KR20180074870A - Explosive projectile of high-angle gun firing type - Google Patents

Abstract

The present invention relates to a cannon-launching shell launch vehicle including a cannon body portion provided with a fuse and a high explosive, a rocket propulsion unit including a rocket body and a rocket propellant and provided at the rear end of the cannon body portion, an ignition delay unit including an igniter body and an igniter, provided at the rear end of the rocket propulsion unit, and igniting the rocket propulsion unit such that ignition is performed in a case where a predetermined time elapses from launching of the shell launch vehicle, and a drag reducing unit provided at the rear end of the rocket propulsion unit to increase a range by reducing the drag generated in the cannon bottom portion of the shell launch vehicle. The igniter and the igniter body are screw-fastened, and thus deviations in terms of rocket propulsion performance and range can be forestalled. As a result, the shell launch vehicle can be improved in terms of accuracy.

Description

{EXPLOSIVE PROJECTILE OF HIGH-ANGLE GUN FIRING TYPE}

In the present invention, the separation force (or tightening force) of the igniter during the combustion of the rocket propellant is uniformly applied to the rocket propellant burner mounted on the large-sized howitzer or the like so that the rocket propulsion performance is varied and the range deviation is generated. And to thereby improve the accuracy of the projectile body, thereby improving the accuracy of the projectile body.

As is well known, there is a continuing need for a range extension technique to improve the operational performance and hitting ability of a large-diameter grenade launcher (i.e., ammunition) that is loaded and launched in a howitzer.

As a technique to meet the demand for this range extension, a method of applying a drag reducer or a rocket propellant to existing ammunition has been developed. In the past, a drag reducer or a rocket propellant was applied individually, but recently, in order to maximize the range A combination of drag reducing agent and rocket propellant is being studied.

Also, because the range requirement may be different depending on the purpose of operation, the projectile body may be developed by applying the drag reduction unit or the rocket propulsion unit alone, or the two devices may be combinedly applied.

At the upper end of such a projectile, a new pipe and a body part are assembled, and at the lower end, a rocket propulsion part and a drag reduction part are assembled, respectively.

In this case, the new pipe functions to blow off the high explosives of the body part or to discharge the dispersed carbon, and it can be classified into mechanical type and electronic type depending on the structure of the new pipe, and can be classified into impact type, have.

In addition, the body part is manufactured by a process such as forging, entering (heating), heat treatment, etc., and the inside of the body part is filled with high explosives or charged with charcoal according to the object to be hit and purpose. There are advantages in the manufacturing process in many aspects such as the manufacturing time of the bullet, charging of high explosives, and formation of uniform fragments by explosion of high explosives.

Meanwhile, the rocket propulsion unit is provided to increase the range of ammunition. The rocket propulsion unit may include a rocket propellant, an ignition retarder, a rocket body, and the drag reduction unit includes a drag reducing agent and a sprayer body. The rotating tangs are welded in the form of a ring at the back of the projectile, which acts to convert the explosion pressure of the charge into the velocity energy and rotational energy of the body at the time of blasting.

Here, the rocket propulsion unit not only increases the speed of the ammunition, but also increases the range by acquiring auxiliary thrust through the combustion of the rocket propellant during the flight after the ammunition is deployed.

In order to ignite the rocket propellant after a certain time delay, an igniter is required. The position of the igniter can be assembled in various positions according to the design. In most ammunition including the rocket propulsion portion, the igniter body The igniter can be assembled.

For example, as shown in FIGS. 1 and 2, the igniter is inserted into the igniter assembly portion of the igniter body, and then the assembly ring is press-fitted and assembled. The press-fitted assembly ring is formed by a strong motion The igniter should be fixed to the igniter body even if the setback force generated by the energy is generated, and when the rocket propellant is burned, when the high pressure formed by the propellant combustion pushes the igniter, the igniter should be detached from the igniter body at a certain pressure In order to achieve this, a separating force corresponding to a specific pressure must be set, and not only separation force but also hermeticity must be ensured.

