Thin-type flight adapter for radial flexible adaptation of missiles

Abstract

This invention provides a thin, flexible adapter for radial adaptation of missiles in the field of missile launch technology. It includes a mounting base and a flexible adapter structure. The inner surface of the mounting base is bonded to the outer surface of the missile body, and both ends of the mounting base are circumferentially secured to the outer surface of the missile body via straps. The inner surface of the flexible adapter structure is bonded to the outer surface of the mounting base, and the two sides of the flexible adapter structure are threaded to the two sides of the mounting base. This invention, by setting a mounting base on the missile body surface and incorporating a flexible adapter structure on the mounting base, reduces the radial dimension of the adapter structure between the missile and the launch tube, increasing the missile loading density; it also enables a launch method without ejected debris during missile launch, improving the safety of ground or shipboard equipment and personnel.

Description

Technical Field

[0001] This invention relates to the field of missile launch technology, and more specifically, to a thin-type flight adapter for radial flexible adaptation of missiles. Background Technology

[0002] To improve the dense loading capability of weapon systems, the radial dimension of missile launch tubes needs to be minimized. Since missiles typically have wings and aerodynamic control surfaces, there is a certain gap between the missile's main body and the inner wall of the launch tube. Furthermore, the missile requires radial support within the launch tube, usually achieved through sliding blocks, rails, or adapters. To fully utilize the gap between the missile and the launch tube created by the wings and aerodynamic control surfaces, a tube-missile adapter system can be used. Traditional adapters require a radial separation mechanism after the missile exits the tube, which occupies the radial space between the tube and the missile. Additionally, the adapter's dispersion after missile exit poses a safety hazard to ground or shipboard equipment and personnel. Summary of the Invention

[0003] To address the shortcomings of existing technologies, the purpose of this invention is to provide a thin-type flight adapter for radial flexible adaptation of missiles.

[0004] According to the present invention, a thin flight adapter for radial flexible adaptation of a missile includes a mounting base and a flexible adaptation structure. The inner surface of the mounting base is bonded to the outer surface of the missile body, and both ends of the mounting base are fixed to the outer surface of the missile body by straps along the circumferential direction.

[0005] The inner surface of the flexible adapter structure is bonded to the outer surface of the mounting base, and the two sides of the flexible adapter structure are threaded to the two sides of the mounting base.

[0006] In some embodiments, the mounting base includes a windward section, a strapping clamping section, and an adapter layer mounting section;

[0007] The windward section has a sloping conical cross-section and is located at both ends of the mounting base;

[0008] The cross-section of the strap clamping section is trapezoidal, and the extension lines of the two waists of the strap clamping section are tangent to the outer circle of the surface of the projectile.

[0009] The adapter layer mounting section is located at the center of the mounting base, and the adapter layer mounting section is provided with an axial limiting groove, which is used to limit the axial movement of the flexible adapter structure.

[0010] In some embodiments, the strap clamping section is provided with a groove, and the size of the strap is matched with the size of the groove.

[0011] In some embodiments, the flexible adapter structure includes a windward surface and an adapter section, the windward surface being disposed at both ends of the adapter section, and the adapter section being provided with a plurality of axial arched through holes.

[0012] In some embodiments, the mounting base is made of high-temperature resistant metal material.

[0013] In some embodiments, the flexible adapter structure is a rubber material flexible adapter structure.

[0014] In some embodiments, the outer surface of the flexible adapter structure is treated with a process of spraying polytetrafluoroethylene powder.

[0015] In some embodiments, the mounting base has multiple threaded holes on both sides, and the flexible adapter structure has multiple through holes on both sides. The two sides of the mounting base and the two sides of the flexible adapter structure are tightly connected to each other through the threaded holes, the through holes, and screws.

[0016] Compared with the prior art, the present invention has the following beneficial effects:

[0017] This invention reduces the radial dimension of the adapter structure between the missile and the launch tube by setting a mounting base on the surface of the missile body and setting a flexible adapter structure on the mounting base, thereby increasing the missile loading density.

[0018] By adopting a flexible adaptable structure with a rubber load-bearing structure, radial flexible support for the missile is achieved inside the launch tube, reducing the impact of transport overload on the missile structure.

[0019] By using straps to secure the adapter of the present invention to the outer surface of the missile body, and simultaneously adhering the adapter of the present invention to the outer surface of the missile body, a launch method without ejected material is achieved during missile launch. The adapter of the present invention will not fall off after the missile is launched from the missile tube, thus improving the safety of ground or shipboard equipment and personnel. Attached Figure Description

[0020] Other features, objects, and advantages of the present invention will become more apparent from the following detailed description of non-limiting embodiments with reference to the accompanying drawings:

[0021] Figure 1 This is a schematic diagram of the overall structure of the present invention;

[0022] Figure 2 This is a schematic diagram of the mounting base structure of the present invention;

[0023] Figure 3 This is a schematic diagram of the flexible adapter structure of the present invention.

[0024] Figure label:

[0025] Mounting base 1 Windward side 21

[0026] Windward section 11, Adaptable section 22

[0027] Strap clamping section 12 Axial arched through hole 221

[0028] Slot 121 Through Hole 23

[0029] Adapter layer installation section 13, strap 3

[0030] Axial limiting groove 131 Projectile 4

[0031] Threaded hole 14, screw 5

[0032] Flexible Adaptive Structure 2 Detailed Implementation

[0033] The present invention will now be described in detail with reference to specific embodiments. These embodiments will help those skilled in the art to further understand the present invention, but do not limit the invention in any way. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present invention. These all fall within the scope of protection of the present invention.

