A drone launching device for a mortar with multi-barrel

Abstract

The present invention relates to a drone launching device that loads a drone into each of the multiple chambers formed in the chamber block of a multi-barreled mortar and launches it to a certain altitude. The purpose of the invention is to provide a drone launching device in which a drone is loaded like a mortar round into each chamber formed in the chamber block of a multi-barreled mortar installed inside an armored vehicle with guaranteed protection, launched, and the drone, which is combined and integrated with the launching device by explosive pressure, is propelled out of the muzzle and, after a certain period of time has elapsed, the launching device and the drone are separated in the air so that the drone unfolds its wings and flies by its own power. The device is characterized by being composed of: a drone with folded wings and propellers; a sabot assembly that connects the drone to the drone and fixes the drone while connecting the drone to the propulsion unit; a propulsion unit that is combined with the sabot assembly and generates a thrust force to launch the drone out of the muzzle; and a separation device that separates the drone and the sabot assembly after the drone has left the muzzle. The present invention overcomes the range limitations of conventional mortars, enabling the destruction and suppression of targets located at distances several times the range of the mortar, and also enables the effect of carrying out a swarm drone attack by launching numerous drones simultaneously.

Description

Technology Field

[0001] The present invention relates to a drone launching device that loads drones into a plurality of chambers formed in the chamber block of a multi-barreled mortar and launches them to a certain altitude. Background Technology

[0002] The use of drones has become commonplace in modern warfare, and countries around the world are competitively developing and producing suicide drones.

[0003] In particular, small suicide drones are effectively used for short-range aerial reconnaissance and the elimination of high-risk targets at the platoon and squad levels, and launchable suicide drones are fired using high-pressure compressed air or CO2 gas from a circular launch tube or a canister, which is a disposable box containing the drone.

[0004] These suicide drones are deployed and launched in the field using dedicated controllers to scout and destroy targets; however, this presents a problem in battlefield situations where friendly and enemy suicide drones coexist, potentially placing the operator in a position where they could become a target of enemy drones. The problem to be solved

[0005] The present invention aims to break away from the concept that mortars use only mortar rounds and to provide a launch device capable of loading, firing, and operating drones like mortar rounds into individual chambers formed within the chamber blocks of a multi-barreled mortar installed inside an armored vehicle with guaranteed protection. The device causes a primer and an explosive charge to detonate via a firing rod, launches a drone integrated with a launch device by the explosive pressure, and separates the launch device from the drone in mid-air after a certain period of time has elapsed, allowing the drone to unfold its wings and fly under its own power. The invention is designed to launch a single self-destructing drone or multiple small self-destructing drones simultaneously. means of solving the problem

[0006] A drone launcher for a multi-barreled mortar according to the present invention for achieving the above objective comprises: a drone (2, 20) with its wings and propeller folded in order to launch a drone loaded into each chamber formed in the chamber block of the multi-barreled mortar;

[0007] A propulsion unit (5) characterized by being configured such that the drone is propelled by the explosive force of the propulsion charge, and the upper part has a hinge groove to which a detachable part is connected and a drone propeller storage groove (52) formed therein, and a ball retainer (4) having a ball installed on the circumferential surface, and the lower bottom surface has a gas inlet pipe (76) formed on a convex surface that is connected to a hemispherical groove, an ignition tube (55) connected to the inner center and the lower part connected to a tripod support, a hollow thin steel hemisphere (54) having a detonator (9) inserted into the ignition tube, and a propulsion charge (8);

[0008] A detachment bundle (6) comprising a plurality of detachment parts (61, 62) that can wrap around a drone and be connected to or separated from a propulsion unit, an uneven coupling part (64, 65) formed on the upper side by hinge pins, a hinge projection (66) formed on the lower side to be connected to a propulsion unit, and a spring (67) having one end connected to the inner circumference of the detachment part to activate the separation of the drone and the detachment part;

