Flexible solid-liquid mechanism of launching tube and launching tube

Abstract

The application provides a flexible missile fixing mechanism of a launching tube and a launching tube in the technical field of weapon systems, which comprises a missile, a missile tail hook, a tube body, a supporting ring, a missile fixing support, a missile fixing bolt, a missile fixing arc plate and a rear cover. A plurality of missile tail hooks are evenly and circumferentially arranged on the tail end surface of the missile, the outer wall of the missile tail hook is arranged in abutment with the inner wall of the supporting ring, and the missile tail hook buckle is arranged on the missile fixing arc plate. The upper surface of the supporting ring is arranged in abutment with the end surface of the missile, and the lower surface of the supporting ring is arranged in abutment with the end surface of the missile fixing support. A single missile fixing arc plate is arranged in the inner buckle of the plurality of missile tail hooks, the missile fixing arc plate is connected with the missile fixing support through the missile fixing bolt, one end of the missile fixing support is connected with the tube body, and the other end of the missile fixing support is connected with the rear cover. The application can reliably constrain the missile under storage and transportation conditions and absorb the vibration energy transmitted to the missile by the transportation vehicle through the flexible characteristics, and can realize constraint force switching under the launching condition and reliably release the constraint of the missile.

Description

TECHNICAL FIELD

[0001] The present application relates to the technical field of weapon systems, in particular to a launching tube flexible missile fixing mechanism and a launching tube. BACKGROUND

[0002] Missile fixing is one of the core functions of a launching tube, which plays a role in reliably restraining a missile in tube storage and transportation conditions and reliably releasing the restraint of the missile in launching conditions. Since the demand for restraint force of the missile fixing mechanism is contrary in different conditions, the missile fixing mechanism is generally composed of explosive bolts, longitudinal locks or separation nuts and other pyrotechnics. In transportation and storage conditions, the pyrotechnic unlocking device has strong restraint capability, and before launching, the pyrotechnic unlocking device is unlocked through an ignition circuit, thereby releasing the restraint of the missile. However, in actual use, the pyrotechnic missile fixing device has high cost, increases the complexity of electricity and timing, and has strong rigidity, poor energy absorption and poor anti-vibration effect, which is not conducive to the storage and transportation of the missile.

[0003] Therefore, the industry needs a new type of missile fixing mechanism that can reliably restrain the missile in storage and transportation conditions and absorb the vibration energy transmitted to the missile by the transport vehicle through the flexible characteristics, and can realize restraint force switching and reliably release the restraint of the missile in launching conditions. At the same time, the mechanism should have a simple structure and low cost. SUMMARY

[0004] In view of the defects in the prior art, the purpose of the present application is to provide a launching tube flexible missile fixing mechanism and a launching tube.

[0005] According to the launching tube flexible missile fixing mechanism provided by the present application, the missile, the missile tail hook, the tube body, the support ring, the missile fixing support, the missile fixing bolt, the missile fixing arc plate and the rear cover are included.

[0006] A plurality of missile tail hooks are uniformly and circumferentially arranged on the end surface of the missile tail, the outer wall of the missile tail hook is arranged in abutment with the inner wall of the support ring, and the missile tail hook buckle is arranged on the missile fixing arc plate.

[0007] The upper surface of the support ring is arranged in abutment with the end surface of the missile, and the lower surface of the support ring is arranged in abutment with the end surface of the missile fixing support.

[0008] A single missile fixing arc plate is arranged in the inner buckle of a plurality of missile tail hooks, the missile fixing arc plate is connected to the missile fixing support through the missile fixing bolt, one end of the missile fixing support is connected to the tube body, and the other end of the missile fixing support is connected to the rear cover.

[0009] In some embodiments, the outer wall of the missile fixing arc plate is designed in an arc shape.

[0010] In some embodiments, the missile fixing arc plate constrains the axial degree of freedom of the missile through the missile tail hook.

[0011] In some embodiments, the support ring restricts the outer wall of the missile tail hook, and the missile arc plate restricts the inner wall of the missile tail hook.

[0012] In some embodiments, the upper part of the support ring is in contact with the missile, the bottom of the support ring is fixedly connected to the barrel, and the inner wall of the support ring is in contact with the missile tail hook.

[0013] In some embodiments, the flexible missile support mechanism further comprises a gas generator, and the upper nozzle of the gas generator is opposite to the missile arc plate.

[0014] In some embodiments, the flexible missile support mechanism adopts a ring spoke structure.

[0015] In some embodiments, after the missile tail hook is separated from the support ring, the missile tail hook is expanded outwardly by being pressed by the missile arc plate.

