A processing technology of a launching tube

Abstract

The application discloses a processing technology of a launching cylinder, and comprises the following steps: S1, processing an aluminum alloy inner liner and a composite longitudinal reinforcement; the composite longitudinal reinforcement is made of carbon fiber composite material, the cross section of the composite longitudinal reinforcement is in a hat type, and the recesses of the composite longitudinal reinforcement are sequentially filled with a first heat preservation layer and a first anti-penetration protection layer to form a composite reinforcement; S2, winding carbon fiber composite material on the surface of the aluminum alloy inner liner as a composite middle liner; S3, cementing a plurality of composite reinforcements on the surface of the composite middle liner; S4, sequentially laying a second heat preservation layer and a second anti-penetration protection layer on the surface of the cylinder formed in the step S3; S5, laying a shielding net on the surface of the cylinder formed in the step S4; and S6, laying carbon fiber composite material on the surface of the cylinder formed in the step S5. The launching cylinder prepared by the application has the characteristics of high mechanical property, high anti-penetration performance, high electromagnetic shielding performance and high heat preservation and insulation performance, and meets the basic performance requirements and functional requirements of the launching cylinder in storage, hoisting, transportation, erecting and launching.

Description

Technical Field

[0001] This invention relates to the field of launch tube technology, and in particular to a manufacturing process for a launch tube. Background Technology

[0002] As modern military operations place increasingly higher demands on weapon systems, composite material launch tubes that combine mechanical properties, thermal insulation properties, and electromagnetic shielding properties have been gradually developed and applied.

[0003] However, existing composite material launch tubes (such as patent number CN103322854B) simply involve laying multiple layers of material sequentially and fixing them using conventional curing processes. This approach doesn't consider the bonding strength of the multi-layered composite structure. Because different materials have different coefficients of thermal expansion, laying each functional layer sequentially can lead to insufficient bonding strength. Furthermore, the different shrinkage rates of different functional layers due to environmental influences can affect the connection between them, potentially causing premature launch tube failure. Additionally, existing technologies don't consider the impact of different material winding directions on performance, often only increasing the thickness of each functional layer to improve performance, thus increasing the overall weight and cost of the launch tube.

[0004] The launch tube disclosed in patent number CN202010824801.5 consists of an inner tube and an outer tube. In order to balance the requirements of low weight and connection between the inner and outer tubes, it is proposed to use longitudinal ribs to co-cur the inner and outer tubes. However, the launch tube does not address the design for heat preservation, penetration protection, etc., nor does it indicate how to achieve the effective performance of each function through reasonable layer distribution and thickness distribution. Summary of the Invention

[0005] To address the technical problem in existing technologies where the bonding strength of the launch tube is insufficient to withstand specified stress values, leading to premature explosion of the launch tube, this invention provides a manufacturing process for the launch tube to solve the aforementioned problem.

[0006] The technical solution adopted by the present invention to solve its technical problem is: a processing technology for a launch tube, including S1: processing an aluminum alloy liner and a composite longitudinal rib; using carbon fiber composite material to process the composite longitudinal rib, the cross-section of the composite longitudinal rib is cap-shaped, and the recess of the composite longitudinal rib is sequentially filled with a first heat insulation layer and a first anti-penetration protective layer to form a composite reinforcement.

[0007] S2: Carbon fiber composite material is wound around the surface of the aluminum alloy inner lining as a composite middle lining.

[0008] S3: Multiple composite reinforcements are bonded to the surface of the composite lining, and the bottom of the first anti-penetration protective layer and the composite longitudinal ribs are bonded to the composite lining.

[0009] S4: The second insulation layer and the second anti-penetration protective layer are sequentially laid on the outer area of ​​the cylinder surface formed in step S3.

[0010] S5: A shielding mesh is laid on the surface of the cylinder formed in step S4.

[0011] S6: A carbon fiber composite material is laid on the surface of the cylinder formed in step S5 as an outer skin layer.

[0012] S7: The top of the composite longitudinal reinforcement is bonded to the shielding mesh and the outer skin layer.

[0013] Furthermore, both the first and second insulation layers are laminated aerogels, and both the first and second anti-penetration protective layers are laminated UHMWPE composite materials.

[0014] Furthermore, the inner surface of the first anti-penetration protective layer and the bottom surface of the composite longitudinal rib are on the same arc-shaped surface.

