation method thereof

Abstract

The invention relates to the technical field of missile launch canisters, in particular to a thin-wall composite launch canister and a preparation method thereof. The launching cylinder comprises a cylinder body and a connecting insert; the cylinder body comprises an ablation-resistant layer and a structural layer, and the structural layer is located on the radial outer side of the ablation-resistant layer; the connecting insert is arranged at the end of the cylinder and comprises a tensile piece and a connecting piece, the tensile piece is an annular piece, the tensile piece is connected to the radial outer side of the ablation-resistant layer in a sleeving mode and located on the radial inner side of the structural layer, and thorns are arranged on the peripheral face of the tensile piece and embedded into the structural layer. The connecting piece is installed at the axial outer end of the tensile piece, and the peripheral face of the connecting piece is flush with the peripheral face of the structural layer. The problem of internal ablation of the launch canister and the problem of connection of the canister body and the metal insert are solved, and the use frequency and the structural reliability of the launch canister are improved.

Description

Technical Field

[0001] The invention relates to the technical field of missile launch tubes, and in particular to a thin-wall composite material launch tube and a preparation method thereof. Background Art

[0002] The missile launch tube is a key component of the missile system. It not only provides orientation and support for the missile, but is also responsible for storing and transporting the missile, as well as regulating the temperature of the missile before launch. The launch tube needs to withstand extreme working conditions, such as high-temperature gas scouring and huge pressure, which places extremely high demands on the material's ablation resistance and structural strength.

[0003] When a missile is launched, the launch tube, as the main load-bearing structure, needs to face the following harsh working conditions: the launch tube needs to withstand 2000K high-temperature gas scouring for a long time during use; when the missile is launched, the launch tube is subjected to great pressure. Since the glass transition temperature of the resin in the composite material layer is low, it is easy to produce defects such as stratification and bubbling during the high-temperature gas scouring process, which affects its reuse; the launch tube body is generally connected to the launch base by metal inserts, and the connection method between the metal insert and the composite material body is generally bonding or rivet connection. When the launch tube is subjected to great pressure, the bonded metal insert is prone to fall off, causing serious consequences; and for thin-walled launch tubes, there is no space for rivet connection and it cannot be realized. Therefore, it is urgent to solve the internal ablation problem of the launch tube and the connection problem between the tube body and the metal insert.

[0004] The main technical problems existing in the prior art include:

[0005] 1. When the launch tube is subjected to high-temperature gas erosion, the composite material layer is prone to stratification and bubbling, resulting in a decrease in ablation resistance.

[0006] 2. The connection between the metal insert and the composite cylinder is not strong enough under high pressure and there is a risk of falling off. Summary of the invention

[0007] In view of the deficiencies in the prior art, the purpose of the embodiments of the present invention is to provide a thin-walled composite launch tube and a preparation method thereof, so as to solve the problem of internal ablation of the launch tube and the connection problem between the tube body and the metal inserts, thereby increasing the number of uses and structural reliability of the launch tube.

[0008] In order to achieve the above objectives, the embodiments of the present invention provide the following technical solutions:

[0009] A thin-walled composite launch tube, comprising: a tube body and a connecting insert; the tube body comprises an ablation-resistant layer and a structural layer, the structural layer is located radially outside the ablation-resistant layer; the connecting insert is arranged at the end of the tube body, comprising a tensile member and a connecting member, the tensile member is an annular member, the tensile member is sleeved on the radial outside of the ablation-resistant layer, and is located radially inside the structural layer, the outer peripheral surface of the tensile member is provided with thorns, the thorns are embedded in the structural layer, the connecting member is installed at the axial outer end of the tensile member, and the outer peripheral surface of the connecting member is flush with the outer peripheral surface of the structural layer.

[0010] The embodiment of the present invention further provides a method for preparing the thin-walled composite material launch tube as described above, comprising:

[0011] Mixing ablation-resistant resin with high-silica fiber cloth tape;

[0012] Design molding molds according to product size and molding process requirements;

[0013] The prepreg tape is wound onto the mold surface using a tape winding process, and then the surface is covered with tape. The ablation layer is preformed in an autoclave at a heating temperature of 130°C-160°C and a heating pressure of 0.3-0.7MPa.

