A drone demolition system

Abstract

A drone demolition system includes a drone body; a mounting mechanism equipped with several first automatic push rods and second automatic push rods; a rocket demolition device including a housing with a lifting ring and a housing cover; a launch tube disposed within the housing; a rocket engine disposed within the launch tube; an explosive zone disposed within the housing, including a head connector and a tail connector, the head connector being connected to the rocket engine; a fuze assembly including a fuze combiner and a fuze, one end of the fuze combiner being connected to the fuze and the other end being connected to the tail connector; a control device disposed within the housing, the control device being connected to the fuze assembly for triggering the fuze action and igniting the explosive zone; and a command and control box disposed outside the housing for receiving external control signals to trigger an ignition signal to ignite the rocket engine and launch; wherein, the rocket demolition device is mounted on the mounting mechanism via the lifting ring and the first automatic push rods, and the second automatic push rods can open the housing cover.

Description

Technical Field

[0001] This application belongs to the field of blasting materials technology, specifically relating to an unmanned aerial vehicle (UAV) blasting system. Background Technology

[0002] In the field of mine clearance equipment, based on their operating principles, they can be divided into mechanical mine clearers and explosive mine clearers. Mechanical mine clearers generally include rolling, striking, and digging types, while explosive mine clearers generally rely on the explosive action of explosives to detonate mines or disable them. In offensive operations, explosive mine clearers are often used to clear anti-personnel minefields or obstacles such as barbed wire in front of or deep into enemy positions to open up infantry passages. Traditionally, explosive mine clearers are carried by engineers who sneak to the vicinity of the minefield, then manually set up the mine clearance equipment and ignite it. This manual explosive mine clearance method is inefficient, risky, time-consuming for engineers to carry, cumbersome to set up, and easily detected by the enemy, leading to mine clearance failure. Summary of the Invention

[0003] This application aims to provide a drone blasting system that is remotely controllable, highly concealed, and easy to operate.

[0004] This application adopts the following technical solution:

[0005] A drone-based demolition system, comprising:

[0006] A drone component, the drone component including a drone body and a wireless remote controller;

[0007] Mounting mechanism, wherein a plurality of first automatic push rods and second automatic push rods are provided on the mounting mechanism;

[0008] A rocket detonator, comprising: a launch box, the launch box including a box body with lifting rings and a box cover; a launch tube, the launch tube disposed within the box body; a rocket engine, the rocket engine disposed within the launch tube; an explosive zone, the explosive zone disposed within the box body, the explosive zone including a head connector and a tail connector, the head connector being connected to the rocket engine; a fuze assembly, the fuze assembly including a fuze combiner and a fuze, one end of the fuze combiner being connected to the fuze, the other end of the fuze combiner being connected to the tail connector; a control device, the control device disposed within the box body, the control device being connected to the fuze assembly for triggering the fuze to activate and ignite the explosive zone; and a command and control box, the command and control box being disposed outside the box body for receiving external control signals to trigger an ignition signal to ignite and launch the rocket engine;

[0009] When the first automatic push rod extends, the rocket detonator rod can be mounted on the first automatic push rod via the lifting ring, i.e., mounted on the mounting mechanism. When the first automatic push rod retracts, the rocket can disengage from the first automatic push rod before detonation, i.e., disengage from the mounting mechanism. When the second automatic push rod extends, it can prevent the box cover from opening. When the second automatic push rod retracts, the box cover can open under the action of gravity.

[0010] Furthermore, the mounting mechanism is a detachable frame structure with an opening at the bottom.

[0011] Furthermore, a first sensor capable of detecting the presence of an object is installed at the bottom opening of the mounting mechanism.

[0012] Furthermore, the control device includes a front control rope and a control umbrella connected to the front control rope, and the front control rope is provided with a rope loop and a fire hook.

[0013] Furthermore, the fuse combiner is provided with a connecting rope, which is threaded into the rope loop;

[0014] The fuse is equipped with a pull rope, which is hooked into the pull hook.

[0015] Furthermore, the command and control box includes:

[0016] The main control board is used to receive external control signals, process external control signals, and issue internal control signals; and

[0017] Battery.

[0018] Furthermore, a second sensor capable of detecting the presence of an object is provided at the box body and the box lid.

[0019] Furthermore, the rocket engine includes a warhead, an electric igniter, a combustion chamber, a propellant grain, and a nozzle mount.