[0015] Furthermore, the thickness of the aluminum alloy inner lining is 7mm~8mm, the thickness of the composite middle lining is 4mm~6mm, the thickness of the composite longitudinal rib is 4mm~6mm, the thickness of the first insulation layer and the second insulation layer is 15mm~18mm, the thickness of the first anti-penetration protective layer and the second anti-penetration protective layer is 15mm~18mm, the thickness of the shielding mesh is 0.095mm~0.097mm, and the thickness of the outer skin layer is 4mm~6mm.

[0016] Furthermore, the outermost laying angle of the composite liner is 45°~60° with the central axis of the launch tube, and the outermost laying angle of the outer skin layer is 80°~90° with the central axis of the launch tube.

[0017] Furthermore, a fiberglass liner is laid between the aluminum alloy inner liner and the composite inner liner, and the fiberglass liner is formed of fiberglass or fiberglass felt.

[0018] Furthermore, the thickness of the fiberglass liner is 0.3mm to 0.5mm.

[0019] Furthermore, the outer surface of the outer skin layer is wrapped with multiple ring ribs, the ring ribs being made of the same material as the outer skin layer, and any one or more ring ribs serving as an erection fulcrum or a rotation fulcrum.

[0020] Furthermore, the outer skin layer is coated with a reflective, heat-insulating, and hydrophobic coating, and the inner surface of the aluminum alloy liner is coated with a heat-insulating and friction-reducing coating.

[0021] The beneficial effects of this invention are: (1) The launch tube prepared by the processing technology of the launch tube described in this invention has the characteristics of high mechanical properties, penetration protection performance, electromagnetic shielding performance and strong thermal insulation performance. The overall weight is less than 7t, which meets the basic performance and functional requirements of the launch tube for storage, hoisting, transportation, erection and launch.

[0022] (2) The manufacturing process of the launch tube described in this invention connects the inner and outer layers of the tube body through the composite longitudinal ribs of the cap shape, and at the same time combines the laying method of each layer of material and the reasonable configuration of the material thickness to make the launch tube structure more reliable. Attached Figure Description

[0023] The present invention will be further described below with reference to the accompanying drawings and embodiments.

[0024] Figure 1 This is a flowchart of the manufacturing process of the launching tube described in this invention; Figure 2 This is a perspective view of a launch tube prepared using the process described in this invention; Figure 3 This is a cross-sectional view of the end face of the launch tube prepared using the process described in this invention; Figure 4 yes Figure 3 Enlarged view of point a in the middle.

[0025] In the figure, 1. Aluminum alloy lining, 2. Composite longitudinal rib, 201. Protruding part, 202. Flanged edge, 3. First insulation layer, 4. First anti-penetration protective layer, 5. Composite middle lining, 6. Second insulation layer, 7. Second anti-penetration protective layer, 8. Shielding mesh, 9. Outer skin layer, 10. Fiberglass middle lining, 11. Ring rib, 12. Reflective thermal insulation and hydrophobic coating, 13. Thermal insulation and friction reduction coating. Detailed Implementation

[0026] Embodiments of the present invention are described in detail below. Examples of these embodiments are shown in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the present invention, and should not be construed as limiting the present invention.

[0027] like Figure 1 As shown, a manufacturing process for a launch tube includes the following steps: S1: Process the aluminum alloy inner liner 1 and the composite longitudinal rib 2; use carbon fiber composite material to process the composite longitudinal rib 2, the cross-section of the composite longitudinal rib 2 is cap-shaped, and the recess of the composite longitudinal rib 2 is sequentially filled with the first thermal insulation layer 3 and the first anti-penetration protective layer 4 to form a composite reinforcement. That is, the composite longitudinal rib 2 has a protruding part 201 and a flange 202, and the first thermal insulation layer 3 and the first anti-penetration protective layer 4 are located in the protruding part 201.

[0028] S2: Carbon fiber composite material is wound around the surface of aluminum alloy inner liner 1 as composite middle liner 5.

[0029] S3: Multiple composite reinforcements are bonded to the surface of the composite lining 5, and the bottom of the first penetration-resistant protective layer 4 and the composite longitudinal rib 2 are bonded to the composite lining 5. That is, within the protruding portion 201, the first insulation layer 3 is located outside the first penetration-resistant protective layer 4.

[0030] S4: The second insulation layer 6 and the second anti-penetration protective layer 7 are sequentially laid on the outer area of ​​the composite reinforcement on the surface of the cylinder formed in step S3, that is, outside the protrusion 201, the second insulation layer 6 is located inside the second anti-penetration protective layer 7.

[0031] S5: A shielding mesh 8 is laid on the surface of the cylinder formed in step S4.