[0009] A separation device characterized by being operated using explosive gas generated inside a hollow thin steel hemisphere, comprising a tapered pin (7) inserted into a hole of an uneven coupling portion (64, 65) formed at the upper end of each detachable part, a cylinder chamber (71) formed in a propulsion cylinder that is connected to a hollow thin steel hemisphere by a gas inlet pipe (76) and equipped with a discharge pipe (77), a piston (72) housed in the cylinder chamber equipped with a rod, and a steel wire (74) connecting the tapered pin and the rod;

[0010] It is characterized by being composed of. Effects of the invention

[0011] The drone launcher for a multi-barreled mortar according to the present invention can provide fire support with mortar rounds from a multi-barreled mortar as well as launch one or dozens of drones simultaneously, thereby overcoming the range limitations of conventional mortars and enabling the destruction and suppression of targets located at distances several times the range of the mortar, and also achieving the effect of performing a swarm drone attack by launching numerous drones simultaneously. Brief explanation of the drawing

[0012] FIG. 1 is a cross-sectional view illustrating that a drone launcher for a multi-barreled mortar according to the present invention is combined and integrated with a drone and loaded into a single chamber formed in the chamber block of the multi-barreled mortar, and that the drone launcher can be used in combination with mortar rounds in the multi-barreled mortar. FIG. 2 is a cutaway view illustrating the configuration of a drone launcher for a multi-barreled mortar according to the present invention. FIG. 3 is an explanatory diagram illustrating the configuration of a separation device for a drone launcher for a multi-barreled mortar according to the present invention, showing only the uneven coupling parts of two detachable parts and showing only the parts of the propulsion part related to the piston chamber. <Explanation of symbols for major parts of the drawing> 1 : Chamber block 10 : Mortar shell 11 : Trigger Rod 2, 20 : Drone 3 : Launching device 4 : Ball retainer 5 : Propulsion section 52 : Propeller protection cylinder 53: Cylindrical protrusion 54: Hollow, thin steel hemisphere 55 : Ignition tube 56 : Tripod support 57 : Propulsion cylinder 6 : Shed skin cluster 61, 62 : Shed skin 64, 65: Uneven joint 66: Hinge projection 67 : Spring 7 : Tapered pin 71: Cylinder chamber 72: Piston 73 : Piston rod 74 : Wire 76 : Gas inlet pipe 77 : Discharge pipe 8 : Propellant 9 : Detonator Specific details for implementing the invention

[0013] Hereinafter, a drone launcher for a multi-barreled mortar according to the present invention will be described with reference to the attached drawings.

[0014] FIG. 1 is a cross-sectional view illustrating that a drone launcher for a multi-barreled mortar according to the present invention is integrated with a drone and loaded into a single chamber formed in the chamber block of the multi-barreled mortar, and that the drone launcher can be used in combination with mortar rounds in the multi-barreled mortar. FIG. 2 is a cutaway view showing a portion of the configuration of a drone launcher for a multi-barreled mortar according to the present invention.

[0015] The multi-barreled mortar is a weapon system consisting of multiple barrels, a chamber block (1), and a firing shock reduction device connected to the bottom of the chamber block, characterized by the ability to load projectiles by rotating the chamber block.

[0016] A drone launcher (3) for a multi-barreled mortar, which utilizes the strengths of the chamber block rotary loading system to operate a mortar round (10) and a drone in combination in a multi-barreled mortar, is characterized by being composed of: a drone (2, 20) with folded wings and propellers as illustrated in FIGS. 1 and 2; a detachable assembly (6) that connects the drone and the propulsion unit while fixing the drone; a propulsion unit (5) that is coupled to the detachable assembly and generates a propulsion force to shoot the drone out of the muzzle; and a separation device that separates the drone and the detachable assembly after they have detached from the muzzle.

