KR101584488B1 - Ammunition for Mortar with Double Joint Structure - Google Patents

Abstract

The present invention relates to an ammunition for a mortar with a double joint structure, which prevents a propulsion part assembly and an airframe from being separated from each other by securing assembling stability while increasing a range using a rocket propellant. The ammunition for a mortar with a double joint structure comprises: a warhead part (10) which includes an airframe (15) filled with a bomblet assembly (20), a firing charge (14), a discharging plate (40), and a fuse (11) screwed to the front end of the airframe (15); and a propulsion part assembly (30) which has a base (33) having an ignition delaying part (34), a rocket housing (31) filled with a rocket propellant (32) and received in the rear end of the airframe (15), and a gun body (35) screwed to the rear end of the base (33).

Description

[0002] Ammunition for Mortar with Double Joint Structure [0003]

The present invention relates to a bombardment type ammunition that is loaded in a large-sized howitzer and fired by a rocket propellant to increase the range, and more particularly, to a bombardment type ammunition in which a charger and a rocket housing are combined The structure is partially modified to assure the stability of the assembly, so that the propulsion subassembly and the body are not separated from each other by the pressure of the foam gun and the combustion of the rocket propellant, and the propulsion subassembly is separated from the body To a bombardment type ammunition having a double bond structure in which a magnetite assembly is released.

In military operations using the howitzer, the need for technology to extend the range of shells to improve operational performance and striking ability is increasing, and in particular, the extension of range technology is essential for large ammunition.

As a technique to meet the demand for extending the range of such ammunition, a method of adding an antidisaster or a rocket propellant to existing ammunition is mainly used. Although drag reducing agents and rocket propellants are basically used separately, recently, a combination of a drag reducing agent and a rocket propellant is being studied in order to maximize the range.

These ammunition are assembled with screw and fastening assembly at the top and bottom of the head of the tofu, respectively. The new tube is divided into mechanical type and electronic type according to the structure of the new tube, and it is divided into impact type, time type type and proximity type type according to the operation mode. In addition, the body is made by the process such as forging, ingress (nozing), heat treatment, etc., and the inside of the body is filled with high explosives depending on the object to be hit and purpose, or the jatane is mounted.

Here, the ammunition in which the charcoal is mounted inside the body is called "dispersed carbon," and the dispersed carbon is filled with dozens to hundreds of small bombs inside the large bomb, and then fired over the target, Means a wide-range suppression weapon capable of emitting and projecting light, and it is also called a cluster bomb or cluster bullet.

There are various types of charcoal mounted on dispersed carbon, and the representative charcoal is Dual-purpose Improved Conventional Munitions (DPICM). The dual purpose bomb (DPICM) is manufactured in a point-to-point structure with a molding pebble method, and has a conical penetrator inside. The conical penetrator will be a high-speed metal jet during the explosion of the jets, exhibiting penetration power in the range of a few inches, and the outer jets will be fragmented after the explosion to exhibit a radius of several meters.

As shown in FIG. 1, the bombardment type ammunition of the dispersed carbon type has a body 15 filled with a magazine assembly 20 having a plurality of magazines assembled therein, a discharging charge 14 for discharge of magenta, And a crown portion (10) including a crown assembly (40) for pushing out the magazine assembly (20) and a crown tube (11) screwed to the tip of the cage (15) to evacuate the discharge charge (14) Wow; A base 33 provided with an ignition delay unit 34 in the interior thereof and a rocket propellant 32 which is filled in the inside thereof and whose rear end is screwed to the base 33, And a propulsion unit assembly 30 having a housing 31 and an injector body 35 screwed to the rear end of the base 33 to fix the drag reducing agent 36.

Here, the discharge charge 14 is filled in a cup-shaped discharge chamber medicine container 13 in which the opened distal end part is in contact with the new pipe 11 and the closed end part thereof is in contact with the discharge spring 14, Is exploded by the bulb 11 and explodes, thereby pushing the bulletin board 40 using the explosion pressure.

The conventional bombardment type ammunition is fired through a punch of a howitzer or the like and is then subjected to inertial flight and then self-propelled to the target point by the propulsion unit assembly 30. When the target bombardment reaches the target point, Thereby discharging the self-assemble assembly 20, so that the separated coals attack the target.