[0032] S6: A carbon fiber composite material is laid on the surface of the cylinder formed in step S5 as an outer skin layer 9.

[0033] S7: The top of the composite longitudinal rib 2 is bonded to the shielding mesh 8 and the outer skin layer 9.

[0034] The difference between this invention and the prior art lies in the following: Figure 3 and Figure 4 As shown, multiple composite longitudinal ribs 2 connect the inner and outer layers of the launch tube. The composite longitudinal ribs 2 are made of the same material as the composite inner lining 5 and the outer skin layer 9 (the shielding mesh 8 has a mesh structure and will not affect the connection between the outer skin layer 9 and the composite longitudinal ribs 2). The connection strength of the three is higher, and the connection is less likely to break due to the influence of the coefficient of thermal expansion. The setting of composite longitudinal ribs 2 can also improve the stress resistance and bending resistance of the tube. Secondly, the insulation layer and the penetration-resistant protective layer are laid in opposite positions inside and outside the composite longitudinal ribs 2, that is, they are laid in a staggered manner. Therefore, they are no longer a single material in the circumferential direction. Furthermore, the composite longitudinal ribs 2 divide the tube into multiple segments in the circumferential direction. When the temperature changes abruptly and the expansion of different materials changes, each layer of material can adjust its radial deformation on the inner and outer sides of the composite longitudinal ribs 2, reducing circumferential misalignment and thus reducing the impact of different material parameters on the structural strength. Solving this technical problem can greatly improve the internal pressure resistance and bending resistance of the launch tube.

[0035] In addition to addressing the stress issues at the connection points of the various layers, the launch tube also needs to address the stress concentration problem of the overall structure. The more severe the stress concentration, the greater the possibility of the launch tube exploding. The internal pressure and bending force experienced by the launch tube under the same working conditions are mainly related to the thickness distribution and material selection of each layer. The launch tube designed below meets the following performance requirements proposed by the customer: (1) Mechanical performance: It can withstand a peak internal pressure of 0.8MPa, a peak temperature of 1000℃, a projectile weight of 50t, and a peak load of no more than 70t at the erection support point. (2) Penetration protection performance: The overall structure can withstand the incidence of ordinary rifle bullets at a distance of 100° from the normal angle. (3) Electromagnetic shielding performance: The shielding effectiveness against electromagnetic interference in the low-frequency and high-frequency bands is no less than 40dB. (4) Thermal insulation performance: The launch tube can withstand the specified solar radiation intensity (total radiation intensity of 1120W / m²) under the specified solar radiation intensity conditions. 2 After continuous irradiation for 4 hours, the temperature inside the tube should not exceed 35℃.

[0036] Both the first insulation layer 3 and the second insulation layer 6 are preferably laminated aerogels. Aerogels have low density and ultra-low thermal conductivity, are completely hydrophobic, and have good fire-retardant properties. The insulation layers can be made of aerogel felt, and the material can be cut to size. The aerogel is laid and cut along with the surface, and can be fixed with pressure-sensitive tape. The first penetration-resistant protective layer 4 and the second penetration-resistant protective layer 7 are both laminated UHMWPE composite materials. UHMWPE composite materials are ultra-high molecular weight polyethylene fiber materials, which can be machined into a specified arc shape for laying and fixing. The shielding mesh 8 can be two layers of copper mesh.

[0037] The inner surface of the first anti-penetration protective layer 4 and the bottom surface of the composite longitudinal rib 2 are preferably on the same arc surface. This increases the bonding area between the entire composite longitudinal rib 2 and the composite lining 5. During fixing, the inner surface of the flange 202 of the composite longitudinal rib 2 is directly bonded to the composite lining 5. The bottom surface of the composite longitudinal rib 2 is the inner surface of the flange 202.

[0038] The thickness of each material has a certain impact on the mechanical properties, functionality, and quality of the launch tube. In the preferred embodiment of the present invention, the thickness of the aluminum alloy inner liner 1 is 7mm~8mm, the thickness of the composite middle liner 5 is 4mm~6mm, the thickness of the composite longitudinal rib 2 is 4mm~6mm, the thickness of the first insulation layer 3 and the second insulation layer 6 is 15mm~18mm, the thickness of the first anti-penetration protective layer 4 and the second anti-penetration protective layer 7 is 15mm~18mm, the thickness of the shielding mesh 8 is 0.095mm~0.097mm, and the thickness of the outer skin layer 9 is 4mm~6mm.

