Pneumatic launching device for patrol ammunition

Abstract

The invention discloses a pneumatic launching device for a patrolling ammunition. The pneumatic launching device is used for providing an initial speed when the patrolling ammunition takes off. The pneumatic launching device comprises a launching tube, a projectile support, a rotatable base and a self-locking mechanism; wherein the rotatable base and the self-locking mechanism are fixed on the launching tube; the sabot is arranged in the tube from the upper part of the launching tube, and the outer surface of the sabot is in contact with the inner surface of the tube; and the self-locking mechanism is arranged at the bottom in the pipe. By arranging the adjustable self-locking mechanism, the launching efficiency can be improved, the launching speed can be increased, the energy loss can be reduced and the like under the condition of the same air supply amount.

Description

Technical Field

[0001] The invention belongs to the technical field of ejection-takeoff type unmanned aerial vehicles and loitering missiles, and in particular to a pneumatic launching device for loitering missiles. Background Art

[0002] Cruise missiles are a product of the integration of UAV technology and missile technology. Their launch methods have evolved from a single airborne launch to a variety of launch methods. According to the launch power device, they can be divided into two launch methods: hot launch and cold launch. Among them, the compressed air type in cold launch is more widely used.

[0003] The diameter of the existing individual cruise missile launcher is generally similar to that of the cruise missile. A sabot is set between the cruise missile and the high-pressure gas. The high-pressure gas acts on the sabot, which pushes the cruise missile to accelerate out of the tube. The compressed air cold launch system has the advantages of no need for thermal protection, small infrared exposure characteristics, good environmental adaptability and high equipment reuse rate. However, the existing compressed air pneumatic launcher has low energy utilization efficiency, which will cause more energy loss, and it is difficult to control the internal ballistic parameters during the launch process. Summary of the invention

[0004] The purpose of the present invention is to provide a pneumatic launching device for a cruise missile, so as to solve the technical problem of how to increase the exit speed of the tube under the condition that the air source pressure and the launch tube length remain unchanged.

[0005] The technical solution to achieve the purpose of the present invention is:

[0006] A pneumatic launch device for a loitering missile comprises a launch tube, a bullet holder arranged in the launch tube, and a gas pipeline connected to the bottom of the launch tube;

[0007] The bottom of the launch tube adopts a double-layer tube structure, including an outer tube and an inner tube, a cavity is formed in the outer tube and the inner tube, and a self-locking mechanism is provided in the cavity to self-lock the bullet support and increase the launch pressure at the bottom of the launch tube;

[0008] The self-locking mechanism comprises a self-locking cylinder, a fixed cylinder, a first base, a second base and a self-locking spring;

[0009] The first base and the second base are both slidably matched with the outer cylinder and the gas pipeline to form a sealing structure; a plurality of self-locking springs are arranged between the first base and the second base to provide a self-locking force for the self-locking cylinder and a reset force for the self-locking mechanism;

[0010] The first base is provided with a plurality of fixed cylinders, and the fixed cylinders are slidably matched with the self-locking cylinders;

[0011] The outer circumferential surface of the bottom of the inner tube of the launch tube is provided with a plurality of through holes for installing the self-locking cylinder of the self-locking mechanism;

[0012] The self-locking cylindrical head portion extends out from the through hole of the launch tube and engages with the circular groove at the bottom of the cartridge case to achieve self-locking of the cartridge case;

[0013] The outer cylinder is rotatably connected with a rotatable base, which is threadedly connected to the second base and can drive the second base to move axially to adjust the self-locking force of the self-locking spring.

[0014] Compared with the prior art, the present invention has the following significant advantages:

[0015] (1) A self-locking mechanism is used at the bottom of the launch tube, which increases the speed at which the projectile exits the tube when it is launched while keeping the gas source pressure and the launch tube length unchanged.

[0016] (2) The rotatable base design is adopted to realize the adjustment function of the self-locking force of the self-locking mechanism and the adjustment function of the ejection speed of the projectile. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 This is a schematic diagram of the overall launch device.