[0016] In some embodiments, the missile arc plate and the missile tail hook are both made of elastic material.

[0017] A launching barrel comprises the flexible missile support mechanism.

[0018] Compared with the prior art, the present application has the following advantages:

[0019] The missile tail hook is installed on the end face of the missile tail, and the outer wall of the missile tail hook is limited in the inner wall of the support ring, while the upper surface of the support ring is attached to the missile, and the lower surface of the support ring is attached to the missile support bracket.

[0020] The missile arc plate is connected to the missile support bracket through missile bolts, and the two ends of the missile support bracket are respectively connected to the barrel and the rear cover.

[0021] The missile can be reliably constrained under storage and transportation conditions, and the vibration energy transmitted to the missile by the transport vehicle can be absorbed through the flexible characteristics. The constraint force can be switched under the launching condition, the constraint of the missile can be reliably released, and the structure is simple and the cost is low. BRIEF DESCRIPTION OF DRAWINGS

[0022] Other features, objects and advantages of the present application will become more apparent from the following detailed description of non-limiting embodiments, made with reference to the accompanying drawings:

[0023] Fig. 1 is a storage and transportation state sectional view of the launching barrel flexible missile support mechanism of the present application;

[0024] Fig. 2 is a launching state sectional view of the launching barrel flexible missile support mechanism of the present application;

[0025] Fig. 3 Figure 1 is a sectional view of the unlocking state of the flexible solid missile mechanism of the launching tube of the present application.

[0026] Reference signs:

[0027] Missile 1 Solid missile support 6

[0028] Missile tail hook 2 Solid missile bolt 7

[0029] Tube body 3 Solid missile arc plate 8

[0030] Support ring 4 Rear cover 9

[0031] Gas generator 5 DETAILED DESCRIPTION

[0032] The present application will be described in detail below with specific examples. The following examples will help those skilled in the art to further understand the present application, but do not limit the present application in any form. It should be noted that those skilled in the art can make several changes and improvements without departing from the concept of the present application. These are within the scope of protection of the present application.

[0033] Example 1

[0034] As shown in Figs. 1-3 , the present application includes missile 1, missile tail hook 2, tube body 3, support ring 4, gas generator 5, solid missile support 6, solid missile bolt 7, solid missile arc plate 8 and rear cover 9. Four missile tail hooks 2 are evenly distributed around the end face of the missile 1, the outer wall of the missile tail hook 2 is arc-shaped and is limited in the inner wall of the annular support ring 4 with a U-shaped cross section. The upper surface of the support ring 4 is attached to the missile 1, and the lower surface of the support ring 4 is attached to the solid missile support 6. One of the four missile tail hooks 2 is an inner recessed solid missile arc plate 8 that can elastically deform, the solid missile arc plate 8 is connected to the solid missile support 6 through the solid missile bolt 7, and the solid missile support 6 is connected to the tube body 3 and the rear cover 9.

[0035] Specifically, in this embodiment, the axial freedom of the missile 1 in use is sequentially transmitted to the tube body 3 and the rear cover 9 through the missile tail hook 2, the solid missile arc plate 8, the solid missile bolt 7, the solid missile support 6, and finally the tube body 3 and the rear cover 9. The swing freedom of the missile 1 is transmitted to the solid missile support 6 through the elastic deformation of the solid missile arc plate 8 and the swing freedom of the solid missile bolt 7, and finally transmitted to the tube body 3 and the rear cover 9.

[0036] Specifically, in the embodiment, the invention exists pre-tightening force in the transport and storage state, the solid missile arc plate 8 is in a compressed state, the missile tail hook 2 is subjected to an expansion force and is transmitted to the support ring 4, thereby forming a larger friction force. The deformation of the solid missile arc plate 8 is less than the design value before the solid missile arc plate 8 reaches instability, at which time the missile tail hook 2 is in the annular constraint of the support ring 4, and the constraint is reliable.

[0037] Specifically, in the embodiment, the invention ignites the gas generator 5 under the launch condition, and the high-pressure and high-temperature gas generated by the gas generator 5 impacts the solid missile arc plate 8. The solid missile arc plate 8 has a large area and is directly opposite the gas generator 5. Under the action of the high-temperature gas pressure, the material of the solid missile arc plate 8 weakens and the whole deforms forward. The missile tail hook 2 obtains a certain release stroke, the missile 1 moves forward and leaves the solid missile effective range of the support ring 4, the annular constraint of the missile tail hook 2 is released, the missile 1 continues to move forward, the missile tail hook 2 pulls the solid missile arc plate 8 and transmits the pulling force to the solid missile bolt 7. Under the joint action of the solid missile bolt 7 and the missile tail hook 2, the solid missile arc plate 8 loses stability and turns over, the constraint of the missile tail hook 2 is released, and the solid missile mechanism completes the unlocking action.