[0039] The influence of varying layer thicknesses on the cylinder's internal pressure resistance is ranked as follows: Composite inner lining 5 = Outer skin layer 9 > Aluminum alloy inner lining 1. The influence of varying layer thicknesses on the cylinder's bending resistance is ranked as follows: Outer skin layer 9 > Composite inner lining 5 > Aluminum alloy inner lining 1. The thickness variations of other functional layers have the weakest impact on mechanical properties. When the composite inner lining 5, outer skin layer 9, and composite longitudinal rib 2 are made of the same material and have a thickness of 4mm to 6mm, the mechanical properties of the cylinder can meet the specified requirements while ensuring a relatively low cylinder mass.

[0040] For the aluminum alloy liner 1, its metallic material ensures good mechanical properties. Simulation experiments show that the lower the thickness of the aluminum alloy liner 1, the greater the stress it experiences. However, increasing the thickness of the aluminum alloy liner 1 increases costs. Combining the data in Table 1, comparing Scheme 1 and Scheme 3, under the condition that the thickness of all other layers is the same and the internal pressure or bending force is the same, when the aluminum alloy liner 1 is 5mm thick, the maximum stress and corresponding stress deformation of the cylinder are significantly higher than when the aluminum alloy liner 1 is 7mm thick, increasing the possibility of explosion. The same applies to Scheme 2 and Scheme 4. Comparing Scheme 1 and Scheme 2, since the composite liner 5 and the outer skin layer 9 are made of the same material, thinning the composite liner 5 while thickening the outer skin layer 9 has little impact on the mechanical properties of the cylinder.

[0041] Table 1 Simulation results of different launch tube structural schemes

[0042] For the composite liner 5 and outer skin layer 9, which have a significant impact on mechanical properties, the laying angle of their materials also has a certain influence on stress. When the outermost laying angle of the composite liner 5 is 45° with the central axis of the launch tube, the bending performance of the launch tube is optimal. When the outermost laying angle of the composite liner 5 and outer skin layer 9 is 80°~90° with the central axis of the launch tube, the resistance to internal pressure of the launch tube is optimal. This invention combines the two, selecting an angle of 80°~90° between the outermost laying angle of the outer skin layer 9 and the central axis of the launch tube to ensure good resistance to internal pressure, while the angle of 45°~60° between the outermost laying angle of the composite liner 5 and the central axis of the launch tube coordinates the bending performance and resistance to internal pressure of the launch tube.

[0043] For the aluminum alloy inner liner 1 and the composite intermediate liner 5 made of composite materials, considering the difference in their coefficients of thermal expansion and the resulting potential for corrosion at different potentials, this invention preferably includes a fiberglass intermediate liner 10 between the aluminum alloy inner liner 1 and the composite intermediate liner 5. The fiberglass intermediate liner 10 is formed of fiberglass or fiberglass mat. The thickness of the fiberglass intermediate liner 10 is 0.3mm to 0.5mm. The fiberglass intermediate liner 10 uses a high-toughness resin to isolate the carbon fiber and the metal inner liner from potential corrosion at different potentials, preventing delamination.

[0044] like Figure 2 As shown, the outer surface of the outer skin layer 9 can also be wrapped with multiple ring ribs 11. The ring ribs 11 are made of the same material as the outer skin layer 9, and any one or more ring ribs 11 serve as the erection support point or the rotation support point. The ring ribs 11 can improve the overall mechanical properties of the launch tube on the one hand, and provide special reinforcement at the erection support point and the rotation support point on the other hand, so as to ensure the bending and torsional stiffness and strength of the overall structure.

[0045] For the thermal insulation of the launch tube, this invention features a triple insulation design, such as... Figure 4 As shown: The first layer of insulation is a reflective thermal insulation and hydrophobic coating 12 applied to the outer skin layer 9, which effectively reflects more than 85% of solar radiation energy and provides a certain degree of thermal barrier against the conduction of external hot air, reducing the impact of solar radiation from the outermost layer.

[0046] The second layer of insulation consists of the first insulation layer 3 and the second insulation layer 6 in the internal structure, the principle of which has been explained above.

[0047] The third layer of insulation is achieved by coating the inner surface of the aluminum alloy liner 1 with a heat-insulating and friction-reducing coating 13, which minimizes the heat transfer and heat radiation effects of high-temperature gases on the aluminum alloy liner 1 and the composite liner 5 during launch, and avoids the degradation of the performance of metal and composite materials caused by high temperatures.