[0018] Figure 2 Schematic diagram of the launch tube.

[0019] Figure 3 Schematic diagram of the self-locking mechanism.

[0020] Figure 4 It is a schematic diagram of the self-locking cylinder of the self-locking mechanism.

[0021] Figure 5 It is a schematic diagram of a self-locking mechanism fixing a cylinder.

[0022] In the figure: 1, launch tube; 2, bullet support; 3, self-locking mechanism; 4, rotatable base; 5, outer tube; 6, inner tube; 7, flange; 8, through hole; 9, gas pipeline; 10, self-locking cylinder; 11, fixed cylinder; 12, first base; 13, second base; 14, self-locking spring DETAILED DESCRIPTION

[0023] The present invention is further described below in conjunction with the accompanying drawings and specific embodiments.

[0024] Combination Figure 1 , Figure 2 , a pneumatic launch device suitable for a cruise missile in this embodiment includes a launch tube 1, a bullet support 2, a self-locking mechanism 3, and a rotatable base 4;

[0025] The bottom of the launch tube 1 adopts a double-layer tube design, including an outer tube 5 and an inner tube 6; the inner diameter of the outer tube 5 is larger than the outer diameter of the inner tube 6, and the outer tube 5 and the inner tube 6 of the launch tube 1 are fixed by welding.

[0026] The sabot 2 is located at the bottom of the launch tube 1, and its outer surface is in contact with the inner surface of the launch tube 1. The cruise missile is located above the sabot 2. The sabot 2 and the missile body are coaxial with the launch tube 1. The outer diameter of the sabot 2 should be consistent with the inner diameter of the inner tube 6. During the movement of the sabot 2, they should fit tightly to play a sealing role. The bottom radius of the sabot 2 is smaller than the radius of the launch tube 1, and the outer circle of the bottom is provided with a circular groove 2-1. When self-locking, the round head part of the self-locking cylinder 10 of the self-locking mechanism 3 is embedded in the circular groove 2-1, and the sabot 2 and the missile body are restricted by the self-locking cylinder 10. During launch, high-pressure gas is transmitted to the bottom of the launch tube 1, and the circular groove 2-1 at the bottom of the sabot 2 applies an upward force to the round head part of the self-locking cylinder 10. When the upward force is greater than the self-locking force, the self-locking cylinder 10 is squeezed out of the launch tube 1, and then the missile body moves upward along the launch tube 1. The sabot 2 is ejected from the tube together with the projectile body after firing, and there is no need to provide a buffer structure on the launch tube 1 to prevent the sabot 2 from exiting the tube, thereby reducing the impact of the sabot 2 on the launch tube 1 during firing;

[0027] The outer tube 5, inner tube 6 and self-locking mechanism 3 of the launch tube 1 form a sealing structure. A hollow cavity is formed between the inner tube 6 and the outer tube 5 of the launch tube 1, and the self-locking mechanism 3 is located in the cavity. The double-layer tube structural design at the bottom of the launch tube 1 reduces the heat transfer during launch and improves the energy utilization efficiency. The outer tube 5 of the launch tube 1 has a flange 7 on the outer ring, which cooperates with the rotatable base 4 and plays an axial positioning role. A plurality of through holes 8 are provided on the outer cylindrical surface of the bottom of the inner tube 6 of the launch tube 1, and the through holes 8 are used to install the self-locking cylinder 10 of the self-locking mechanism 3.

[0028] The launch tube 1 structure is made of composite materials, and the reinforcement of the composite tube is glass fiber and high silica fiber. At the same time, the corresponding material can be selected according to the requirements of different performances to ensure that the structure of the composite tube can reduce the weight of the entire tube. The bottom of the inner tube 6 of the launch tube 1 is welded to the gas pipeline 9.