[0038] Specifically, in the embodiment, the solid missile arc plate 8 is an arc-shaped unstable structure that will turn over and lose stability when the central pressure reaches a certain value, release the constraint, and achieve unlocking.

[0039] Specifically, in the embodiment, the constraint stroke of the support ring 4 on the missile tail hook 2 matches the instability stroke of the solid missile arc plate 8.

[0040] Specifically, in the embodiment, the solid missile arc plate 8 is connected with the solid missile support 6 through the solid missile bolt 7 with a swing degree of freedom.

[0041] Specifically, in the embodiment, the solid missile arc plate 8 is directly opposite the upper nozzle of the gas generator 5. Under the initial high-temperature gas pressure sprayed by the gas generator 5, the solid missile arc plate 8 produces reverse deformation and material weakening.

[0042] Specifically, in the embodiment, its feature is that after the missile tail hook 2 leaves the support ring 4, it expands outward under the extrusion of the solid missile arc plate 8, which is conducive to the instability separation of the solid missile arc plate 8.

[0043] Specifically, in the embodiment, the swing degree of freedom of the solid missile bolt 7 and the solid missile arc plate 8 and the missile tail hook 2 realize the flexible adaptation function of the missile 1 in the transportation process.

[0044] Specifically, in the embodiment, under the condition of axial movement of the missile 1, the extrusion force between the solid missile arc plate 8 and the missile tail hook 2 increases, which leads to the increase of the friction force between the missile tail hook 2 and the support ring 4, thereby achieving the function of dissipating kinetic energy.

[0045] Embodiment 2

[0046] A launch tube comprising the launch tube flexible solid mechanism of embodiment 1.

[0047] In the description of the present application, it needs to be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer" and the like 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 the present application and simplifying the description, and do not indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore cannot be understood as a limitation on the present application.

[0048] The specific embodiments of the present application are described above. It needs to be understood that the present application is not limited to the above specific embodiments, and various changes or modifications can be made by those skilled in the art within the scope of the claims, which does not affect the essential content of the present application. The embodiments of the present application and the features in the embodiments can be arbitrarily combined with each other without conflict.

Claims

1. A launch tube flexible solid motor mechanism, characterized by, Missile (1), missile tail hook (2), barrel (3), support ring (4), missile support bracket (6), missile bolt (7), missile arc plate (8) and rear cover (9); A plurality of missile tail hooks (2) are evenly distributed on the tail end face of the missile (1), the outer wall of the missile tail hook (2) is arranged in close contact with the inner wall of the support ring (4), and the missile tail hook (2) is clamped on the missile arc plate (8); The upper surface of the support ring (4) is arranged in close contact with the end face of the missile (1), and the lower surface of the support ring (4) is arranged in close contact with the end face of the missile support bracket (6); A single missile arc plate (8) is arranged in the inner buckle of a plurality of missile tail hooks (2), the missile arc plate (8) is connected to the missile support bracket (6) through the missile bolt (7), one end of the missile support bracket (6) is connected to the barrel (3), and the other end of the missile support bracket (6) is connected to the rear cover (9); The outer wall of the missile arc plate (8) is designed in an arc shape; The missile arc plate (8) restricts the axial freedom of the missile (1) through the missile tail hook (2); The support ring (4) is arranged outside the missile tail hook (2), and the missile arc plate (8) is arranged inside the missile tail hook (2); It also includes a gas generator (5), and the upper nozzle of the gas generator (5) is arranged opposite to the missile arc plate (8); The missile support bracket (6) adopts a ring spoke structure; The missile arc plate (8) is an arc unstable structure, which will overturn and lose stability when the central pressure reaches a preset value, release the constraint, and achieve unlocking.

2. The launch can flexible solid motor mechanism of claim 1, wherein, The upper part of the support ring (4) is arranged in contact with the missile (1), the bottom of the support ring (4) is fixedly connected with the barrel (3), and the inner wall of the support ring (4) is arranged in contact with the missile tail hook (2).

3. The launch can flexible solid motor mechanism of claim 1, wherein, After the missile tail hook (2) is separated from the support ring (4), the missile tail hook (2) is arranged to be extruded and expanded outward through the missile arc plate (8).

4. The launch can flexible solid motor mechanism of claim 1, wherein, The missile arc plate (8) and the missile tail hook (2) are both made of elastic material.

5. A launch tube characterized by, The launching barrel flexible missile fixing mechanism comprises the launching barrel flexible missile fixing mechanism according to any one of claims 1-4.

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