According to this necessity, the assembly ring is usually made of lead, and the separating force of the igniter is set in a hollow assembly space formed between the inner diameter of the rocket body circular assembly and the outer diameter of the circular igniter, For example, a ring shape obtained by cutting a thick pipe) into a press apparatus.

In addition, the separation force of the igniter is determined by the dimensions of the three components of the rocket body, the igniter, and the assembly ring. When each component is processed or manufactured in large quantities, it has substantially dimensional deviations. A difference in separation force may occur due to the deviation.

Even in the process of assembling them, when the assembly ring is press-fitted, the separation force may be varied due to the pressing pressure of the press equipment, the pressing depth, and the like. That is, the separation force is the result of the contact area, frictional force, and stress of the motor body and the igniter after the assembly ring is press-fitted.

Of course, it is possible to provide the separating force required in design through process control while strictly managing the combination of dimensions of the three parts and performing the most precise processing, but there is a problem that the entire manufacturing cost including the process cost is increased.

On the other hand, the material of the assembly ring is lead to ensure assembly and hermeticity. The lead material has a higher coefficient of thermal expansion and a lower melting point than other metals, so that when the heat is applied relatively higher than the melting point, When the rocket propellant is combined with the drag reducing agent for the purpose of extending the range, the drag reducing agent first burns for a certain time before the rocket propellant ignites. When the rocket propellant is burned for at least 10 seconds or more at about 500 ° C Since the assembly ring is directly exposed to the flame while the drag reducing agent is burned on the assembly ring fastening structure, the physical properties of the assembly ring due to the heat at high temperature are changed, and it is directly connected to the change of the separation force. It can act as a factor preventing it from occurring.

As described above, in order to prevent the difference in the range of each ammunition from the difference in the range of the ammunition due to the characteristics of the conventional ammunition that strikes a target range corresponding to the target, rather than the precision guided shell aimed at precisely blowing the target with a small quantity, , It is necessary to uniformly separate the propellant from the combustion pressure uniformly. However, there is a problem that the combustion pressure difference of the rocket propellant is caused by the dimensional deviation of the parts and the deviation of the separation force due to thermal deformation, There is a problem that the difference in the range of each ammunition is severe, and also the dispersion degree is increased, thereby hindering the effective hitting of the target.

1. Published Patent Application No. 10-2006-0006983 (published on January 20, 2006) 2. Registration No. 10-0156675 (registered on July 23, 1998)

In the present invention, the separation force (or tightening force) of the igniter during the combustion of the rocket propellant is uniformly applied to the rocket propellant burner mounted on the large-sized howitzer or the like so that the rocket propulsion performance is varied and the range deviation is generated. And to improve the accuracy of the projectile body, thereby providing a projectile-type projectile body.

In addition, the present invention can maintain the fastening performance and the sealing performance realized in the assembling ring coupling system by assembling the igniter body and the igniter directly by using the screw fastening method without using the assembly ring fastening method which is difficult to provide a uniform separation force To provide a bombarded ballistic launcher in which the igniter can be uniformly separated from the combustion pressure of a particular rocket propellant.

The objects of the embodiments of the present invention are not limited to the above-mentioned objects, and other objects not mentioned can be clearly understood by those skilled in the art from the following description .

According to an embodiment of the present invention, there is provided a rocket propulsion unit including a rocker body including a rocker body and a rocket propellant, a rocker propulsion unit provided at a rear end of the rocker body, and an igniter body and an igniter, An ignition delay unit provided at a rear end of the rocket propulsion unit for igniting the rocket propulsion unit to ignite when a lapse of a predetermined time elapses after the lunar launch object is fired; And a drag reducing part provided at a rear end of the propelling part, wherein the igniter body and the igniter are coupled by a screw fastening method.