[0017] The above propulsion unit (5) is coupled to the drone through a detachable casing assembly and is a cylinder with the same diameter as the chamber of the chamber block, making chamber insertion easy. When the propulsion unit cylinder is loaded into the chamber, a sealed space is formed by a hemispherical groove. When the firing rod (11) ignites the primer, the propellant charge stored in the hemispherical groove explodes, and the gas pressure generated at this time propels the detachable casing assembly coupled to the propulsion unit and the drone until they exit the muzzle. Its configuration includes a drone propeller protection cylinder groove (52) having a cylindrical projection (53) formed at a certain height that serves as a support to maintain the central axis of the propulsion unit cylinder and firmly fix the drone when multiple detachable casings, each coupled to the propulsion unit by a hinge, are coupled, and a hinge groove formed to which each detachable casing is coupled is formed, and a hemispherical groove is formed on the lower bottom surface. A propulsion cylinder (57) characterized by having a ball container (4) equipped with a moving body installed on the circumferential surface of the cylinder;

[0018] A hollow thin steel hemisphere (54) that is combined and integrated into the hemispherical groove of the propulsion cylinder to prevent friction and twisting during propulsion movement in the barrel due to deformation of the hemispherical groove caused by the explosive force of high temperature and high pressure to which the propulsion charge is instantaneously exposed when it explodes;

[0019] It is characterized by being composed of a primer coupled to the lower part of the ignition tube; and a propellant charge (8) fitted into the ignition tube.

[0020] The above hollow thin steel hemisphere (54) is a hollow hemisphere made of thin steel sheet so as to withstand the high heat and high pressure generated when the explosive explodes inside the hemispherical groove, and is integrated with the hemispherical groove of the propulsion cylinder to form three cylinder chambers (71), and a gas inlet pipe (76) connecting the cylinder chambers and the hollow thin steel hemisphere to supply high-pressure gas to each cylinder chamber;

[0021] It is characterized by having an ignition tube (55) comprising a conical end portion connected to the center of a hollow thin steel hemisphere, a primer insertion groove formed on the bottom surface of the conical portion, an ignition hole drilled in the conical surface to allow the explosive force of the primer to lead to the explosion of the propellant charge, and a tripod support (56) that connects the bottom of the conical portion and the inner surface of the steel hemisphere to prevent twisting.

[0022] The above-mentioned detachment assembly (6) serves to connect the drone and the propulsion unit, facilitates the storage and movement of the drone by ensuring a secure connection between the launch device and the drone, protects the drone by blocking contact between the drone and the inner surface of the mortar's barrel during the process of the drone being fired toward the muzzle, and is equipped with a function to quickly detach multiple detachment members from the drone. To implement these functions, the assembly is characterized by having multiple arc-shaped surfaces that wrap around and connect to the body of the drone to fix the drone, wherein the upper part of each piece is formed with an uneven coupling part (64, 65) equipped with a tapered pin insertion hole to facilitate the connection and separation of the multiple arc-shaped surfaces, and the lower part is formed with a hinge projection (66) that receives propulsion force and connects to the propulsion unit cylinder, allowing it to rotate approximately 90 degrees in the connected state, and comprises multiple detachment members (61, 62) that can store one drone or several small drones;

[0023] A spring (67) inserted into the inner surface of each detachment, with one end in contact with the drone body and the other end fixedly coupled to the detachment, so that when multiple detachments are separated, the detachments are ejected from the drone by the compressive force of the spring, allowing the drone to unfold its wings normally;

[0024] It is characterized by being composed of a hinge projection (66) formed at the lower part of each detachable, which is connected to the propulsion part by a hinge pin, acts as the center of motion of the detachable, and tightens the body of the drone together with the uneven coupling part to connect the drone.

[0025] As an embodiment of the present invention, a detachment bundle for a simple structure and easy separation is formed by combining three detachments.

[0026] FIG. 3 is an explanatory diagram illustrating the configuration of the separation device of a drone launcher for a multi-barreled mortar according to the present invention, showing only the uneven coupling parts of the two detachable parts and only the parts of the propulsion part related to the piston chamber.