Bombardment ammunition is loaded on the howitzers in the state of being attached to the shell filled with the charge, and the inertia flight is carried out by the explosive power of the charge in the launch. In this process, since the drag reducing agent 36 in the injector body 35 is burnt, the flying distance is increased compared with the inertial flying due to the charge explosion. When the drag reducing agent 36 is completely burned, the ignition delay unit 34 burns the rocket propellant 32 in the rocket housing 31 and the ignition delay unit 34 is separated. Thus, the body 15 in which the charging assembly 20 is housed can fly to the target point.

When the body 15 reaches the target point, the new tube 11 operates to ignite the discharge charge 14, and a large pressure acts on the discharge plate 40 due to the explosion of the discharge discharge 14. The pusher assembly 40 and the pusher assembly 30 are moved to the rear of the body 15 to push the pusher assembly 20 and the pusher assembly 30 and the pusher assembly 20 and the pusher assembly 20, The publication 40 is separated from the head portion 10. The magenta assembly 20 is released above the target point and the discharged coals fly independently to attack the target.

In this way, the propulsion unit assembly 30 increases the range by using the rocket propellant 32 that is burned after the inertial flight. However, unlike the slow-burning drag reducing agent 36, the rocket propellant 32, . Accordingly, when the rocket propellant 32 is ignited, the lower end portion of the turbocharger 10 and the propulsion unit assembly 30 may be separated from each other.

This is because when the rocket propellant 32 is ignited, a strong pressure (expansion pressure) is generated due to the combustion of the rocket propellant 32 inside the propellant assembly 30 and this pressure acts on the propellant assembly 30 This is because deformation of the propulsion subassembly 20 has occurred. This deformation affects a portion where the bulge portion 15 of the bulletproof portion 10 and the pushing subassembly 30 are engaged so as to open the gap of the engagement portion so that the direct cause .

As an alternative to preventing the deformation of the propellant assembly 30 due to the pressure generated by the combustion of the rocket propellant, a separate device or component is added to the joint portion of the body 15 and the propellant assembly 30, There is a method of strengthening or reducing the deformation by increasing the thickness of the propellant assembly and strengthening the strength. However, both methods have a disadvantage in that the range of ammunition performance is degraded by increasing the total weight of the ammunition.

Meanwhile, as a result of investigation of the prior art related to the present invention, a large number of patent documents have been searched and some of them will be described as follows.

Patent Document 1 discloses a structure in which the warhead assembly and the propulsion unit assembly are integrally assembled and the separating mechanism separates the propulsion assembly and the warhead assembly after the explosion, It is possible to improve the range and accuracy as well as to increase the volume of the gun body by increasing the volume of the gun body compared to the conventional wing stabilized type ammunition, It describes the bombardment ammunition with the mechanism.

Patent Document 1 is similar to the present invention in that it describes the technology related to the bombardment type ammunition, but it is a technical point that the propulsion unit assembly is separated after the bombardment to fly only the warhead assembly, The technical point is completely different from the present invention in which additional separation is not performed.

Patent Document 2 discloses a rocket motor in which a new pipe is mounted on a tip end and a high explosive charge is filled in the inside thereof, a rocket propeller is filled in the inside thereof, a rocking motor And a disc-shaped auxiliary plate which is threadedly coupled to the rocket motor unit and formed between the rocker motor unit and the turntable, thereby preventing the rocket motor unit from being detached from the turntable during flight And a rocket propulsion range extension gun having a rocker motor part separation zone in order to maintain the performance of the extension of the range and to prevent the damage of the ally due to the nearness.

However, in Patent Document 2, similar to the present invention in that the rocket motor portion is not separated from the bullet portion, a plurality of screw holes are formed on the outer surface of the screw fastening portion, and a fastening screw is fastened to each screw hole to reinforce the fastened state And it is disadvantageous in that the productivity is deteriorated because an additional processing step and an additional part are required.

KR 10-2011-0070013 A KR 10-2012-0055327 A

SUMMARY OF THE INVENTION The present invention has been made in order to solve the problems of the prior art described above, and it is an object of the present invention to provide a propulsion unit assembly that does not require complicated devices or components, It is possible to prevent detachment of the pusher assembly from the bullet portion due to the deformation of the screw fastening portion by preventing the screw fastening portion of the bullet portion and the pushing portion assembly from being deformed by the pressure so as to maximize the effect of the slip distance. The present invention is directed to provide a bombardment type ammunition.

In addition, the present invention provides a double-joint structure in which the propulsion subassembly is separated from the cushion when the propulsion subassembly is released from the cushion due to the ejection pressure, It is intended to provide a bombardment ammunition.