[0029] Combination Figure 3 , Figure 4 , Figure 5 , the self-locking mechanism 3 includes a self-locking cylinder 10, a fixed cylinder 11, a first base 12, a second base 13 and a self-locking spring 14;

[0030] The self-locking cylinder 10 of the self-locking mechanism 3 is located in the through hole 8 on the side of the bottom of the launch tube 1. The round head of the self-locking cylinder 10 extends out of the tube and cooperates with the circular groove 2-1 at the bottom of the cartridge holder 2. The bottom of the self-locking cylinder 10 has two slide grooves, including an intersecting inclined slide groove 10-1 and a vertical slide groove 10-2; the inclined slide groove 10-1 is slidably matched with the fixed cylinder 11, and the vertical slide groove 10-2 acts as a limiter for the fixed cylinder 11 to prevent the self-locking cylinder 10 from extending too long from the round head part. The self-locking cylinder 10 plays the role of self-locking the cartridge holder 2 and the projectile during launch, so that the cartridge holder 2 and the projectile are launched from the launch tube 1 only when the low-pressure chamber at the bottom of the launch tube 1 obtains a sufficiently large pressure. When the gas source pressure remains unchanged, the projectile obtains a greater acceleration, energy loss is reduced, and launch efficiency is improved;

[0031] When self-locking, the fixed cylinder 11 of the self-locking mechanism 3 is embedded in the inclined slide groove 10-1 of the self-locking cylinder 10 and slides together. The bottom of the fixed cylinder 11 is connected to the first base 12 of the self-locking mechanism 3 through a thread. When the self-locking cylinder 10 is extruded into the tube, it drives the fixed cylinder 11 to move downward. The fixed cylinder 11 moves downward along the axis of the launch tube 1 together with the first base 12 through a threaded connection.

[0032] There are six pairs of self-locking cylinders 10 and fixed cylinders 11, which are evenly arranged in the hollow cavities of the inner tube 6 and the outer tube 5 of the launch tube 1. The fixed cylinders 11 are also threadedly connected to the first base 12.

[0033] The first base 12 of the self-locking mechanism 3 is located in the hollow cavity between the inner tube 6 and the outer tube 5 at the bottom of the launch tube 1. The outer diameter of the first base 12 should be consistent with the inner diameter of the outer tube 5 of the launch tube 1, and it should be slidably matched with the launch tube 1. The first base 12 is hollowed out in the middle to allow the gas pipeline to pass through. There are threaded holes on the front side connected to the fixed cylinder 11, and there are self-locking springs 14 evenly distributed on the back side that are fixedly connected to it. When working, the force of the self-locking spring 14 is transmitted to the cartridge case 2 through the self-locking mechanism 3. When launching, the force applied to the cartridge case 2 is greater than the self-locking force generated by the self-locking spring 14, and the self-locking mechanism 3 moves downward. After launching, the spring resets the self-locking mechanism 3;

[0034] The second base 13 of the self-locking mechanism 3 is located in the hollow cavity between the inner tube 6 and the outer tube 5 at the bottom of the launch tube 1. The outer diameter of the second base 13 should be consistent with the inner diameter of the outer tube 5 of the launch tube 1, and it should be slidably matched with the outer tube 5. The inner and outer rings of the second base 13 are covered with sealing rings. The outer ring is sealed with the outer tube 5 of the launch tube 1, and the inner ring is sealed with the gas pipeline. The outer tube 5 and the inner tube 6 of the launch tube 1 form a sealing structure with the second base 13 of the self-locking mechanism 3. The upper part of the second base 13 is fixedly connected to the spring, and the lower cylindrical structure has a T-shaped thread, and the cylindrical part is threadedly matched with the rotatable base 4;

[0035] The two ends of the self-locking spring 14 of the self-locking mechanism 3 are respectively fixed on the first base 12 and the second base 13 of the self-locking mechanism 3. When self-locking, the self-locking spring 14 provides a self-locking force, and the launching force generated during launching is transmitted to the first base 12. When the launching force is greater than the force generated by the self-locking spring 14, the first base 12 compresses the self-locking spring 14 to move downward. When the second base 13 moves upward, the compression amount of the self-locking spring 14 increases, and the self-locking force increases accordingly.

