Lock bullet structure

Abstract

The utility model provides a missile locking structure which solves the problem that a small-caliber missile is not easy to lock and go out of a chamber in a limited space. A bullet locking structure comprises a bullet support body, a mounting groove is formed in the front end of the bullet support body, a cushion block is arranged in the mounting groove, a positioning hole is formed in the side wall of the bullet support body, a lock hook and the cushion block are pressed in the mounting groove after a positioning screw penetrates through the positioning hole, and an arc-shaped thin-wall face is arranged in the circumferential direction of the front end of the bullet support body. The rear end of the sabot body is provided with a groove used for acting on high-pressure fuel gas. By the adoption of the locking structure, enough locking force can be provided for the barrel-loaded missile, it can be guaranteed that the missile smoothly exits from a chamber during launching, the locking structure is simple in structure, the locking hook, the gasket, the mounting groove and the positioning screw are combined and locked with the tail of the missile, connection of the missile locking structure and the missile is achieved, the machining technology is simple, and the space of the tail of the missile is saved.

Description

Technical Field

[0001] The present invention relates to the technical field of canister missiles, and particularly to a missile locking structure for canisters. Background Art

[0002] The locking structure is an important part of a canister missile. This mechanism needs to meet the requirement of non-destructive drop height in the missile safety design, ensure reliable fixation of the missile in the launch tube, and enable the missile to smoothly exit the tube during launch. Since this device needs to provide a large locking force to meet the requirement of non-destructive drop in the design, but the space at the missile tail is small and the size of the parts is limited, it is difficult to coordinate the design and the process. Utility Model Content

[0003] The present utility model provides a missile locking structure, which solves the problems that it is not easy to lock and the missile cannot exit the tube smoothly in a limited space for small-caliber missiles.

[0004] The technical solution of the present utility model is realized as follows:

[0005] A missile locking structure includes a projectile support body. An installation groove is provided at the front end of the projectile support body. A cushion block is arranged in the installation groove. A positioning hole is provided on the side wall of the projectile support body. After a positioning screw passes through the positioning hole, a locking hook and the cushion block are pressed tightly in the installation groove. An arc-shaped thin wall surface is provided circumferentially at the front end of the projectile support body. A groove for the action of high-pressure gas is provided at the rear end of the projectile support body.

[0006] A ring-shaped positioning platform adapted to the tail of the missile body is provided at the front end of the projectile support body, and a limiting block is provided on the ring-shaped positioning platform.

[0007] An airtight groove is provided circumferentially on the projectile support body.

[0008] Four pin holes are evenly distributed in the circumferential direction at the rear end of the projectile support body, and the pin holes are used for the locking connection between the tube and the missile.

[0009] Using the locking structure of the present invention can provide sufficient locking force for the canister missile and ensure that the missile can smoothly exit the tube during launch. The solution of this application has a simple structure. The locking hook, gasket, installation groove and positioning screw are combined with the missile tail to realize the connection between the locking structure and the missile. The processing technology is simple and the space at the missile tail is saved. Brief Description of the Drawings

[0010] In order to more clearly illustrate the technical solutions in the embodiments of the present utility model or the prior art, the following will briefly introduce the drawings required for use in the description of the embodiments or the prior art. Obviously, the following drawings are only some embodiments of the present utility model. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0011] Figure 1It is a schematic structural diagram of the present utility model;

[0012] Figure 2 It is an axonometric view of the present utility model;

[0013] Figure 3 It is an axonometric view of the sabot body;

[0014] Figure 4 It is an axonometric view of the locking hook;

[0015] Figure 5 It is an axonometric view of the spacer block;

[0016] Wherein: locking hook 1, spacer block 2, positioning screw 3, sabot body 4, mounting groove 5, arc-shaped thin-walled surface 6, annular positioning platform 7, limit block 8, gas-tightening groove 9, pin hole 10, groove 11. Specific embodiments

[0017] Next, the technical solutions in the embodiments of the present utility model will be clearly and completely described in conjunction with the accompanying drawings in the embodiments of the present utility model. Obviously, the described embodiments are only a part of the embodiments of the present utility model, rather than all the embodiments. Based on the embodiments of the present utility model, all other embodiments obtained by those of ordinary skill in the art without creative efforts shall fall within the protection scope of the present utility model.