According to an aspect of the present invention, there is provided a self-discharge device including: a body filled with a magazine assembly in which a plurality of magazines are assembled; a discharge plate for discharging a magazine and a magazine assembly; A tip end portion including a distal end of the tip; A rocket housing which is screwed to the rear end of the base to receive a drag reducing agent, and a rocking member which is fixed to the rear end of the rocking member, And a sprayer assembly having a sprayer body for holding the sprayer assembly,

In a bombardment type ammunition in which when a discharge pipe is operated due to operation of a new pipe after reaching a target position, a rocker housing and a body are separated from each other by a discharge,

The base and the body are connected to each other by a wedge or a concave / convex coupling with respect to a plane perpendicular to the threaded portion so that deformation does not occur in the screwed portion of the rocket housing and the body due to the combustion pressure generated when the rocket propellant in the rocket housing is burnt. And are assembled by staggering each other.

According to the present invention, there is provided a bombardment type ammunition having a double bond structure in which an inclined surface is formed at a rear end portion of the body so that the body and the base are wedged, And an inclined surface corresponding to the inclined surface is formed.

 According to the present invention, there is provided a bombardment type ammunition, wherein a circumferential protrusion is formed at a rear end portion of the bullet so that the bulb and the base are concavo-convex connected to each other, A circumferential groove into which the projecting portion of the protrusion is inserted is formed.

According to the bombardment type ammunition having the double bond structure of the present invention, the base and the rocket housing are fastened to each other by a saw screw so that the base and the rocket housing are not separated from each other by the high pressure generated when the rocket propellant is burned. .

Further, according to the bombardment type ammunition having the double bond structure of the present invention, when the bombardment is released, the propulsion subassembly is not separated from the body due to the firing pressure, and when the propulsion subassembly is discharged from the body Characterized in that the base and the rocket housing are engaged and the rocket housing is engaged with the torso so that the rocket housing is disengaged and the magnet assembly is released.

In addition, according to the bombardment type ammunition having the double bond structure of the present invention, the bullet is formed in a cylindrical shape so that the maximum amount of the carbon can be loaded.

According to the present invention, the injector body is formed in a boat-tail shape for reducing drag.

In addition, according to the bombardment type ammunition having the double bond structure of the present invention, the bullet body further includes a rotating ball which is attached to the bullet body to rotate the bullet through interaction with a steel wire formed on the bulge .

The bombardment type ammunition having the double bond structure of the present invention has a wedge or concave / convex coupling structure of the body and the base so that the body and the base can be stably assembled even when the rocket propellant is burned, It is possible to prevent the problem that the tofu portion of the ammunition and the propulsion subassembly are separated without adding the weight of the ammunition or increasing the weight of the ammunition.

In addition, according to the bombardment type ammunition having the double bond structure of the present invention, the base and the rocket housing are coupled to each other and the rocket housing is coupled to the torso. When the gun is deployed, There is an effect that the propellant subassembly is separated from the body and the selfassembly assembly is released when it is released by the discharge charge from above the target.

BRIEF DESCRIPTION OF THE DRAWINGS Fig. 1 is a schematic view showing a bombarded ammunition of a dispersed carbon type. Fig.
FIG. 2 is a reference view showing an operation process of a dispersed carbon-based bombardment type ammunition. FIG.
FIG. 3 is a view showing a bombarded ammunition having a double bond structure according to the present invention. FIG.
FIGS. 4 and 5 are enlarged views showing a coupling portion between a body and a base, which are essential parts of the present invention. FIG.

DETAILED DESCRIPTION OF THE PREFERRED EMBODIMENTS Hereinafter, a bombardment type ammunition having a double bond structure according to the present invention will be described with reference to the accompanying drawings.

As shown in FIGS. 3 to 5, the bombardment type ammunition having the double bond structure according to the present invention includes a body 15 filled with a magazine assembly 20 in which a plurality of magazines are assembled, A discharge tube 14 for discharging the discharge charger 14 and a discharge tube 40 for pushing out the charging assembly 14, a tube 11 screwed on the tip of the body 15 to evacuate the discharge charge 14, And a rotating barrel (12) for rotating the body (15) through interaction with a steel wire formed on the bobbin (15); A base 33 provided with an ignition delay unit 34 in the interior thereof and a rocket propellant 32 which is filled in the inside thereof and whose rear end is screwed to the base 33, And a propeller assembly (30) having a housing (31) and an injector body (35) screwed to the rear end of the base (33) to fix the drag reducing agent (36) The rocket housing 31 and the body 15 are separated from each other by the discharge plate 40 and the pusher assembly 30 and the magnet assembly 20 Is emitted.

