KR101485111B1 - Manufacturing method of projectile casing is provided with a seperation wall - Google Patents

Abstract

The present invention relates to a method for manufacturing a projectile casing having an integrated separation wall. The method for manufacturing a projectile casing having an integrated separation wall according to the present invention comprises: a heating step of heating a metal material; a first forging step of forming a lower space by forging a lower part of the metal material heated in the heating step; a second forging step of forming an upper space by forging an upper part of the metal material heated in the heating step, wherein the upper space and the lower space have respective independent spaces separated by a separation wall; and a nosing step of nosing the metal material to install a fuse at the top end of the upper space in the metal material forged in the second forging step. According to the present invention, the separation wall is included to store an explosive and a propellant respectively in independent spaces in a main body in order to prevent heat caused by ignition of the propellant from being delivered to the explosive. Thus, it is possible to prevent unexpected explosion of the explosive.

Description

BACKGROUND OF THE INVENTION 1. Field of the Invention [0001] The present invention relates to a method of manufacturing a body having an integral separating wall,

The present invention relates to a method of manufacturing a body having an integral separating wall, and more particularly, to a method of manufacturing a body having an integral separating wall, which comprises a partition wall for accommodating explosives and a propellant in independent spaces, The present invention relates to a method of manufacturing a body having an integral separating wall capable of preventing the body from being transmitted.

Generally, launch vehicles such as ammunition are composed of a fuse, a warhead, and a propulsion unit. The fuse can be divided into a mechanical or electronic fuse. The fuse is a time function that explodes due to impact on the target, . These mechanical / fire fighters are sturdy and simple in structure, but they are limited in their ability to effectively kill enemies hidden in coveralls and cover.

In contrast, the electronic fuse has a proximity function using a radio wave including the function of a mechanical fuse, and it is possible to combine various functions such as a jetting function and an impact delay function which explodes after penetration. Such an electronic fuse box is advantageous in that it can be combined with a compact, precise and various functions. However, there are restrictions such as securing a small special power supply suited to the application and ensuring reliability against a harsh environment.

The explosive-use high-explosive assemblies using these new pipes are used to suppress intruder and target targets by the fragments generated by the high-temperature and high-pressure gas generated when the explosive of high-performance explosives filled in the body explodes.

Conventionally, the warhead of the high-explosive-use high-explosive is formed into a cup-like shape, and then the upper end of the mouth portion of the upper explosive is closed by the ingestion process to form a new pipe joint portion and a pushing portion, In the case of medium-sized ammunition, the propulsion unit uses a cartridge type of brass or iron shell, inserts a propellant therein and clamps the warhead at the end. In the case of a large-sized ammunition such as a howitzer plate, A propellant is embedded in a depleted container without a shell, and when the ammunition is fired, a warhead with a new pipe is inserted in the pore, a propellant assembly of the depleted container is inserted from the rear, the closure is closed, . Further, on the outer circumferential surface of such ammunition, there is provided a rotating band which is rotated by a steel wire to impart flight stability to the warhead.

So far, various methods have been devised to extend the range of ammunition flying. Among them, in the case of an extension gun for attaching an auxiliary propulsion unit to an ammunition, a propulsion unit and a warhead unit are separated from each other in the prior art. In this propulsion unit, high temperature is generated by combustion of the propellant. It shall be made of materials and structures capable of withstanding heat and pressure, and the warhead shall be made of materials that can form debris.

However, it is not easy to manufacture a conventional long-range extended high-explosive bomb, in which the tofu portion and the propulsion portion are separately separated, and the propulsion portion coupled in a separated form is damaged by falling during handling, There is a problem in that it can be separated from the drum by the pressure by the pressure. Further, a separate member for coupling the propulsion part and the toe part is required, which causes a problem that the total weight increases, and as a result, the destruction of the toe part is also reduced.

Fig. 1 shows the structure of such a conventional ammunition. The ammunition assembly shown in Fig. 1 comprises a turbocharger 10 and a propeller casing 4 constituted by a fuse 1, a toroid 2, a high explosive 3, a propeller opening 4 formed in the propeller casing 4, (5), and a propellant (20) composed of a propellant (6) located inside the propellant casing.

In such a conventional ammunition assembly, the body is made of a material capable of forming debris, and the propellant casing (4) is separately provided with good heat insulation property to prevent the heat generated by the combustion of the propellant (6) .

In such a structure, however, the gas generated from the propellant 6 is discharged to the joint portion between the propulsion section 20 and the warhead 10, and more specifically, to the propulsion section casing 4 and the high explosive 3, It sometimes occurs that the warhead is pulled out to the assembly part between the bodies 2 and the propulsion part is separated.

In addition, in the conventional ammunition, a separate body 2 separated from the pushing portion for ensuring the safety of the body from the impact of the impact and sealed at the bottom of the body is used, but in this case, the body can not be designed or manufactured to have a constant shape When the explosion of the high explosive filled inside is generated, non-uniform natural debris is generated. At this time, energy is consumed in the seam, and the size and the scattering direction of the debris are not uniform.