[0027] The above separation device is characterized by wrapping the body of the drone with a plurality of detachable parts and connecting each of them with tapered pins to firmly restrain the drone, thereby facilitating storage and movement of the drone, and removing the tapered pins using high-pressure gas generated from the propulsion unit when the drone is loaded into the chamber and fired. Immediately after the drone and the drone launcher are separated from the muzzle, each detachable part is ejected from the drone, and subsequently, the propulsion unit is also separated from the drone along with the detachable part, so that the drone, freed from restraint, unfolds its wings and flies under its own power to enter into a mission.

[0028] To implement these functions, as illustrated in FIG. 3, a tapered pin (7) inserted into the hole of the uneven coupling portion (64, 65) of each detachable skin;

[0029] A cylinder chamber (71) having a discharge pipe (77) that facilitates the movement of the piston and is connected to the interior of a hollow, thin steel hemisphere via a gas inlet pipe (76); and a piston (72) having a rod that is housed in the cylinder chamber and functions to pull out a tapered pin connected to a steel wire coupled to a rod while advancing downward by explosive high-pressure gas;

[0030] It is characterized by being composed of a steel wire (74) connecting the tapered pin and the piston rod.

[0031] The ball retainer (4) equipped with the above-mentioned rolling element (ball) is a component in which balls are arranged at regular intervals on a metal plate such as a strip and coupled to allow ball rotation. It is coupled to the upper circumferential surface of each detachment and the circumferential surface of the propulsion cylinder, and when the detachment bundle coupled with the drone is propelled toward the muzzle, it comes into contact with the inner surface of the gun barrel. As it moves forward, the balls rotate due to the force of rotation in line with the direction of the rifling, thereby counteracting the force of rotation of the launching device and preventing the drone from rotating.

[0032] Therefore, as an example, it was installed only on the circumferential surface of the propulsion part, but if necessary, ball retainer pieces consisting of 3-4 balls can be attached to various parts to prevent rotation.

Claims

Claim 1 A drone (2, 20) with wings and propellers folded to launch a drone loaded into each chamber formed in the chamber block of a multi-barreled mortar; a propulsion unit (5) characterized by having a hinge groove to which a detachable casing is connected and a drone propeller storage groove (52) formed on the upper part, a ball retainer (4) equipped with a ball installed on the circumferential surface, a thin steel hemisphere (54) that is quickly hollowed out and connected to a hemispherical groove on the lower bottom surface, and a propulsion charge (8), and propelling the drone by the explosive force of the propulsion charge; a detachable casing bundle (6) composed of a plurality of detachable casings (61, 62) that can surround a single drone and be connected to or separated from the propulsion unit and are connected to the propulsion unit by a hinge pin; and a tapered pin (7) inserted into a hole of an uneven coupling part (64, 65) formed on the upper part of each detachable casing, and a discharge pipe (77). A drone launcher for a multi-barreled mortar, characterized by being composed of a cylinder chamber (71) formed in a propulsion cylinder and connected to a hollow thin steel hemisphere by a gas inlet pipe (76), a piston (72) housed in the cylinder chamber having a rod, and a steel wire (74) connecting a tapered pin and the rod, and operating using explosive gas generated inside the hollow thin steel hemisphere. Claim 2 A drone launching device for a multi-barreled mortar according to claim 1, characterized in that the plurality of detachable casings (61, 62) constituting the detachable casing assembly are composed of: an uneven coupling portion (64, 65) formed on the upper side to wrap around and fix the drone; a hinge projection (66) formed on the lower side to be coupled to a propulsion portion; and a spring (67) having one end coupled to the inner circumference of the detachable casing to activate the separation of the drone and the detachable casing. Claim 3 A drone launcher for a multi-barreled mortar, characterized in that, in claim 1; the hollow thin steel hemisphere (54) of the propulsion unit is coupled and integrated into the hemispherical groove of the propulsion unit and comprises a gas inlet pipe (76) formed on a convex surface; an ignition tube (55) coupled to the inner central part and coupled to a tripod support at the bottom; and a primer (9) inserted into the ignition tube.

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