It is preferable that the base 33 be formed of a material that prevents the screwed portion A of the rocket housing 31 and the body 15 from being deformed by the combustion pressure generated when the rocket propellant 32 in the rocket housing 31 is burned, And the body 15 are assembled by being staggered against each other with respect to a plane perpendicular to the threaded fastening portion A through wedge coupling or concavo-convex coupling.

4, an inclined surface 15a is formed at a rear end portion of the body 15 so that the body 15 and the base 33 are wedged, An inclined surface 33a corresponding to the inclined surface 15a of the body 15 may be formed.

 5, a circumferential protrusion 15b is formed at the rear end of the body 15 so that the body 15 and the base 33 are concavo-convex, and the outer side of the distal end of the base 33 And a circumferential groove 33b into which the protrusion 15b of the body 15 is inserted may be formed at the end portion.

The threaded portion A includes a discharge screw portion 31b formed on the outer peripheral surface of the rear end of the rocket housing 31 and a discharge screw portion 15c formed on the inner peripheral surface of the rear end of the body 15, So that the pushing assembly 30 and the magazine assembly 20 can be easily separated by the publication 40 when they are released.

However, the base 33 and the rocker housing 31 are separated from each other by the high pressure generated when the rocker 33 and the rocker housing 31 are burned or when the rocker propellant 32 is burned The base 33 and the rocket housing 31 are preferably fastened with a saw screw. To this end, a toothed screw portion 33c is formed on the outer side of the tip of the base 33 and a toothed screw portion 31a is formed on the inner side of the rear end of the rocket housing 31.

In addition, the dual purpose high bomb requires the ability to release the jets when it reaches the target without being separated by the launch pressure during the bombardment. To this end, the base 33 and the rocket housing 31 are engaged to release the propellant assembly 30 from the body 15 and release the maggot assembly 20 upon release from the target and the rocket housing 31 is coupled to the body 15).

The injector body 35 is preferably formed in a boat-tail shape to reduce the drag force. The injector body 35 is preferably formed in a cylindrical shape such that the charcoal 15 is maximally loaded. Do.

The bombardment type ammunition having the double bond structure of the present invention having the above-described structure is assembled by staggering each other against a plane perpendicular to the threaded portion of the tofu portion and the propulsion unit assembly. In the combustion of the rocket propellant, Thereby preventing deformation.

A magazine assembly 15 in which a magazine 15 and a plurality of magazines are stacked is inserted into the inside of a body 15 to which a rotary barrel 12 is welded on the outside of the rear end, 14) is installed. A male screw formed on the outer circumferential surface of the lower end of the new tube 11 is fastened to a female screw formed on the inner circumferential surface of the upper end of the cylindrical body 15 so that the new tube 11 is brought into contact with the discharge charge of the discharge tube. (11) is assembled.

After the rocket housing 31 is filled with the rocket propellant 32, the rocket housing 31 is inserted into the rear of the body 15 and the rocket housing 31 is inserted into the body 15 ). A base 33 having an injector body 35 equipped with a drag reducing agent 36 at its rear end and an ignition retard 34 therein is screwed into the rear end of the rocket housing 31, Thereby completing the bombardment type ammunition consisting of the head portion 10 and the thrust assembly 30.

In the normal propulsion subassembly 30, a deformation force acts on the inside of the propulsion subassembly 30 due to the pressure generated when the rocket propellant 32 is burned, So that the tightened portion of the portion A is opened and the fastening force of the screw fastening portion A is weakened.

However, in the present invention, unlike the conventional structure in which the surfaces vertical to the screw fastening portion A assembled with the flange portion 10 and the pushing portion assembly 30 are linearly in contact with each other, the wedge- So that even if a pressure due to the combustion of the rocket propellant (32) is applied to the screw fastening portion (A), it is structurally prevented from being deformed so that the screw fastening portion (A) is prevented from being widened. Therefore, even after the rocket propellant 32 of the propellant assembly 30 is burned after the bombardment ammunition is fired, the propellant assembly 30 is not separated from the body 15.

As described above, by merely changing the structure of the screw fastening portion A without changing the thickness of the screw fastening portion A or adding a component such as the stop bolt, It is possible to expect not only a simple process but also an effect that the desired distance can be maintained.