[0014] installing the tensile member onto the surface of the ablation layer;

[0015] The launch tube structure layer is prepared using epoxy resin system and carbon fiber;

[0016] The cured product is machined and then demoulded to complete the assembly of the connecting inserts and the product is completed.

[0017] One or more technical solutions provided in the embodiments of the present invention have at least the following technical effects or advantages:

[0018] 1. The launch tube includes a tube body and a connecting insert; the tube body is composed of an ablation-resistant layer and a structural layer, wherein the structural layer is located radially outside the ablation-resistant layer. The ablation-resistant layer is designed to resist high-temperature gas erosion and extend the service life of the launch tube. The connecting insert is located at the end of the tube body and is composed of a tensile member and a connecting member. The tensile member is sleeved on the outside of the ablation-resistant layer and forms a good combination with the structural layer. The outer peripheral surface of the tensile member is provided with thorns, which are embedded in the structural layer, and can significantly enhance the structural stability and connection strength of the tube body, ensuring that the launch tube will not fail or fall off under the harsh conditions of high pressure and high temperature during the missile launch process.

[0019] 2. The present invention adopts cloth tape winding to form the ablation-resistant layer, which not only meets the ablation-resistant function of the component, but also improves the structural strength of the ablation-resistant layer; the separation of the metal inserts and the use of the thorn structure solve the problem of unreliable connection between the cylinder and the metal insert, and at the same time realizes the designability of the winding layer to meet the high internal pressure requirements of the product; the inner surface ablation-resistant layer and the structural layer are co-cured and formed as a whole to ensure the reliability of product quality.

[0020] Advantages of additional aspects of the present invention will be given in the following description, and in part will become obvious from the following description, or will be learned through practice of the present invention. BRIEF DESCRIPTION OF THE DRAWINGS

[0021] In order to more clearly illustrate the technical solutions in the embodiments of the present application or the prior art, the drawings required for use in the embodiments or the prior art descriptions are briefly introduced below. Obviously, the drawings described below are only some embodiments recorded in the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without creative work. In addition, the spacing or size between each other is exaggerated to show the position of each part, and the schematic diagram is only used for illustration.

[0022] Figure 1 is an overall schematic diagram of a launch tube provided by an embodiment of the present invention;

[0023] Figure 2 is an enlarged schematic diagram of the end of a launch tube provided by an embodiment of the present invention;

[0024] Figure 3 is a side view of a tensile member provided by an embodiment of the present invention;

[0025] Figure 4 is a front view of a tensile member provided by an embodiment of the present invention;

[0026] In the figure: 1, connecting piece; 2, tensile member; 3, thorn; 4, structural layer; 5, ablation-resistant layer; DETAILED DESCRIPTION

[0027] It should be noted that the following detailed descriptions are illustrative and are intended to provide further explanation of the present invention. Unless otherwise specified, all technical and scientific terms used in the present invention have the same meanings as those commonly understood by those of ordinary skill in the art to which the present invention belongs. In addition, it should also be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0028] In order to solve the technical problems mentioned in the background technology, this embodiment proposes a thin-walled composite material launch tube. Figure 1As shown in FIG. 1 , the launch tube includes a tube body and a connecting insert (metal insert). The tube body is composed of an ablation-resistant layer and a structural layer, wherein the structural layer is located radially outside the ablation-resistant layer. The ablation-resistant layer is designed to resist high-temperature gas erosion and extend the service life of the launch tube. Figure 2 , Figure 3 As shown, the connecting insert is located at the end of the barrel, and is composed of a tensile member and a connecting member. The tensile member is sleeved on the outside of the ablation-resistant layer and forms a good combination with the structural layer. The outer peripheral surface of the tensile member is provided with thorns, which are embedded in the structural layer, which can significantly enhance the structural stability and connection strength of the barrel, ensuring that the launch tube will not fail or fall off under the harsh conditions of high pressure and high temperature during the missile launch process.

[0029] like Figure 2 , Figure 4 As shown, the outer circumference of the tensile member is divided into three sections along the axial direction, the inner end of the outer circumference is a conical structure, the conical structure is embedded between the ablation-resistant layer and the structural layer, the middle section of the outer circumference is provided with the thorns, the outer end of the outer circumference has a concave platform, and the connecting member is installed on the concave platform.