[0034] Example 1

[0035] like Figure 1-3 As shown, the inner surface of the mounting base 1 is an arc surface, and the inner surface of the mounting base 1 is bonded to the outer surface of the projectile 4. The inner surface of the flexible adapter structure 2 is bonded to the outer surface of the mounting base 1, and the two sides of the flexible adapter structure 2 are screwed to the two sides of the mounting base 1 by screws 5. The mounting base 1 and the projectile 4 are tied and fixed in the circumferential direction by the straps 3.

[0036] Specifically, in this embodiment, the mounting base 1 is made of a high-temperature resistant metal material, characterized by low density and good high-temperature mechanical properties. A windward section 11 with a conical structure is provided at the front end of the mounting base 1 to reduce air resistance during missile flight. A strap tightening section 12 is provided on the mounting base 1 for securing the strap 3. The strap tightening section 12 has a trapezoidal structure, and its two waist extension lines are tangent to the outer circle of the missile body 4 surface, increasing the fit between the strap 3, the mounting base 1, and the missile body 4. An axial limiting groove 131 is also provided on the mounting base 1, which serves to axially limit the flexible adapter structure 2.

[0037] Specifically, in this embodiment, the flexible adapter structure 2 is made of rubber material, and its outer surface is coated with polytetrafluoroethylene powder to reduce friction during missile launch. The flexible adapter structure 2 has a windward surface 21 and an adapter section 22. The windward surface 21 is located at both ends of the adapter section 22, and the adapter section 22 adopts a variable structure with uneven elevations. Multiple axial arched through holes 221 are provided on the adapter section 22 to achieve variable stiffness under radial external pressure load conditions. Through this variable stiffness structural design, the force-displacement curve of the adapter section 22 is approximately "J"-shaped, including a flat section and a rising section. This achieves the following during missile loading into the launch tube: in the initial loading section, the flexible adapter structure 2 is easily compressible and deformed radially, resulting in low friction upon entering the tube. In the final loading section, the stiffness of the adapter section 22 on the flexible adapter structure 2 increases rapidly, increasing friction and achieving radial constraint and limitation of the missile.

[0038] Specifically, in this embodiment, during missile transportation, the flexible adapter structure 2 with rubber bearing structure plays a role in radial support for the missile. At the same time, due to the high elasticity of rubber, it can effectively perform shock absorption and buffering during transportation.

[0039] Specifically, in this embodiment, during the missile launch process, the flexible adapter structure 2 with its surface coated with polytetrafluoroethylene powder has a low coefficient of friction with the inner surface of the launch tube, resulting in low friction when the missile exits the tube. At the same time, after the missile exits the tube, the adapter of the present invention follows the missile and does not generate any debris, thereby improving the safety of ground or shipboard equipment and personnel.

[0040] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application 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. Therefore, they should not be construed as limitations on this application.

[0041] Specific embodiments of the present invention have been described above. It should be understood that the present invention is not limited to the specific embodiments described above, and those skilled in the art can make various changes or modifications within the scope of the claims, which do not affect the essence of the present invention. Unless otherwise specified, the embodiments and features described in this application can be arbitrarily combined with each other.

Claims

1. A thin-type flight adapter for radial flexible adaptation of missiles, characterized in that, It includes a mounting base (1) and a flexible adapter structure (2). The inner surface of the mounting base (1) is bonded to the outer surface of the projectile (4), and both ends of the mounting base (1) are tied and fixed to the outer surface of the projectile (4) in the circumferential direction by straps (3). The inner surface of the flexible adapter structure (2) is bonded to the outer surface of the mounting base (1), and the two sides of the flexible adapter structure (2) are threaded to the two sides of the mounting base (1). The mounting base (1) includes a windward section (11), a strapping clamping section (12), and an adapter layer mounting section (13); The windward section (11) has a sloping conical shape in cross section, and the windward section (11) is located at both ends of the mounting base (1); The cross-section of the strap pressing section (12) is trapezoidal, and the two waist extension lines of the strap pressing section (12) are tangent to the outer circle of the surface of the projectile (4); The adapter layer mounting section (13) is located at the center of the mounting base (1), and the adapter layer mounting section (13) is provided with an axial limiting groove (131), which is used to limit the axial movement of the flexible adapter structure (2). The mounting base (1) has multiple threaded holes (14) on both sides, and the flexible adapter structure (2) has multiple through holes (23) on both sides. The two sides of the mounting base (1) and the two sides of the flexible adapter structure (2) are tightly connected to each other through the threaded holes (14), the through holes (23) and the screws (5). The flexible adapter structure (2) includes a windward surface (21) and an adapter section (22). The windward surface (21) is located at both ends of the adapter section (22), and the adapter section (22) is provided with a plurality of axial arched through holes (221).

2. The thin-type flight adapter for radial flexible adaptation of missiles according to claim 1, characterized in that, The strap tightening section (12) is provided with a groove (121), and the size of the strap (3) is matched with the size of the groove (121).

3. The thin-type flight adapter for radial flexible adaptation of missiles according to claim 1, characterized in that, The mounting base (1) is a high-temperature resistant metal mounting base.

4. The thin-type flight adapter for radial flexible adaptation of missiles according to claim 1, characterized in that, The flexible adapter structure (2) is made of rubber material.

5. The thin-type flight adapter for radial flexible adaptation of missiles according to claim 1, characterized in that, The outer surface of the flexible adapter structure (2) is treated with a process of spraying polytetrafluoroethylene powder.

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