[0020] The beneficial effects of this application are:

[0021] This application enables remote and covert blasting operations using drones carrying explosives, achieving efficient and rapid automatic blasting. After the blasting is completed, the rocket explosives can be automatically dropped, and the drone can return for continued use. Attached Figure Description

[0022] Figure 1 This is a schematic diagram of the overall structure of an embodiment of this application;

[0023] Figure 2 This is a schematic diagram of the mounting mechanism structure in the embodiments of this application.

[0024] Figure 3 This is a side sectional view of the blasting device in an embodiment of this application;

[0025] Figure 4 This is a schematic diagram of the internal structure of the blasting device in an embodiment of this application;

[0026] Figure 5 This is a schematic diagram of the control device structure in an embodiment of this application;

[0027] In the picture:

[0028] 1. Rocket launcher;

[0029] 100 Launch box, 110 Box body, 111 Ground support frame, 112 Lifting ring, 113 Shoulder strap ring, 120 Box cover, 121 Foam board;

[0030] 200 launch tubes;

[0031] 300 rocket engine, 310 warhead, 320 electric igniter, 330 combustion chamber, 340 propellant grain, 350 nozzle mount.

[0032] 400 command and control box;

[0033] 500 explosive belt, 510 towing rope, 520 head connector, 530 tail connector;

[0034] 600 Control device, 610 Front control rope, 611 Rope loop, 612 Fire hook, 620 Control umbrella;

[0035] 700 fuse assembly, 710 fuse combiner, 720 fuse, 730 pull cord, 740 connecting cord;

[0036] 800 drone airframe;

[0037] 900 Mounting mechanism, 910 First automatic push rod, 920 Second automatic push rod, 930 First sensor. Detailed Implementation

[0038] To make the above-mentioned features and advantages of this application more apparent and understandable, the specific embodiments of this application are described in detail below with reference to the accompanying drawings. Many specific details are set forth in the following description to provide a thorough understanding of this application. However, this application can be implemented in many other ways different from those described herein, and those skilled in the art can make similar modifications without departing from the spirit of this application. Therefore, this application is not limited to the specific embodiments disclosed below.

[0039] In the description of this application, it should be understood that the terms "upper", "lower", "front", "back", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this application and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application.

[0040] Reference Figure 1-5 This application provides an unmanned aerial vehicle (UAV) demolition system, comprising:

[0041] A drone component, the drone component including a drone body 800 and a wireless remote controller;

[0042] Mounting mechanism 900, wherein a plurality of first automatic push rods 910 and second automatic push rods 920 are provided on mounting mechanism 900;

[0043] A rocket detonator 1, comprising a launch box 100, the launch box 100 including a housing 110 with several lifting rings 112 and an openable and closable cover 120; a launch tube 200 disposed within the housing 110; a rocket engine 300 disposed within the launch tube 200; an explosive belt 500 disposed within the housing 110, the explosive belt 500 including a head connector 520 and a tail connector 530, the head connector 520 being connected to the rocket engine 300; and a fuze assembly 700, the fuze assembly 700 including a fuze combiner 710 and a fuze 720, wherein one of the fuze combiner 710... One end of the fuse assembly 710 is connected to the fuse 720, and the other end of the fuse assembly 710 is connected to the tail connector 530; a control device 600 is disposed inside the housing 110 and is connected to the fuse assembly 700 to trigger the fuse 720 to ignite the explosive band 500; and a command and control box 400 is disposed outside the housing 110 to receive external control signals to trigger ignition signals to ignite the rocket engine 300 and launch it therein. The rocket detonator 1 is mounted on the mounting mechanism 900 via the lifting ring 112 and the first automatic push rod 910, and the second automatic push rod 920 can open the housing cover 120.

[0044] Specifically, the mounting mechanism 900 is installed on the UAV body 800. The first automatic push rod 910 is retracted, and the rocket detonator 1 is mounted on the first automatic push rod 910 via the lifting ring 112. The first automatic push rod 910 is extended and contacts the corresponding side wall of the mounting mechanism 910 to fix the rocket detonator 1. During blasting, the operator uses the wireless remote control to control the UAV body 800 to carry the rocket detonator 1 to a predetermined position. The second automatic push rod 920 is retracted to open the box cover 120 under gravity. A control signal is sent to the command and control box 400 through the external control system. After receiving the external control signal, the command and control box 400 processes the signal and then sends an internal control signal to ignite the rocket engine 300. The rocket engine 300 ignites and launches, bringing out the explosive zone 500 and the control device 600. Under the action of the control device 600, the fuse 720 is triggered to ignite the explosive zone 500, thereby completing a large-area blasting and obstacle clearing operation. After the blasting is completed, the operator remotely retracts the first automatic push rod 910, causing the lifting ring 112 to detach from the first automatic push rod 910. The launch box 100 then detaches from the mounting mechanism 900 under gravity, thus completing the deployment. The drone body 800, carrying the mounting mechanism 900, remotely returns for continued use. It should be understood that the drone body 800 should include a detachable battery structure to power the drone body 800 and other electrical components.