[0048] This triple insulation system provides insulation protection from the inside, middle, and outside, ensuring that the temperature of the cylinder itself is minimized by the environment.

[0049] In the description of this invention, it should be understood that the terms "thickness", "inner", "outer", "axial", "radial", "circumferential", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings, and are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0050] Furthermore, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. In the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0051] In this specification, the illustrative expressions of the terms do not necessarily refer to the same embodiments. Moreover, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments.

[0052] Based on the above-described preferred embodiments of the present invention, and through the foregoing description, those skilled in the art can make various changes and modifications without departing from the inventive concept. The technical scope of this invention is not limited to the contents of the specification, but must be determined according to the scope of the claims.

Claims

1. A manufacturing process for a launching tube, characterized in that, include: S1: Process aluminum alloy lining (1) and composite longitudinal rib (2); use carbon fiber composite material to process composite longitudinal rib (2), the cross-section of the composite longitudinal rib (2) is cap-shaped, the recess of the composite longitudinal rib (2) is filled with the first insulation layer (3) and the first anti-penetration protective layer (4) in sequence to form a composite reinforcement, the composite longitudinal rib (2) has a protruding part (201) and a flange (202), the first insulation layer (3) and the first anti-penetration protective layer (4) are located in the protruding part (201); S2: A carbon fiber composite material is wound around the surface of the aluminum alloy inner liner (1) as a composite middle liner (5); S3: Multiple composite reinforcements are bonded to the surface of the composite lining (5), the bottom of the first anti-penetration protective layer (4) and the composite longitudinal rib (2) are bonded to the composite lining (5), and the first insulation layer (3) is located outside the first anti-penetration protective layer (4) in the protruding part (201). S4: The second insulation layer (6) and the second anti-penetration protective layer (7) are sequentially laid on the outer area of ​​the composite reinforcement on the surface of the cylinder formed in step S3. Outside the protruding part (201), the second insulation layer (6) is located inside the second anti-penetration protective layer (7). S5: A shielding mesh (8) is laid on the surface of the cylinder formed in step S4. S6: A carbon fiber composite material is laid on the surface of the cylinder formed in step S5 as an outer skin layer (9). S7: The top of the composite longitudinal rib (2) is bonded to the shielding mesh (8) and the outer skin layer (9).

2. The processing technology of the launching tube according to claim 1, characterized in that: The first insulation layer (3) and the second insulation layer (6) are both laminated aerogels, and the first anti-penetration protective layer (4) and the second anti-penetration protective layer (7) are both laminated UHMWPE composite materials.

3. The processing technology of the launching tube according to claim 1, characterized in that: The inner surface of the first anti-penetration protective layer (4) and the bottom surface of the composite longitudinal rib (2) are on the same arc surface.

4. The processing technology of the launching tube according to claim 1, characterized in that: The thickness of the aluminum alloy inner lining (1) is 7mm~8mm, the thickness of the composite middle lining (5) is 4mm~6mm, the thickness of the composite longitudinal rib (2) is 4mm~6mm, the thickness of the first insulation layer (3) and the second insulation layer (6) is 15mm~18mm, the thickness of the first anti-penetration protective layer (4) and the second anti-penetration protective layer (7) is 15mm~18mm, the thickness of the shielding mesh (8) is 0.095mm~0.097mm, and the thickness of the outer skin layer (9) is 4mm~6mm.

5. The processing technology of the launching tube according to claim 2, characterized in that: The outermost laying angle of the composite liner (5) is 45°~60° with the central axis of the launch tube, and the outermost laying angle of the outer skin layer (9) is 80°~90° with the central axis of the launch tube.

6. The processing technology of the launching tube according to claim 1, characterized in that: A fiberglass liner (10) is also laid between the aluminum alloy inner liner (1) and the composite inner liner (5). The fiberglass liner (10) is formed of fiberglass or fiberglass felt.

7. The processing technology of the launching tube according to claim 6, characterized in that: The thickness of the fiberglass liner (10) is 0.3mm~0.5mm.

8. The processing technology of the launching tube according to claim 1, characterized in that: The outer surface of the outer skin layer (9) is wrapped with multiple ring ribs (11), the ring ribs (11) are made of the same material as the outer skin layer (9), and any one or more ring ribs (11) serve as the starting point or rotation point.

9. The processing technology of the launching tube according to claim 1, characterized in that: The outer skin layer (9) is coated with a reflective heat-insulating and hydrophobic coating (12), and the inner surface of the aluminum alloy liner (1) is coated with a heat-insulating and friction-reducing coating (13).

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