Integrated pulse projectile recoilless launching device based on supercritical carbon dioxide

Abstract

The application provides an integrated pulse bullet recoilless launching device based on supercritical carbon dioxide, which comprises a firing mechanism, a pulse bullet and a recoil reduction mechanism; the firing mechanism comprises a barrel and a trigger, and the trigger is used for outputting a firing current to the pulse bullet after being pressed; the pulse bullet is installed in the barrel, and a phase change chamber is arranged in the pulse bullet, liquid carbon dioxide and heating powder are encapsulated in the phase change chamber; the pulse bullet is provided with a contact point, which is used for igniting the heating powder after receiving the firing current, so that the liquid carbon dioxide is converted into a supercritical state and is sprayed backward from the tail of the phase change chamber to generate a forward reaction thrust, and the pulse bullet is launched from the barrel; and the recoil reduction mechanism is arranged at the tail end of the barrel. The power output of the application depends on the carbon dioxide phase change process, and no high-temperature tail flame is generated in the whole process, so that the secondary safety hidden danger caused by high temperature of the traditional launching device is fundamentally eliminated, and the application is especially suitable for scenes with extremely high safety requirements, such as fire rescue, flammable and explosive environment operation and the like.

Description

Technical Field

[0001] This invention relates to the field of fire extinguishing device technology, and in particular to an integrated pulse projectile recoilless launching device based on supercritical carbon dioxide. Background Technology

[0002] Pulse extinguishing devices can launch pulse projectiles. They are devices that use instantaneous high-pressure gas to drive the extinguishing medium (water, dry powder, foam, etc.) to be sprayed in a high-speed pulse form.

[0003] In current engineering applications, pulse projectile launches mostly rely on propellants such as gunpowder for power. This not only faces problems such as high risks in the transportation and storage of propellants and cumbersome approval processes, but also suffers from technical defects such as large recoil during launch leading to poor device stability, low landing accuracy, and high-temperature exhaust flames that can easily cause secondary safety hazards. Summary of the Invention

[0004] This invention aims to at least partially solve one of the technical problems in related technologies. Therefore, the purpose of this invention is to propose an integrated pulse projectile recoilless launcher based on supercritical carbon dioxide, addressing the high risks associated with the transportation and storage of energetic agents, and improving operational safety and reliability.

[0005] To achieve the above objectives, this invention proposes an integrated pulse bullet recoilless launching device based on supercritical carbon dioxide, comprising a firing mechanism, a pulse bullet, and a recoil reduction mechanism. The firing mechanism includes a barrel and a trigger, the trigger being located on the outside of the barrel and used to output a firing current to the pulse bullet when pressed. The pulse grenade is installed inside the barrel, and the pulse grenade has a phase change chamber inside, which contains liquid carbon dioxide and a heating propellant. The pulse grenade has a contact that is electrically connected to the trigger, which is used to ignite the heating propellant after receiving the firing current, causing the liquid carbon dioxide to be converted to a supercritical state and ejected from the tail of the phase change chamber, generating a forward reaction thrust that launches the pulse grenade out of the barrel. The recoil reduction mechanism is located at the tail end of the barrel and is used to reduce the recoil force generated during launch.

[0006] According to one embodiment of the present invention, the firing mechanism further includes a trigger frame, a gun body, a power switch, a battery, a wire, and an adapter; the gun body is fixedly connected to the lower part of the barrel; the trigger is mounted inside the gun body and is hinged to the trigger frame; the battery, the power switch, the wire, the adapter, and the contact of the pulse grenades are sequentially electrically connected to form a firing circuit; the adapter is located at the tail end of the barrel and is used to connect to the contact of the pulse grenades after the pulse grenades are loaded to achieve electrical conduction; the power switch is used to connect the circuit between the battery and the trigger when pressed.

[0007] According to one embodiment of the present invention, the firing mechanism further includes an outer cylinder and a sight; the outer cylinder is sleeved on the outer wall of the barrel and fixedly connected to the gun body, and the sight is mounted on the side wall of the outer cylinder.