[0030] The outer circumference of the tensile member is divided into three parts. The conical structure design at the inner end enables it to be effectively embedded between the ablation-resistant layer and the structural layer, forming a mechanical locking effect and further enhancing the stability of the connection. The thorn part in the middle section can be embedded in the structural layer, increasing the friction and adhesion between the structural layer and improving the overall load-bearing capacity of the tensile member. The concave platform design at the outer end provides a flat mounting surface for the connector, ensuring a stronger connection between the connector and the tensile member, thereby improving the pressure resistance and structural integrity of the entire launch tube.

[0031] The connection between the connector and the tensile member can be various, for example, the connector and the tensile member are connected by one or more of threads, adhesives or rivets. Threaded connection is convenient for quick disassembly and assembly, and for later maintenance and replacement; adhesives can provide strong adhesion to ensure that separation does not occur under high temperature and high pressure conditions; rivet connection increases the stability and tensile strength of the structure. The combination of any one or more of the above connection methods can effectively improve the reliability of the launch tube under extreme conditions, ensure the firmness between the connector and the tensile member, and thus ensure the overall safety of the launch tube.

[0032] The ablation-resistant layer is a mixture of ablation-resistant resin and high-silica fiber cloth tape. The mixture of ablation-resistant resin and high-silica fiber cloth tape has excellent high-temperature resistance. The selection of ablation-resistant resin makes it difficult for the ablation-resistant layer to delaminate or bubble under the environment of high-temperature gas flushing, while the addition of high-silica fiber cloth tape enhances the mechanical strength of the ablation-resistant layer, which can effectively resist the thermal shock and physical impact generated during the launch process. This material combination achieves the optimal balance between the function and structure of the ablation-resistant layer, ensuring the durability and reliability of the launch tube.

[0033] The ablation-resistant resin is a mixture of one or more of a modified phenolic resin system, an organic-inorganic hybrid carbon-based resin, and a hybrid modified silicon-based resin. The modified phenolic resin system has good thermal stability and excellent mechanical properties, the organic-inorganic hybrid carbon-based resin performs well in terms of temperature resistance and corrosion resistance, and the use of hybrid modified silicon-based resin enhances the material's oxidation resistance. By selecting and proportioning different resins according to specific application requirements, the performance of the ablation-resistant layer can be further optimized to meet the use requirements of high-strength launch tubes under various extreme conditions.

[0034] The mixture of ablation-resistant resin and high-silica fiber tape is mixed in a ratio of (0.4-0.5): (0.6-1). This ratio ensures that the ablation-resistant resin can effectively penetrate and cover the high-silica fiber tape, thereby forming a high-strength, high-temperature resistant composite material. Within this ratio range, the adhesion and structural strength of the ablation-resistant resin can be maximized, and the reinforcing effect of the high-silica fiber tape can also be fully reflected. This optimized ratio configuration ensures that the ablation-resistant layer will not be damaged due to temperature fluctuations or external forces during operation, thereby increasing the overall service life of the launch tube.

[0035] The structural layer is made of an epoxy resin system and carbon fiber. The combination of the epoxy resin system and carbon fiber gives the structural layer excellent strength and rigidity. After curing, the epoxy resin forms a dense cross-linked structure that can effectively withstand external loads. At the same time, the high strength characteristics of carbon fiber enhance the tensile resistance of the structural layer. During the launch process, the structural layer needs to withstand complex stresses from both inside and outside. This material combination ensures that the structural layer remains stable in a high temperature and high pressure environment, prevents structural failure, and improves overall safety and reliability.

[0036] In summary, in the thin-walled composite launch tube structure, the ablation-resistant layer is located on the inner wall of the tube, and the structural layer is coated on the outside of the ablation-resistant layer, which solves the internal ablation problem of the launch tube and the connection problem between the tube and the metal insert. The present invention adopts a cloth tape winding process on the outer surface of the mold to prepare the ablation-resistant layer, which improves the ablation of the high-temperature gas on the tube structure and increases the number of times the tube is used; the metal insert adopts a split structure, and the presence of the thorn structure improves the connection reliability between the tube and the metal insert.