Also, according to the embodiment of the present invention, it is possible to provide a foam gun type flash projecting body in which the flash tube and the torus portion are each formed in a streamlined conical shape.

In addition, according to the embodiment of the present invention, the gun body and the rocket propelling unit may be provided with a foam gun type flash projecting body provided with a disk-shaped auxiliary plate so as to maintain the state of engagement between the two.

In addition, according to the embodiment of the present invention, the igniter body and the igniter may be provided with a foam gun type flash projecting body having an O-ring made of a rubber material at a joint portion to supplement the sealing force.

In the present invention, the separation force (or tightening force) of the igniter during the combustion of the rocket propellant is uniformly applied to the rocket propellant burner mounted on the large-sized howitzer or the like so that the rocket propulsion performance is varied and the range deviation is generated. Therefore, it is possible to improve the accuracy of the flying object.

In addition, the present invention can maintain the fastening performance and the sealing performance realized in the assembling ring coupling system by assembling the igniter body and the igniter directly by using the screw fastening method without using the assembly ring fastening method which is difficult to provide a uniform separation force The igniter can be uniformly separated from the specific rocket propellant combustion pressure.

In addition, by applying the screw fastening method to the igniter body and the igniter, it is possible to simplify the assembling process by eliminating the need for the assembling ring, the press equipment, and the assembling process according to the conventional assembling method of the assembling ring, Can be remarkably reduced, and the level of the dimensional control of the assembled portion of the igniter body and the igniter can be easily managed, thereby improving the productivity.

Since the assembling ring, which is a component having a relatively large possibility of thermal deformation due to the generation of dimensional deviation and drag reducing flame, is removed due to the application of the screw fastening method as described above, the possibility of deviation of separation force is prevented in advance, As the effect on the flame is prevented, the igniter can be uniformly separated at a uniform pressure, and a plurality of threads are brought into close contact with each other at the time of assembly while excluding the assembly ring, .

As a result, it is possible to effectively reduce the deviation of the rocket propulsion performance and the slip distance deviation by minimizing the difference in the propellant combustion phenomenon by the ammunition as the igniter is uniformly separated.

FIGS. 1 and 2 are views showing a conventional foam ring type carbon material of an assembling ring system,
FIGS. 3 to 5 are views illustrating an embossed carbon ejector according to an embodiment of the present invention,
FIG. 6 and FIG. 7 are views for explaining a separation force deviation of the foam gun type flash projecting body according to the embodiment of the present invention,
FIGS. 8 and 9 are views for explaining the difference in the pressure lines when the rocket propellant is burned due to the separation force deviation of the gun-type carbon eraser according to the embodiment of the present invention.

Advantages and features of embodiments of the present invention and methods of achieving them will become apparent with reference to the embodiments described in detail below with reference to the accompanying drawings. The present invention may, however, be embodied in many different forms and should not be construed as limited to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the invention to those skilled in the art. To fully disclose the scope of the invention to those skilled in the art, and the invention is only defined by the scope of the claims. Like reference numerals refer to like elements throughout the specification.

In the following description of the present invention, a detailed description of known functions and configurations incorporated herein will be omitted when it may make the subject matter of the present invention rather unclear. The following terms are defined in consideration of the functions in the embodiments of the present invention, which may vary depending on the intention of the user, the intention or the custom of the operator. Therefore, the definition should be based on the contents throughout this specification.

Hereinafter, embodiments of the present invention will be described in detail with reference to the accompanying drawings.

FIGS. 3 to 5 are views illustrating a collapsible burnable object according to an embodiment of the present invention. FIGS. 6 and 7 are views for explaining a separation force deviation of a collapsible burnable object according to an embodiment of the present invention. And FIGS. 8 and 9 are views for explaining the difference in pressure line when the rocket propellant is burned due to the separation force deviation of the gun-type carbon launcher according to the embodiment of the present invention.