Meanwhile, as a result of the launch test applied to the bombardment ammunition for the verification of the present invention, the separation of the bombardment occurred in about 40% of the total test amount in the ammunition of the specification in which the present invention was not used. However, It was confirmed that separation of the tofu 10 and the propulsion subassembly 30 did not occur in all of the ammunition. In addition, it was confirmed through the structural analysis that the amount of widening of the screw fastening portion (A) was also reduced.

In addition, as a result of the ground release test and the launch test applied to the bombardment ammunition for the verification of the present invention, all the ammunition of the specification to which the present invention is applied does not cause separation at the time of bombardment, It was confirmed that the jig 30 was separated from the body 15 and the jigger assembly 20 was released.

While the present invention has been particularly shown and described with reference to exemplary embodiments thereof, it is to be understood that the invention is not limited to the disclosed exemplary embodiments, but, on the contrary, Those skilled in the art will appreciate that many modifications and variations of the present invention are possible without departing from the spirit and scope of the invention. And all such modifications and changes as fall within the scope of the present invention are therefore to be regarded as being within the scope of the present invention.

10 ... tofu
11 ... New building
12 ... Swivel Stand
...
14 ... discharge discharge
15 ...
15a ... inclined surface
15b ... protrusions
15c ... release thread
20 ... magnet assembly
30 ... propulsion assembly
31 ... Rocket housings
31a ... tooth thread
31b ... release thread
32 ... rocket propellant
33 ... base
33a ... inclined surface
33b ... groove
33c ... tooth thread
34 ... ignition delay unit
35 ... injector body
36 ... drag reduction agent
40 ... publishing room

Claims (8)

(40) for pushing out the discharge charger (14) and the magazine assembly (20) for discharging the magenta, and a discharger (40) for discharging the magazine assembly (20) A capillary (10) including a capillary (11) screwed to the tip of the body (15) to expel the charge (14);
A base 33 provided with an ignition delay unit 34 in the interior thereof and a rocket propellant 32 which is filled in the inside thereof and whose rear end is screwed to the base 33, And a propeller assembly (30) having a housing (31) and an injector body (35) screwed to the rear end of the base (33) to secure the drag reducing agent (36)
The rocket housing 31 and the body 15 are separated by the spring plate 40 when the discharge tube 14 is activated by the operation of the new tube 11 after reaching the target position, (20) is discharged,
The base 33 and the base 33 are fixed so as not to be deformed by the combustion pressure generated when the rocket propellant 32 in the rocket housing 31 is burned, Wherein the body (15) is assembled by being staggered and staggered with respect to a plane perpendicular to the threaded fastening portion (A) through wedge or uneven coupling to secure structural stability. The method according to claim 1,
A threaded portion 15c is formed at the rear end of the body 15 so that the base 33 is coupled to the rocket housing 31 and the rocket housing 31 is engaged with the body 15, A threaded portion 31b corresponding to the threaded portion 15c of the body 15 is formed on the outside of the rocket housing 31. A threaded portion 31a is formed on the inner side of the rocket housing 31, Is formed with a threaded portion (33c) corresponding to the threaded portion (31a) of the threaded portion (31). The method according to claim 1,
An inclined surface 15a is formed at a rear end portion of the body 15 so that the body 15 and the base 33 are wedged and an inclined surface 15a is formed at an outer end of the tip of the base 33, And the inclined surface (33a) corresponding to the inclined surface (15a) is formed. The method according to claim 1,
A protrusion 15b in the circumferential direction is formed at the rear end of the body 15 so that the body 15 and the base 33 are concavo-convexed and the body 15 is fixed to the outer end of the tip of the base 33, Is formed with a circumferential groove (33b) into which the projecting portion (15b) of the projecting portion (15b) is inserted. The method according to claim 1,
The base 33 and the rocket housing 31 are fastened with a saw screw so that the base 33 and the rocket housing 31 are not separated from each other by the high pressure generated when the rocket propellant 32 is burned. ≪ tb > The method according to claim 1,
Wherein the body (15) is formed in a cylindrical shape so as to maximally mount the magnetite. The method according to claim 1,
Wherein the sprayer body (35) is formed in a boat-tail shape for reducing drag. ≪ RTI ID = 0.0 > 35. < / RTI > 8. The method according to any one of claims 1 to 7,
Wherein the body (15) further comprises a rotating barrel (12) attached to the body (15) so as to rotate the body (15) through interaction with a steel wire formed on the body Bombardment ammunition.

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