[0037] This embodiment also provides a method for preparing a thin-walled composite material launch tube, comprising the following steps:

[0038] a. Making ablation-resistant prepreg tape

[0039] The mixture of ablation-resistant resin and high-silica fiber cloth tape is mixed in a ratio of (0.4-0.5): (0.6-1). The ablation-resistant resin is mixed with one or more of a modified phenolic resin system, an organic-inorganic hybrid carbon-based resin, and a hybrid modified silicon-based resin. The core of this step is to mix the selected ablation-resistant resin with the high-silica fiber cloth tape in proportion to form an ablation-resistant prepreg tape for the subsequent winding molding process. This prepreg tape is the basis of the ablation-resistant layer of the launch tube, ensuring that it has excellent mechanical properties and high temperature resistance after molding.

[0040] b. Make mold

[0041] Design the molding mold according to the size of the product and the requirements of the molding process. Making the mold is a key link in the entire molding process. The design of the mold needs to be strictly carried out in accordance with the specifications and structural characteristics of the launch tube to ensure the accuracy and consistency of subsequent molding, thereby affecting the performance of the final product.

[0042] c. Forming of inner surface ablation-resistant layer

[0043] The cloth tape winding process is used to wrap the prepreg tape onto the mold surface, and then the BOPP tape (a tape based on biaxially oriented polypropylene film) is coated on the surface. The ablation layer is preformed in an autoclave, with a heating temperature of 130°C-160°C and a heating pressure of 0.3-0.7MPa. The cloth tape winding process used in this step is an important means to ensure the uniformity and density of the ablation-resistant layer. Under the action of the autoclave, the prepreg tape will solidify at the set temperature and pressure to form an inner surface layer with high ablation resistance. This process is crucial to improving the thermal stability and mechanical strength of the launch tube.

[0044] d. Installation of tensile parts

[0045] Install the tensile member on the surface of the ablation layer and install it in place through the tooling. This step involves accurately installing the tensile member on the cured ablation layer to ensure a good bond between the tensile member and the ablation layer.

[0046] e. Preparation of structural layer

[0047] The launch tube structural layer is prepared using an epoxy resin system and carbon fiber. At this stage, a mixture of epoxy resin and carbon fiber is applied to the inner surface of the mold to make the structural layer. This step requires ensuring that the mixture is evenly coated in order to form a high-strength and uniform structural layer, providing a basis for the mechanical properties of the launch tube.

[0048] f. Product demoulding

[0049] The cured product is machined and then demoulded to complete the assembly of the metal inserts. Finally, the product is tested for performance and the product is completed. Curing is an important step to improve the final performance of the structural layer, ensuring that the resin is fully cross-linked and forms a solid structure. This process is indispensable for enhancing the mechanical properties and temperature resistance of the launch tube. Finally, after all the curing steps, the finished launch tube is removed from the mold. At this time, the launch tube has excellent ablation resistance and structural performance, and can withstand various extreme conditions during the launch process in actual use.

[0050] By adopting specific ablation-resistant layer materials and molding processes, the ablation resistance and structural strength of the launch tube are improved. At the same time, through the innovative metal insert structure design, the connection reliability between the tube body and the metal insert is enhanced. This patent aims to increase the number of uses of the launch tube and the reliability of the overall structure to meet the application requirements of the missile launch tube under extreme working conditions.

[0051] In order to make the technical solution provided by the present invention clearer, two examples are used for illustration:

[0052] Example 1

[0053] The thin-walled launch tube of this embodiment includes an ablation-resistant layer, a structural layer and metal inserts (connecting parts and tensile parts), such as Figure 1 , Figure 2 , Figure 3 As shown. The ablation-resistant layer is a mixture of modified phenolic resin and high-silica tape, with a mass ratio of resin to high-silica fiber tape of 0.4:0.8; the curing process is 130℃ / 120min+150℃ / 60min, and the molding pressure is 0.3MP. By setting a reinforced carrier (high-silica tape) and applying winding tension through a winding process, it is ensured that the ablation-resistant layer is not easy to crack and fall off, and the number of uses of the ablation-resistant layer is increased.

[0054] The metal insert is divided into a connecting part and a tensile part. The two parts are connected by threads, which improves the connection strength between the connecting part and the tensile part. The presence of thorns in the tensile part improves the connection strength between the structural layer and the tensile part, thereby ensuring the connection strength between the metal insert and the composite material.