[0045] It should be noted that the first automatic push rod 910 and the second automatic push rod 920 can be electric push rods electrically connected to the UAV body 800, or other push rod structures capable of automatic extension and retraction in existing technologies. The wireless remote controller can integrate corresponding control buttons or joysticks to wirelessly control the first automatic push rod 910 and the second automatic push rod 920. It should be understood that those skilled in the art can implement this function using existing technologies. It should also be noted that the box cover 120 and the box body 110 can be connected by a snap-fit ​​spring pin. When the rocket detonator 1 is mounted on the mounting mechanism 900, the second automatic push rod 920 extends its end to block the box cover 120. When it is necessary to open the box cover 120, the second automatic push rod 920 is controlled to retract, causing the second automatic push rod 920 to separate from the box cover 120. At this time, the box cover 120 is unobstructed and will open as expected. Figure 1As shown, it flips open under the action of gravity; it should be noted that before the rocket detonator 1 is mounted, a lock is provided between the box 110 and the box cover 120 to lock them together. During mounting, the lock needs to be opened, and then the extension of the second automatic push rod 920 closes the box cover 120. It should be noted that this application includes... Figure 2 Only one first automatic push rod 910 is shown in the figure. In order to ensure the stability of the rocket detonator 1, the mounting mechanism 900 of this application should be equipped with multiple first automatic push rods 910 that can operate simultaneously in appropriate positions.

[0046] Reference Figure 1 and 2 It is understood that the mounting mechanism 900 is a detachable frame structure and the bottom of the mounting mechanism 900 is open.

[0047] Specifically, the mounting mechanism 900 can be manufactured using a lightweight yet strong material, such as aluminum profiles or other feasible materials. The manufacturing process can involve welding or bolting. The mounting mechanism 900 can be made from the same material to create a hook structure for mounting onto the drone body 800. Correspondingly, the drone body 800 can be equipped with... Figure 1 The two ends are flight control units and battery structures, and the middle is a connecting rod that connects the flight control units and battery structures, which facilitates the mounting and dismounting of the mounting mechanism 900.

[0048] Reference Figure 2 It is understood that a first sensor 930 capable of detecting the presence of an object is installed at the bottom opening of the mounting mechanism 900.

[0049] Specifically, the first sensor 930 is electrically connected to the UAV body 800. After the rocket detonator 1 is mounted in place, it can detect the presence of the detonator 1 and send a signal to the UAV body 800. After the rocket detonator 1 is released, it can detect the absence of the object and send a signal to the UAV body 800. The first sensor 930 can be a contact switch, photoelectric sensor, or infrared sensor, or other existing technologies.

[0050] Reference Figure 2-5 It is understood that the control device 600 includes a front control rope 610 and a control umbrella 620 connected to the front control rope 610. The front control rope 610 is provided with a rope loop 611 and a fire hook 612.

[0051] Specifically, the front control rope 610 is connected to the fuse assembly 700. The rocket engine 300 ignites and flies out of the launch tube 200, dragging the explosive belt 500 towards the target area. The control device 600 flies out of the launch box 100 under the pull of the explosive belt 500. At the same time, the control parachute 620 unfolds into the wind. Under the combined action of gravity and the resistance of the control parachute 620, the explosive belt 500 straightens in the air and lands above the obstacles in the target area. At the same time, the fuse 720 activates and delays, detonating the explosive belt 500, detonating to clear obstacles such as landmines or barbed wire.

[0052] Reference Figure 5 It is understood that the fuse combiner 710 is provided with a connecting rope 740, which is inserted into the rope loop 611;

[0053] The fuse 720 is provided with a pull rope 730, which is hooked into the pull hook 612. The pull hook 612 is connected to the front control rope 610 through the pull hook connecting rope.