[0008] According to one embodiment of the present invention, the pulse projectile further includes a pressure-controlled diaphragm and a Laval nozzle; the pressure-controlled diaphragm is disposed at the tail outlet of the phase change chamber, and is used to maintain a seal before the internal pressure of the phase change chamber reaches a preset value and to rupture and release the gas flow after the preset value is exceeded; the Laval nozzle is located downstream of the pressure-controlled diaphragm and is used to improve the efficiency of the reaction thrust.

[0009] According to one embodiment of the present invention, the pulse bullet further includes an electrically excited plug and a conductive post; the electrically excited plug is sealed and installed at the front end of the phase change chamber; the conductive post passes through the electrically excited plug axially, and the rear end of the conductive post is electrically connected to the heating agent; the front end of the conductive post is electrically connected to the contact of the pulse bullet.

[0010] According to one embodiment of the present invention, the recoil reduction mechanism includes a pressure relief nozzle, a baffle, and a latch; the pressure relief nozzle is fixedly connected to the tail end of the body tube and communicates with the inner cavity of the body tube; the inlet end of the pressure relief nozzle is provided with a stepped surface, and the baffle is installed on the stepped surface for shearing and rupturing when the pressure in the body tube reaches a preset value, so that pressurized gas is ejected rearward through the pressure relief nozzle; the latch is used to detachably lock the pressure relief nozzle to the body tube.

[0011] Compared with the prior art, the beneficial effects of the present invention are as follows: 1. This invention uses supercritical carbon dioxide as the core power source to replace traditional gunpowder and other energetic agents, completely avoiding the high risks and cumbersome approval processes associated with the transportation and storage of energetic agents. Furthermore, carbon dioxide is widely available and inexpensive, significantly reducing the cost of using and maintaining the device.

[0012] 2. This invention effectively reduces recoil during launch by providing dual protection through a recoil reduction mechanism and stable supercritical carbon dioxide power output, avoiding structural damage caused by severe vibration, significantly improving barrel stability and pulse bullet impact accuracy, and making its operational reliability significantly superior to traditional launch devices.

[0013] 3. The power output of this invention relies on the carbon dioxide phase change process, and no high-temperature exhaust flame is generated throughout the process. This fundamentally eliminates the secondary safety hazards caused by high temperatures in traditional launching devices. It is especially suitable for scenarios with extremely high safety requirements, such as fire rescue and operations in flammable and explosive environments, and has stronger environmental adaptability.

[0014] 4. This invention integrates liquid carbon dioxide, heating propellant, and pulse grenade body into a single pulse grenade, achieving a structural design that combines modularity and integration. The core components are easy to disassemble and assemble, and the pulse grenade type, pressure control diaphragm, baffle, and other components can be quickly changed according to operational needs, achieving "one machine with multiple functions". At the same time, it simplifies the maintenance process and provides strong support for continuous operation.

[0015] Additional aspects and advantages of the invention will be set forth in part in the description which follows, and in part will be obvious from the description, or may be learned by practice of the invention. Attached Figure Description

[0016] Various other advantages and benefits will become apparent to those skilled in the art upon reading the following detailed description of preferred embodiments. The accompanying drawings are for illustrative purposes only and are not intended to limit the invention. Furthermore, the same reference numerals denote the same parts throughout the drawings. Wherein: Figure 1 This is a schematic diagram of an integrated pulse missile recoilless launching device based on supercritical carbon dioxide in one embodiment of the present invention.

[0017] Figure 2 yes Figure 1 A cross-sectional view of the recoilless firing mechanism.

[0018] Figure 3 This is a schematic diagram of the firing mechanism in one embodiment of the present invention.

[0019] Figure 4 yes Figure 3 A cross-sectional view of the firing mechanism.

[0020] Figure 5 This is a schematic diagram of the recoil reduction mechanism.

[0021] Figure 6 yes Figure 5 A cross-sectional view of the recoil reduction mechanism.

[0022] Figure 7 This is a top view of the pressure relief nozzle after it has been opened.