[0036] The rotatable base 4 is installed on the outer cylinder 5 at the bottom of the launch tube 1 and rotates with the outer cylinder 5. The flange 7 of the outer cylinder 5 of the launch tube 1 is embedded in the groove of the rotatable base 4. The rotatable base 4 has a cylindrical structure inside, and a T-shaped thread is provided on the inner side of the cylinder. The cylindrical part is spirally matched with the second base 13 of the self-locking mechanism 3. When the rotatable base 4 rotates right, the second base 13 of the self-locking mechanism 3 is driven to move downward through the threaded connection, the spring contraction amount decreases, the force applied by the spring to the self-locking mechanism 3 decreases, and at the same time, the self-locking force applied by the self-locking mechanism 3 to the sabot 2 decreases, and the initial launch force required for the sabot 2 and the projectile body to be launched also decreases, the initial acceleration obtained decreases, and the final launch speed when it is out of the tube is also reduced; the same is true when the rotatable base 4 rotates left, and the launch speed of the cruise missile when it is finally out of the tube increases.

Claims

1. A pneumatic launch device for a loitering missile, comprising a launch tube, a sabot disposed in the launch tube, and a gas pipeline connected to the bottom of the launch tube; characterized in that: The bottom of the launch tube adopts a double-layer tube structure, including an outer tube and an inner tube, a cavity is formed in the outer tube and the inner tube, and a self-locking mechanism is provided in the cavity to self-lock the bullet support and increase the launch pressure at the bottom of the launch tube; The self-locking mechanism comprises a self-locking cylinder, a fixed cylinder, a first base, a second base and a self-locking spring; The first base and the second base are both slidably matched with the outer cylinder and the gas pipeline to form a sealing structure; a plurality of self-locking springs are arranged between the first base and the second base to provide a self-locking force for the self-locking cylinder and a reset force for the self-locking mechanism; The first base is provided with a plurality of fixed cylinders, and the fixed cylinders are slidably matched with the self-locking cylinders; The outer circumferential surface of the bottom of the inner tube of the launch tube is provided with a plurality of through holes for installing the self-locking cylinder of the self-locking mechanism; The self-locking cylindrical head portion extends out from the through hole of the launch tube and engages with the circular groove at the bottom of the cartridge case to achieve self-locking of the cartridge case; The outer cylinder is rotatably connected with a rotatable base, which is threadedly connected to the second base and can drive the second base to move axially to adjust the self-locking force of the self-locking spring.

2. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: The bottom of the self-locking cylinder is provided with two slide grooves, including an intersecting inclined slide groove and a vertical slide groove; the inclined slide groove is slidably matched with the fixed cylinder, and the vertical slide groove plays a limiting role on the fixed cylinder.

3. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: The outer ring of the bottom of the bullet support is provided with a circular groove, and the self-locking cylindrical round head part cooperates with the circular groove of the bottom of the bullet support.

4. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: The outer ring of the outer cylinder of the launch tube has a flange, which cooperates with the rotating base and plays a role in axial positioning; the rotatable base has a cylindrical structure inside, the inner side of the cylinder has a thread, and the cylindrical part is spirally matched with the second base.

5. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: The inner and outer rings of the second base are sleeved with sealing rings, the outer ring is sealed with the outer tube 5 of the launch tube 1, and the inner ring is sealed with the gas pipeline.

6. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: There are six pairs of self-locking cylinders and fixed cylinders in total, which are evenly arranged in the hollow cavities of the inner tube and the outer tube of the launch tube.

7. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: The fixed cylinder is threadedly connected to the first base.

8. The pneumatic launch device for loitering missiles according to claim 1, characterized in that: The transmitting tube is made of composite fiber material.

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