[0054] Specifically, the length of the connecting rope 740 should be greater than the overall length of the pull rope 730, the pull hook 612, and the pull hook connecting rope. After the rocket engine 300 is launched, the explosive zone 500 is dragged out of the housing 110, and the fuse assembly 700 and the control device 600 are also dragged out of the housing 110. When the fuse assembly 700 is dragged, the pull rope 730, the pull hook 612, and the pull hook connecting rope are subjected to the force of the front control rope 610, thereby triggering the fuse 720 to act. After the fuse 720 is triggered and pulled out, the connecting rope 740 is tensioned and brings out the front control rope 612 and the control umbrella 620. The control umbrella 620 unfolds in the wind, causing the explosive zone to extend as a whole.

[0055] It is understood that the command and control box 400 includes:

[0056] The main control board is used to receive external control signals, process external control signals, and issue internal control signals; and

[0057] Battery.

[0058] Specifically, the main control board may be a PCB control board that integrates a wireless signal transceiver or a wired signal transceiver and other electrical components. It is understood that those skilled in the art can use existing technical means to implement the functions of the controller.

[0059] Understandable

[0060] A second sensor capable of detecting the presence of an object is provided between the box body 110 and the box cover 120.

[0061] Specifically, the second sensor is configured to detect when the lid 120 is open. Only when the lid 120 is detected to be open can the main control board send an ignition signal. The second sensor can be an existing technology such as a contact switch, photoelectric sensor, or infrared sensor, and is electrically connected to the main control board.

[0062] Reference Figure 3 It is understood that the rocket engine 300 includes a warhead 310, an electric igniter 320, a combustion chamber 330, a propellant grain 340, and a nozzle mount 350.

[0063] The above description is merely a preferred embodiment of this application and is not intended to limit this application. Various modifications and variations can be made to this application by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the principles of this application should be included within the protection scope of this application.

Claims

1. A drone demolition system, characterized by, include: A drone component, the drone component including a drone body and a wireless remote controller; Mounting mechanism, wherein a plurality of first automatic push rods and second automatic push rods are provided on the mounting mechanism; A rocket detonator, comprising: a launch box, the launch box including a box body with several lifting rings and a box cover; a launch tube, the launch tube disposed within the box body; a rocket engine, the rocket engine disposed within the launch tube; an explosive zone, the explosive zone disposed within the box body, the explosive zone including a head connector and a tail connector, the head connector being connected to the rocket engine; a fuze assembly, the fuze assembly including a fuze combiner and a fuze, one end of the fuze combiner being connected to the fuze, and the other end of the fuze combiner being connected to the tail connector; a control device, the control device disposed within the box body, the control device being connected to the fuze assembly for triggering the fuze to activate and ignite the explosive zone; and a command and control box, the command and control box being disposed outside the box body for receiving external control signals to trigger an ignition signal to ignite and launch the rocket engine; Specifically, when the first automatic push rod extends, it can hang the rocket detonator rod on the first automatic push rod via the lifting ring, i.e., hang it on the mounting mechanism. When the first automatic push rod retracts, it can disengage the rocket detonator from the first automatic push rod, i.e., disengage it from the mounting mechanism. When the second automatic push rod extends, it can prevent the box cover from opening. When the second automatic push rod retracts, the box cover can open under the action of gravity. The control device includes a front control rope and a control umbrella connected to the front control rope. The front control rope is provided with a rope loop and a firing hook.

2. The drone demolition system of claim 1, wherein, The mounting mechanism is a detachable frame structure with an opening at the bottom.

3. The drone demolition system of claim 2, wherein, A first sensor capable of detecting the presence of an object is installed at the bottom opening of the mounting mechanism.

4. The drone demolition system of claim 1, wherein, The fuse combiner is provided with a connecting rope, which is threaded into the rope loop; The fuse is equipped with a pull rope, which is hooked into the pull hook.

5. The drone demolition system of claim 1, wherein, The command and control box includes: The main control board is used to receive external control signals, process external control signals, and issue internal control signals; and Battery.

6. The unmanned aerial vehicle (UAV) blasting system according to claim 1, characterized in that, The box body and lid are equipped with a second sensor capable of detecting the presence of objects.

7. The unmanned aerial vehicle (UAV) blasting system according to claim 1, characterized in that, The rocket engine includes a warhead, an electric igniter, a combustion chamber, a propellant grain, and a nozzle mount.

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