[0018] As Figures 1 to 5 shown, a locking and loading structure includes a sabot body 4. An installation groove 5 is provided at the front end of the sabot body 4. The spacer block 2 is arranged in the installation groove 5. A positioning hole is provided on the side wall of the sabot body 4. After the positioning screw 3 passes through the positioning hole, the locking hook 1 and the spacer block 2 are pressed tightly in the installation groove 5. An arc-shaped thin-walled surface 6 is provided circumferentially at the front end of the sabot body 4. A groove 11 for the action of high-pressure gas is provided at the rear end of the sabot body 4. Four equally distributed pin holes 10 are provided on the circumference at the rear end of the sabot body 4 to provide a pin locking connection between the tube and the missile. The arc-shaped thin-walled surface 6 is an energy-absorbing structure. When the locking and loading structure reaches the stop position at the muzzle of the launch tube during missile launch, the locking and loading structure stays at the muzzle, and the arc-shaped thin-walled surface 6 absorbs energy and deforms to buffer the vibration and impact received by the missile.

[0019] In this application, the sabot body 4 is the main part of the locking and loading structure, and its material is aluminum alloy 2A12-T4, etc. The material of the locking hook is 65Mn spring steel, etc. After the heat treatment process, the performance meets the locking and loading requirements in the design specifications. The locking hook 1 is combined with the tail of the missile to lock, realizing the connection between the locking and loading structure and the missile.

[0020] The working principle of this application is as follows: When this application is launched with the missile to the muzzle stop position of the launch tube, the missile locking structure stays at the muzzle. The arc-shaped thin wall surface 6 absorbs energy and deforms, buffering the vibration and impact on the missile. The groove 11 at the rear side of the missile locking structure is the acting end of the high-pressure gas, and a gas-tight groove 9 is provided circumferentially to prevent the forward leakage of the high-pressure gas. The locking force of the missile locking structure is provided by four groups of locking hooks on it. A cushion block is placed below each group of locking hooks and is fixedly connected to the sabot body through a positioning screw.

[0021] Preferably, the front end of the sabot body 4 is provided with an annular positioning platform 7 adapted to the tail of the missile body, and a limiting block 8 is provided on the annular positioning platform 7. The annular positioning platform 7 cooperates with the tail structure of the missile body, and the limiting block 8 is used for precise positioning and limiting during the cooperation.

[0022] The sabot body 4 is provided with a gas-tight groove 9 circumferentially. When the gunpowder gas passes through the gas-tight groove 9, the volume at this place expands, causing the pressure of the sabot body to drop, forming a vortex and changing the flow direction. After multiple expansions, the flow rate slows down. This gas-tight groove structure can play a role in blocking the leakage of the gas.

[0023] The working process of this invention is as follows: The annular positioning platform 7 is butted against the groove at the tail of the missile. Four groups of locking hooks 1 and gaskets 2 are placed into the corresponding installation grooves of the sabot body. After being placed in place, the positioning screws 3 are tightened to complete the locking connection between the missile locking structure and the missile. After the missile enters the launch tube, the sabot body 4 is aligned with the corresponding pin holes 10 on the launch tube, and the launch tube and the missile locking structure are connected by connecting pins, thereby completing the locking connection between the launch tube and the missile.

[0024] When the missile is launched, the rear end of the missile locking structure is pushed by the high-pressure gas in the launch tube, cutting the connecting pin between the tube and the missile, and pushing the missile body to move towards the muzzle of the launch tube. When the missile locking structure moves with the missile to the muzzle stop position of the launch tube, the missile locking structure stays at the muzzle, and the missile breaks free from the locking hooks and flies out of the launch tube.

[0025] The above are only the preferred embodiments of the present utility model and are not intended to limit the present utility model. Any modifications, equivalent replacements, improvements, etc. made within the spirit and principle of the present utility model shall be included within the protection scope of the present utility model.

Claims

1. A lock bullet structure, comprising a bullet tray body (4), characterized in that: The front end of the sabot body (4) is provided with an installation groove (5), the spacer block (2) is arranged in the installation groove (5), positioning holes are provided on the side wall of the sabot body (4), and after the positioning screw (3) passes through the positioning holes, the locking hook (1) and the spacer block (2) are pressed in the installation groove (5). An arc-shaped thin wall surface (6) is provided circumferentially at the front end of the sabot body (4), and a groove (11) for the action of high-pressure gas is provided at the rear end of the sabot body (4).

2. The lock spring structure according to claim 1, wherein: The front end of the sabot body (4) is provided with an annular positioning platform (7) adapted to the tail of the projectile body, and a limiting block (8) is provided on the annular positioning platform (7).

3. The lock spring structure according to claim 1, wherein: An airtight groove (9) is provided circumferentially on the sabot body (4).

4. The lock spring structure according to any one of claims 1 to 3, characterized in that: Four pin holes (10) are evenly distributed in the circumferential direction at the rear end of the sabot body (4), and the pin holes (10) are used for the locking connection between the cylinder and the projectile.

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