Aerodynamic launching device for a cruise missile

Abstract

The application discloses a kind of aerodynamic launching device for cruise missile, for providing initial speed when cruise missile takes off;The aerodynamic launching device includes launch tube, shell support, rotatable base, self-locking mechanism;Wherein, the rotatable base and self-locking mechanism are fixed on the launch tube;The shell support is placed in the tube from above the launch tube, and its outer surface is in contact with the inner surface of the tube;The self-locking mechanism is placed in the bottom of the tube.By setting adjustable self-locking mechanism, can make in the same air supply gas amount, launch efficiency increases, launch speed improves, reduces energy loss, etc.

Description

Technical Field

[0001] The present invention belongs to the technical field of catapult-launched unmanned aerial vehicles (UAVs) and loitering missiles, and in particular to a pneumatic launching device for loitering missiles. Background Art

[0002] Loitering missiles are a product of the integration of drone and missile technologies. Their launch methods have evolved from a single airborne drop to a variety of other methods. Based on their launch propulsion systems, they can be categorized as hot launch and cold launch. Compressed air cold launch is the most widely used.

[0003] Existing individual cruise missile launchers typically have a diameter similar to that of the cruise missile. A sabot is placed between the cruise missile and the high-pressure gas. The high-pressure gas acts on the sabot, which in turn propels the cruise missile out of the tube and accelerates it. Compressed air cold launch systems offer advantages such as no need for thermal protection, minimal infrared exposure, good environmental adaptability, and high equipment reuse. However, existing compressed air pneumatic launchers have low energy efficiency, resulting in significant energy loss, and are difficult to control internal ballistic parameters during launch. Summary of the Invention

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

[0005] The technical solutions for achieving the purpose of the present invention are:

[0006] A pneumatic launch device for a loitering munition comprises a launch tube, a sabot disposed in the launch tube, and an air 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 inside the outer tube and the inner tube. A self-locking mechanism is provided in the cavity to self-lock the cartridge case and increase the launch pressure at the bottom of the launch tube.

[0008] The self-locking mechanism includes 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 provided 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, which are slidably matched with the self-locking cylinders;

[0011] The outer circumferential surface of the bottom of the inner cylinder 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 from the launch tube through hole and engages with the circular groove at the bottom of the sabot to achieve self-locking of the sabot;

[0013] The outer cylinder is rotatably connected to 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 of the projectile out of 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 the self-locking mechanism fixing the cylinder.

[0022] Figure: 1, launch tube; 2, cartridge holder; 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 will be further described below with reference to the accompanying drawings and specific embodiments.

[0024] Combine Figure 1 , Figure 2 , a pneumatic launch device suitable for a loitering missile in this embodiment includes a launch tube 1, a sabot 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, with its outer surface 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 together to provide a seal. The sabot 2 has a smaller bottom radius than the launch tube 1. The outer ring of the bottom has a circular groove 2-1. When self-locking, the rounded end of the self-locking cylinder 10 of the self-locking mechanism 3 fits into the circular groove 2-1, and the sabot 2 and the missile body are restrained by the self-locking cylinder 10. During launch, high-pressure gas is transmitted to the bottom of the launch tube 1. The circular groove 2-1 at the bottom of the sabot 2 applies an upward force to the rounded end of the self-locking cylinder 10. When the upward force exceeds the self-locking force, the self-locking cylinder 10 is squeezed out of the launch tube 1, and then moves upward along the launch tube 1 with the missile body. 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 and inner tube 6 of the launch tube 1 form a sealed structure with the self-locking mechanism 3. A hollow cavity is formed between the inner tube 6 and outer tube 5 of the launch tube 1, and the self-locking mechanism 3 is located within this cavity. The double-layered tube structure at the bottom of the launch tube 1 reduces heat transfer during launch, improving energy efficiency. The outer tube 5 of the launch tube 1 has a flange 7 on its outer circumference, which cooperates with the rotatable base 4 and provides axial positioning. The outer circumferential surface of the bottom of the inner tube 6 of the launch tube 1 is provided with multiple through-holes 8 for mounting the self-locking cylinders 10 of the self-locking mechanism 3.

[0028] The launch tube 1 is constructed of composite material, with glass fiber and high-silica fiber being used as reinforcement. The appropriate material can be selected based on performance requirements to ensure the composite tube structure reduces overall weight. The bottom of the inner tube 6 of the launch tube 1 is welded to the gas pipeline 9.

[0029] Combine 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 from 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 slides with the fixed cylinder 11, and the vertical slide groove 10-2 limits the fixed cylinder 11, preventing the self-locking cylinder 10 from extending too far from the round head. 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 reaches a sufficiently high pressure. When the gas source pressure remains unchanged, the projectile obtains a greater acceleration, energy loss is reduced, and launch efficiency is improved.

[0031] During 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 cavity 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 slides with the launch tube 1. The middle of the first base 12 is hollowed out to allow the gas pipeline to pass through. There are threaded holes on the front side that are connected to the fixed cylinder 11, and there are self-locking springs 14 on the back side that are also evenly distributed and 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 slides 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 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. The cylindrical part is threadedly engaged with the rotatable base 4;

[0035] The ends of the self-locking spring 14 of the self-locking mechanism 3 are respectively fixed to the first base 12 and the second base 13 of the self-locking mechanism 3. During self-locking, the self-locking spring 14 provides a self-locking force. During firing, the launch force generated is transmitted to the first base 12. When the launch force exceeds the force generated by the self-locking spring 14, the first base 12 compresses the self-locking spring 14 downward. As the second base 13 moves upward, the self-locking spring 14 is further compressed, and the self-locking force increases accordingly.

[0036] The rotatable base 4 is mounted 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 inside of the cylinder. The cylindrical part is screwed together with the second base 13 of the self-locking mechanism 3. When the rotatable base 4 rotates clockwise, the second base 13 of the self-locking mechanism 3 is driven downward by 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. The initial launch force required for the sabot 2 and the projectile to be launched also decreases, the initial acceleration obtained decreases, and the final launch speed when leaving the tube is also reduced. The same is true when the rotatable base 4 rotates counterclockwise. The final launch speed of the cruise missile when leaving the tube increases.

Claims

1. A pneumatic launch device for a loitering munition, comprising a launch tube, a sabot disposed within the launch tube, and an air 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 inside the outer tube and the inner tube. A self-locking mechanism is provided in the cavity to self-lock the cartridge case and increase the launch pressure at the bottom of the launch tube. The self-locking mechanism includes 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 provided 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, which are slidably matched with the self-locking cylinders; The outer circumferential surface of the bottom of the inner cylinder 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 from the launch tube through hole and engages with the circular groove at the bottom of the sabot to achieve self-locking of the sabot; The outer cylinder is rotatably connected to 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; 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 slides with the fixed cylinder, and the vertical slide groove plays a limiting role on the fixed cylinder.

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

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

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

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

6. The pneumatic launch device for loitering munitions according to claim 1, characterized in that: The fixing cylinder is threadedly connected to the first base.

7. The pneumatic launch device for loitering munitions according to claim 1, characterized in that: The launching tube is made of composite fiber material.

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