[0023] Explanation of reference numerals in the attached figures: 1-Relief nozzle, 2-Baffle, 3-Latch, 4-Pressure control diaphragm, 5-Phase change chamber, 6-Body tube, 7-Heating propellant, 8-Electrically activated plug, 9-Outer cylinder, 10-Conductive column, 11-Sight scope, 12-Trigger, 13-Power switch, 14-Battery, 15-Wire, 16-Laval nozzle, 17-Adapter. Detailed Implementation

[0024] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and are only used to explain the invention, and should not be construed as limiting the invention. Rather, embodiments of the invention include all variations, modifications, and equivalents falling within the spirit and scope of the appended claims.

[0025] The following is for reference. Figures 1 to 7 This describes an integrated pulse projectile recoilless launching device based on supercritical carbon dioxide according to an embodiment of the present invention.

[0026] Combination Figure 1 and Figure 2 As shown, the integrated pulse grenade recoilless launching device based on supercritical carbon dioxide includes a firing mechanism, a pulse grenade, and a recoil reduction mechanism. Pulse grenades can be used in fire rescue environments. They are a new type of fire-fighting equipment that utilizes the instantaneous expansion of high-pressure gas to generate a high-speed jet, remotely delivering extinguishing media (such as water mist, dry powder, inert gas, etc.) to the fire source in pulse form.

[0027] The firing mechanism includes a barrel 6 and a trigger 12. The trigger 12 is located on the outside of the barrel 6 and is used to output a firing current to the pulse projectile when pressed. The pulse projectile is installed inside the barrel 6 and contains a phase change chamber 5. The phase change chamber 5 encapsulates liquid carbon dioxide and a heating propellant 7. The pulse projectile has contacts electrically connected to the trigger 12, which ignite the heating propellant 7 upon receiving the firing current. This causes the liquid carbon dioxide to convert to a supercritical state and be ejected rearward from the tail of the phase change chamber 5, generating a forward reaction thrust that launches the pulse projectile from the barrel 6. A recoil reduction mechanism is located at the tail end of the barrel 6 to reduce the recoil generated during firing.

[0028] In this embodiment, the pulse grenade integrates the phase change chamber, heating charge 7, and contacts into a single integrated structure, avoiding leakage and contamination caused by on-site loading. During use, the operator simply inserts the pulse grenade into the barrel 6 and completes the electrical connection before firing, resulting in a short response time.

[0029] Combination Figure 3 and Figure 4 As shown, in some optional embodiments of the present invention, the firing mechanism further includes a trigger frame, a receiver, a power switch 13, a battery 14, a wire 15, and an adapter 17. The receiver is fixedly connected to the lower part of the barrel 6. The receiver can integrate multiple grips and shoulder supports to achieve stable firing. The trigger frame is located inside the receiver, and the trigger 12 is hinged to the trigger frame. The battery 14, power switch 13, wire 15, adapter 17, and the contact of the pulse grenades are sequentially electrically connected to form the firing circuit. The adapter 17 is located at the rear end of the barrel 6 and is used to connect to the contact of the pulse grenades after they are loaded to achieve electrical conduction. The power switch 13 can be a push-button switch, used to connect the circuit between the battery 14 and the trigger when pressed. The heating powder 7 can only be ignited when the power switch 13 and the trigger 12 are pressed simultaneously.

[0030] In addition, the firing mechanism includes an outer barrel 9 and a sight 11. The outer barrel 9 is fitted onto the outer wall of the barrel 6 and fixedly connected to the gun body. The sight 11 is mounted on the side wall of the outer barrel 9 to assist in aiming at the target and improve firing accuracy. The outer barrel 9 can be made of resin material, which is lightweight and heat-insulating.

[0031] In some alternative embodiments of the present invention, combined with Figure 2 and Figure 4 As shown, the pulse projectile also includes a pressure-controlled diaphragm 4 and a Laval nozzle 16. The pressure-controlled diaphragm 4 is located at the tail outlet of the phase change chamber 5 and is used to maintain a seal before the internal pressure of the phase change chamber 5 reaches a preset value and to rupture and release the gas flow after the preset value is exceeded. The Laval nozzle 16 is located downstream of the pressure-controlled diaphragm 4 and is used to improve the efficiency of the reaction thrust.