In addition, the conventional high-explosive airplane is flying at a very high speed and receives force in a direction opposite to the flight direction of the bullet due to the drag caused by the vacuum generated in the anteroposterior part during flight, .

As a result, the present applicant has found that, as shown in FIG. 2, in order to solve the problems of the conventional high-explosion as described above, the high explosive and the propulsion unit are arranged and assembled in the integral body, (Korean Registered Patent No. 10-1249772, registered on Mar. 28, 2013), which is equipped with a built-in type body capable of being stable and structurally stable, and additionally provided with a drag reduction device, .

The ammunition assembly desired by the present applicant is a new ammunition assembly that includes a new pipe 31, an integral body 32, a high explosive 33 disposed within the integral body, a propellant casing 34, the propellant casing 34, A charging stopper 35 for separating the propulsion casing 33 from the propulsion casing 34, an insulation plate 36, a propulsion engine insulation plate 37 attached to the propulsion casing 34, a propulsion device and a drag reducing casing 41), and a drag reducing device (42).

However, there has been a problem in that high-temperature and high-pressure gas transferred to the charge plug 35 and the insulating plate 36 can be transferred to the high explosive 33 during combustion of the propellant.

SUMMARY OF THE INVENTION The present invention has been made in an effort to solve the above-described problems, and an object of the present invention is to provide a fuel cell system and a fuel cell system in which a separating wall for accommodating explosives and a propellant in independent spaces is provided inside the body, And to prevent the explosion of unexpected explosives. The present invention relates to a method of manufacturing a body having an integral separating wall.

The present invention also relates to a method of manufacturing a body having an integral separating wall which is manufactured by a forging process so that the separating wall is integrally formed on the inner wall of the body, and the high temperature and high pressure gas of the propellant is prevented from being transmitted to the explosive device .

In addition, the present invention relates to a method of manufacturing a body having an integral separating wall which is made of an insulating material and can prevent heat from being transmitted to the separating wall and main body through explosives.

According to an aspect of the present invention, there is provided a method of manufacturing a body having an integral separating wall, the method including heating a metal material, forging a lower portion of the metal material heated in the heating step, The upper space and the lower space are separated by a separating wall so as to have a space independent from each other, and the upper space is formed by forging the upper portion of the metal material heated in the heating step, The method according to claim 1, further comprising a step of forging the metal material in the second forging step, wherein the metal material is forged on the top of the upper space of the forged metal material, , A rocket propellant and a drag reducing agent are disposed, the drag reducing agent is placed in the lower portion of the rocket propellant in a state where it is stored in a drag reducing agent casing And the rocket propellant is stored between the separating wall and the drag reducing casing.

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As described above, according to the present invention, there is provided a partition wall for allowing the explosive and the propellant to be contained in independent spaces in the body, thereby preventing the heat generated by the ignition of the propellant from being transmitted to the explosive, There is an advantage that it can be prevented.

In addition, the main body is manufactured in a forging process, and the separating wall is integrally formed on the inner wall of the main body, so that the high-temperature, high-pressure gas of the propellant is prevented from being transmitted to the explosive.

Also, since the body is made of an insulating material, the heat can be prevented from being transmitted through the partition wall and the main body by explosives.

1 to 2 are sectional views of a projectile according to the prior art.
3 is a perspective view of a body having an integral separating wall according to the present invention.
FIG. 4 is a cross-sectional view of a projectile to which a body having an integral separating wall according to the present invention is applied.
5 to 6 are flowcharts of a method of manufacturing a body having an integral separating wall according to the present invention.

Hereinafter, embodiments of the present invention will be described with reference to the accompanying drawings. The same reference numerals shown in the drawings denote the same members. In describing the present invention, a detailed description of known functions and configurations incorporated herein will be omitted so as to avoid obscuring the subject matter of the present invention.

(A) and a rocket propellant (B) to prevent the high temperature and high pressure gas of the rocket propellant (B) from being transmitted to the explosive (A) when the rocket propellant (B) B are divided by the separating wall 130.

The partition wall 130 functions as a kind of partition wall that divides the upper space 110 and the lower space 120 formed in the main body 100 and the upper space 110 is provided with the explosive A , And a rocket propellant (B) is disposed in the lower space.

The drag reducing agent C may be disposed in the lower space 120 together with the rocket propellant B and the drag reducing agent C may be disposed between the rocket propellant B and the drag reducing agent casing 300 Respectively.

Hereinafter, a body having an integral separating wall according to the present invention will be described.

The body having the integral type separating wall according to the present invention includes a main body 100 and a separating wall 130 provided on the inner wall of the main body 100.

The main body 100 is formed in a tubular shape having upper and lower openings, and a partition wall 130 dividing an inner space is formed on the inner wall of the main body 100. It is a feature of the present invention that the separating wall 130 is integrally formed with the main body 100.

4 and 6, the divided space defined by the partition wall 130 is divided into an upper space 110 in which the explosive A is disposed and a rocket propellant B in which the explosive A is disposed And a lower space 120.