[0055] Example 2

[0056] The thin-walled launch tube of this embodiment includes an ablation-resistant layer, a structural layer, and metal inserts (connecting parts and tensile parts). Figure 1 , Figure 2 , Figure 3As shown. The ablation-resistant layer is a mixture of hybrid modified silicon-based resin and high-silica tape, with a mass ratio of resin to high-silica fiber tape of 0.5:0.8; the curing process is 140℃ / 60min, and the molding pressure is 0.4MP. By setting a reinforced carrier (high-silica tape) and applying winding tension through a winding process, it is ensured that the ablation-resistant layer is not easy to crack and fall off, and the number of uses of the ablation-resistant layer is increased.

[0057] The metal insert is divided into a connecting part and a tensile part. The two parts are connected by thread + bonding. Coating the threads with thread fastener can effectively prevent the threads from loosening and improve the connection strength between the connecting part and the tensile part. The presence of thorns in the tensile part improves the connection strength between the structural layer and the tensile part, thereby ensuring the connection strength between the metal insert and the composite material.

[0058] Although the above describes the specific implementation mode of the present invention in conjunction with the accompanying drawings, it is not intended to limit the scope of protection of the present invention. Those skilled in the art should understand that various modifications or variations that can be made by those skilled in the art on the basis of the technical solution of the present invention without creative work are still within the scope of protection of the present invention.

Claims

1. A thin-walled composite material launch tube, characterized in that: include: Cylinder and connecting inserts; The cylinder comprises an ablation-resistant layer and a structural layer, wherein the structural layer is located radially outside the ablation-resistant layer; The connecting insert is arranged at the end of the cylinder, and includes a tensile member and a connecting member. The tensile member is an annular member, which is sleeved on the radially outer side of the ablation-resistant layer and is located on the radially inner side of the structural layer. The outer peripheral surface of the tensile member is provided with thorns, and the thorns are embedded in the structural layer. The connecting member is installed at the axial outer end of the tensile member, and the outer peripheral surface of the connecting member is flush with the outer peripheral surface of the structural layer.

2. The thin-walled composite material launch tube according to claim 1, characterized in that: The outer circumference of the tensile member is divided into three sections along the axial direction, the inner end of the outer circumference is a conical structure, the conical structure is embedded between the ablation-resistant layer and the structural layer, the middle section of the outer circumference is provided with the thorns, the outer end of the outer circumference has a concave platform, and the connecting member is installed on the concave platform.

3. The thin-walled composite material launch tube according to claim 1, characterized in that: The connecting member is connected to the tensile member by one or more of threads, adhesives or rivets.

4. The thin-walled composite material launch tube according to claim 1, characterized in that: The ablation-resistant layer is formed by mixing ablation-resistant resin and high-silica fiber cloth tape.

5. The thin-walled composite material launch tube according to claim 4, characterized in that: The ablation-resistant resin is a mixture of one or more of a modified phenolic resin system, an organic-inorganic hybrid carbon-based resin, and a hybrid modified silicon-based resin.

6. The thin-walled composite material launch tube according to claim 4, characterized in that: The mixture of the ablation-resistant resin and the high-silica fiber cloth tape is mixed in a ratio of (0.4-0.5): (0.6-1).

7. The thin-walled composite material launch tube according to claim 1, characterized in that: The structural layer is made of epoxy resin system and carbon fiber.

8. A method for preparing a thin-walled composite material launch tube as claimed in any one of claims 1 to 7, characterized in that: include: Mixing ablation-resistant resin with high-silica fiber cloth tape; Design the molding mold according to the product size and molding process requirements; The prepreg tape is wound onto the mold surface using a tape winding process, and then the surface is covered with tape. The ablation layer is preformed in an autoclave at a heating temperature of 130°C-160°C and a heating pressure of 0.3-0.7MPa. installing the tensile member onto the surface of the ablation layer; The launch tube structure layer is prepared using epoxy resin system and carbon fiber; The cured product is machined and then demoulded to complete the assembly of the connecting inserts and the product is completed.

9. The preparation method according to claim 8, characterized in that: The mass ratio of resin to high-silica fiber tape is 0.4:0.8; the curing process is 130℃ / 120min+150℃ / 60min, and the molding pressure is 0.3MP.

10. The preparation method according to claim 8, characterized in that: The ablation-resistant layer adopts a mixture of hybrid modified silicon-based resin and high-silica fiber tape, and the mass ratio of resin to high-silica fiber tape is 0.5:0.8; the curing process is 140℃ / 60min, and the molding pressure is 0.4MP.

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