[0032] The launching device of this invention can achieve precise matching of launching power by flexibly adjusting four parameters: carbon dioxide filling amount, heating propellant dosage, and pressure control diaphragm, thereby meeting the launching requirements of pulse projectiles in different scenarios.

[0033] like Figure 4 As shown, in some embodiments, the pulse bomb further includes an electrically activated plug 8 and a conductive post 10. The electrically activated plug 8 is sealed and installed at the front end of the phase change chamber 5. The conductive post 10 extends axially through the electrically activated plug 8, and its rear end is electrically connected to the heating agent 7. The front end of the conductive post 10 protrudes outside the electrically activated plug 8 and is electrically connected to the contacts of the pulse bomb via a wire.

[0034] Combination Figure 1 , Figure 5 , Figure 6 and Figure 7As shown, in some embodiments, the recoil reduction mechanism includes a pressure relief nozzle 1, a baffle 2, and a latch 3. The pressure relief nozzle 1 is fixedly connected to the tail end of the body tube 6 and communicates with the inner cavity of the body tube 6. The inlet end of the pressure relief nozzle 1 has a stepped surface, and the baffle 2 is installed on the stepped surface to shear and rupture when the pressure inside the body tube 6 reaches a preset value, allowing pressurized gas to be ejected rearward through the pressure relief nozzle 1. The latch 3 is used to detachably lock the pressure relief nozzle 1 to the body tube 6. The latch 3 is pivotally connected to the tail end of the body tube 6. The latch 3 includes a hinge structure. Specifically, the latch 3 includes a hinge structure, one side of which is fixed to the outer wall of the tail end of the body tube 6, and the other side is connected to the front end of the pressure relief nozzle 1, so that the pressure relief nozzle 1 can rotate relative to the body tube 6 around the hinge axis to open the pressure relief nozzle to a maximum of 180 degrees, facilitating the replacement of the baffle 2. After replacing the baffle 2, reset the pressure relief nozzle 1 to the coaxial position with the barrel 6, and re-lock the latch 3 to restore the firing function.

[0035] The operation of the propulsion device according to a specific embodiment of the present invention is as follows: When the power switch 13 is pressed and the trigger 12 is pressed simultaneously, the current passes through the conductive column 10 to ignite the heating propellant 7, and then the temperature in the phase change chamber 5 rises rapidly; when the critical phase change condition is reached, the carbon dioxide in the phase change chamber 5 rapidly changes to a supercritical carbon dioxide state, and the pressure rises rapidly in sync. When the pressure in the phase change chamber 5 reaches the preset pressure of the pressure control diaphragm 4, the pressure control diaphragm 4 undergoes shear rupture; the high-pressure gas completes expansion acceleration and energy conversion inside the barrel 6 through the Laval nozzle 16 at the tail of the phase change chamber 5, and the high-speed jet ejected from the Laval nozzle 16 forms an axial thrust, pushing the pulse projectile body to accelerate along the axis of the barrel 6 until the pulse projectile body exits the barrel and obtains a predetermined initial velocity. During this process, the pressure in the sealed space between the Laval nozzle 16 and the baffle 2 continues to rise due to the continuous accumulation of gas; when the pressure reaches the preset pressure of the baffle 2, the baffle 2 undergoes shear rupture, at which time the high-pressure gas in the barrel 6 is rapidly released through the pressure relief nozzle 1, greatly reducing the recoil generated during the launch process. After the entire launch process is completed, the baffle 2 can be replaced by opening latch 3 in preparation for the next launch.

[0036] It should be noted that in the description of this invention, the terms "first," "second," etc., are used for descriptive purposes only and should not be construed as indicating or implying relative importance. Furthermore, in the description of this invention, unless otherwise stated, "a plurality of" means two or more.

[0037] In the description of this specification, references to terms such as "one embodiment," "some embodiments," "example," "specific example," or "some examples," etc., indicate that a specific feature, structure, material, or characteristic described in connection with that embodiment or example is included in at least one embodiment or example of the invention. In this specification, the illustrative expressions of the above terms do not necessarily refer to the same embodiment or example. Furthermore, the specific features, structures, materials, or characteristics described may be combined in any suitable manner in one or more embodiments or examples.