4, the drag reducing agent C is preferably connected to the opening of the lower space 120, but the drag reducing agent C in the lower space 120 is not limited to the rocket propellant B As shown in Fig. In this case, the drag reducing agent (C) should be stored inside the separate drag reducing agent casing (300).

The drag reduction casing 300 has circular penetrations 301 and 302 on the upper and lower surfaces thereof and heat generated when the rocket propellant B is burned is passed through the penetration portion 301 on the upper surface, (C) is burned, and the rocket propellant (B) is ignited by a separate propulsion device (not shown).

As described above, since the drag reducing agent (C) is burned, a certain amount of gas is continuously supplied to the anchor portion during high-speed flight, thereby reducing the drag caused by the vacuum generated in the anteroposterior portion of the projectile in flight. As a result, A more detailed description of the operation of drag reducing agent (C) and rocket propellant (B) is as disclosed in Korean Patent No. 10-1249772, which is known to the applicant.

The rocket propellant B is disposed inside the lower space 120 without a separate rocket propellant casing as in the prior art. The rocket propellant casing is separated from the inner wall of the main body 100 by a separation May be omitted by the wall 130.

Accordingly, since the rocket propulsion casing is omitted in the design of the body, it is possible to reduce the weight and reduce the connection area, thereby reducing the negative pressure during the ignition of the rocket propellant (B), that is, , And the accuracy can be increased.

When the rocket propellant (B) is ignited by the separation wall (130) formed integrally with the main body (100), the connection part between the explosive (A) and the rocket propellant (A) from being transmitted.

As shown in FIG. 4, a fuse 200, which is an explosive device capable of blowing explosives disposed in the upper space 110, is installed in the opening of the upper space 110, In order to minimize the resistance of the air, the shape in which the new pipe 200 and the main body 100 are combined has a generally bell-shaped shape.

Accordingly, it is preferable that the upper portion of the main body 100 is removed during the manufacturing of the main body 100.

Hereinafter, a method of manufacturing a body having the integral separating wall having the above-described structure will be described with reference to FIGS. 5 to 6. FIG.

The method of manufacturing a body having the integral separating wall according to the present invention includes a heating step (S100), a first forging step (S200), a second forging step (S300), and a filling step (S400).

The heating step S100 is a step of heating the metal material M forming the main body 100 so that a forging process can be performed. The main body 100 of the present invention contains 0.5 to 0.7% of carbon, Of 0.80 to 0.90% by weight. For example, the main body 100 is preferably formed of a material from which fragments can be easily formed.

In addition, the main body 100 is provided with a heat-resistant heat resistant material (not shown) so as to prevent heat generated by ignition of the rocket propellant B disposed in the lower space 120 from being transmitted to the inside of the upper space 110. [ May be used.

The metal material M heated by the heating step S100 as described above is subjected to hot forging twice. The first forging step S200 is a step for heating the heated metal material M, as shown in FIG. 6 (b) The lower portion of the heated metal material M is forged to form the lower space 120 and the second forging step forging the upper portion of the heated metallic material M as shown in Figure 6 (c) ).

Forging (forging) is a method of making a uniform shape by a mechanical method of kneading or pressing a solid metallic material with a hammer or the like, and forging at a temperature higher than the temperature at which recrystallization proceeds in the material (Hot forging), forging at a recrystallization temperature is referred to as "hot forging", and forging at a lower temperature is called cold forging (cold forging).

As the upper portion of the metal material M is forged by the second forging in the state where the lower portion is forged by the first forging step S200, the separating wall 130 is formed integrally with the upper space 110, The lower space 120 has an independent space.

The explosive A may be disposed in the upper space 110 and the rocket propellant B may be disposed in the lower space 120 as described above.

In addition, after the second forging step S300, the new metal material M is forged through the second forging step S300 so that the new pipe 200 can be installed on the upper part of the upper space 110. [ Step S400 is performed.

Optimal embodiments have been disclosed in the drawings and specification. Although specific terms are used herein, they are used for the purpose of describing the present invention only and are not used to limit the scope of the present invention described in the meaning of the claims or the claims. Therefore, it will be understood by those skilled in the art that various changes and modifications may be made without departing from the scope of the present invention. Accordingly, the true scope of the present invention should be determined by the technical idea of the appended claims.

A-explosive B-rocket propellant
C-drag reducing agent
100-body 110-upper space
120-lower space 130-separating wall
200-fuse
300-drag reducing agent casing 301, 302-

Claims (7)

delete delete delete delete A heating step of heating the metal material,
A first forging step of forging a lower portion of the metal material heated in the heating step to form a lower space;
A second forging step of forming an upper space by forging the upper part of the metal material heated in the heating step so that the upper space and the lower space have independent spaces by the partition walls;
Wherein the metal material is forged in the second forging step, and a new pipe is installed at the top of the upper space of the metallic material,
An explosive is disposed inside the upper space,
Inside the lower space,
Characterized in that a rocket propellant and a drag reducing agent are disposed in a lower portion of the rocket propellant in a state where the drag reducing agent is stored in the drag reducing agent casing so that the rocket propellant is stored between the separation wall and the drag reducing agent casing Wherein the separating wall is provided with an integral separating wall. delete delete

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