[0038] Although embodiments of the present invention have been shown and described above, it is understood that the above embodiments are exemplary and should not be construed as limiting the present invention. Those skilled in the art can make changes, modifications, substitutions and variations to the above embodiments within the scope of the present invention.

Claims

1. An integrated pulse projectile recoilless launching device based on supercritical carbon dioxide, characterized in that, Includes the firing mechanism, pulse blast, and recoil reduction mechanism; The firing mechanism includes a barrel (6) and a trigger (12), the trigger (12) being located on the outside of the barrel (6) and used to output firing current to the pulse bullet when pressed; The pulse projectile is installed inside the barrel (6). The pulse projectile is provided with a phase change chamber (5), which contains liquid carbon dioxide and a heating agent (7). The pulse projectile is provided with a contact that is electrically connected to the trigger (12), which is used to ignite the heating agent (7) after receiving the firing current, so that the liquid carbon dioxide is converted into a supercritical state and ejected from the tail of the phase change chamber (5) to generate a forward reaction thrust, which launches the pulse projectile out of the barrel (6). The recoil reduction mechanism is located at the tail end of the barrel (6) and is used to reduce the recoil force generated during launch.

2. The integrated pulse projectile recoilless launching device based on supercritical carbon dioxide according to claim 1, characterized in that, The firing mechanism also includes a trigger frame, a gun body, a power switch (13), a battery (14), a wire (15), and an adapter (17); the gun body is fixedly connected to the lower part of the barrel (6); the trigger is mounted inside the gun body and is hinged to the trigger frame; the battery (14), the power switch (13), the wire (15), the adapter (17), and the contact of the pulse bullet are sequentially electrically connected to form a firing circuit; the adapter (17) is located at the tail end of the barrel (6) and is used to connect to the contact of the pulse bullet after the pulse bullet is loaded to achieve electrical conduction; the power switch (13) is used to connect the line between the battery (14) and the trigger when pressed.

3. The integrated pulse projectile recoilless launching device based on supercritical carbon dioxide according to claim 2, characterized in that, The firing mechanism also includes an outer cylinder (9) and a sight (11); the outer cylinder (9) is fitted onto the outer wall of the barrel (6) and fixedly connected to the gun body, and the sight (11) is mounted on the side wall of the outer cylinder (9).

4. The integrated pulse projectile recoilless launching device based on supercritical carbon dioxide according to claim 1, characterized in that, The pulse projectile also includes a pressure-controlled diaphragm (4) and a Laval nozzle (16); the pressure-controlled diaphragm (4) is located at the tail outlet of the phase change chamber (5) and is used to maintain a seal before the internal pressure of the phase change chamber (5) reaches a preset value and to rupture and release the airflow after the preset value is exceeded; the Laval nozzle (16) is located downstream of the pressure-controlled diaphragm (4) and is used to improve the efficiency of the reaction thrust.

5. The integrated pulse projectile recoilless launching device based on supercritical carbon dioxide according to claim 1, characterized in that, The pulse bomb also includes an electrically excited plug (8) and a conductive post (10); the electrically excited plug (8) is sealed and installed at the front end of the phase change chamber (5); the conductive post (10) passes through the electrically excited plug (8) axially, and the rear end of the conductive post (10) is electrically connected to the heating agent (7); the front end of the conductive post (10) is electrically connected to the contact of the pulse bomb.

6. The integrated pulse projectile recoilless launching device based on supercritical carbon dioxide according to claim 1, characterized in that, The recoil reduction mechanism includes a pressure relief nozzle (1), a baffle (2), and a latch (3); the pressure relief nozzle (1) is fixedly connected to the tail end of the body tube (6) and communicates with the inner cavity of the body tube (6); the inlet end of the pressure relief nozzle (1) is provided with a stepped surface, and the baffle (2) is installed on the stepped surface to shear and rupture when the pressure in the body tube (6) reaches a preset value, so that the pressurized gas is ejected backward through the pressure relief nozzle (1); the latch (3) is used to detachably lock the pressure relief nozzle (1) onto the body tube (6).

Images