3 to 9, the foam gun type flash unit according to the embodiment of the present invention includes a body 110, a rocket propelling unit 120, an ignition delay unit 130, a drag reduction unit 140, . Hereinafter, the front end of the foam gun type flash projectile will be referred to as a front end portion, a tan head portion, and the rear end portion thereof will be described as a rear end portion, an anchor portion, and the like.

The bulge portion 110 is coupled with the bulge 112 at the front end and the bullet explosion 114 is filled in the bulge portion 110. A female thread is formed at the front end portion of the bulge portion 110 And a male screw is formed on the rear end (e.g., the rear end outer peripheral surface) of the cantilevered portion 110 by a screw coupling method with the male screw formed on the lower end (e.g., the lower end peripheral surface) Can be coupled with a female screw formed on a front end portion (for example, a front end inner circumferential surface, etc.) of the rocket body 112 of the rocket propelling unit 120 in a screw tightening manner.

Here, the new tube 112 and the cylindrical portion 110 coupled to the new tube 112 may be formed in a streamlined conical shape in order to reduce air resistance.

The rocket propelling unit 120 is provided at the rear end of the cantilever unit 110 so as to be ignited when a predetermined time (for example, 6-10 seconds) elapses after the cantilever is fired. The rocket propelling unit 120 includes a rocket body 122, A rocket propellant 124, and the like.

A disk-shaped auxiliary plate (not shown) may be provided between the rocker propelling unit 120 and the above-described cylindrical portion 110 so as to maintain the engaged state between the two, And a male screw is formed on the outer circumferential surface of the outer circumferential surface of the outer circumferential surface of the outer circumferential surface of the rocker propelling section 120 so as to be coupled to the inner circumference of the rocket propelling section 120 in a screw- The screw assembly can be formed.

A male thread is formed on the rear end of the rocket body 122 of the rocket propelling unit 120 and a front end of the injector body 142 of the drag reducing unit 140 An inner circumferential surface, etc.) with a female screw.

The ignition delay unit 130 is provided at the rear end of the rocket propelling unit 120 to ignite the rocket propelling unit 120 when a certain time (for example, 6-10 seconds, etc.) An igniter body 132, an igniter 134, and the like.

Here, the igniter body 132 is connected to the inner combustion space of the rocket propellant 124 provided at the rocket propelling portion 120, and the rear end portion (the anchor portion direction) 124 is burned, it is blown out through the nozzle and opened to jet toward the jet opening 146, and the igniter 134 can be coupled to the opened portion.

The igniter 134 is provided so that the front end portion (in the direction of the tumbler) is located in the inner combustion space of the rocket propellant 124 through the front end portion of the igniter body 132 so as to ignite the rocket propellant 124, (In the direction of the anvil) can be coupled to the igniter body 132 in a screw tightening manner.

5, an amalgam is formed on the inner surface of the assembled portion of the igniter body 132, and a male screw is formed on the outer surface of the assembled portion of the igniter 134, so that the inside of the igniter body 132 The igniter 134 can be firmly coupled.

Here, the shape of the thread can form various types of threads as well as a triangular screw shape so as to provide the necessary bonding force and separation force, and the corresponding separation force is determined by the pressure level required by the rocket propellant combustion And the thread shape can be formed so as to be separated corresponding to the pressure level.

The pressure of the rocket propellant 124 in the inner combustion space of the rocket propellant 124 is suddenly increased when the rocket propellant 124 is burned up until the igniter 134 is detached from the igniter body 132 And that pressure can act as a force to push the igniter 134 out of the igniter body 132.

In addition, when the inner pressure of the inner combustion space of the rocket propellant 124 becomes equal to or higher than a certain level, the force pushing the igniter 134 from the igniter body 132 becomes a relatively greater force than the separating force (or tightening force) The screw engagement portion of the body 132 is opened in the circumferential outer direction so that the igniter 134 can be separated while being pushed toward the rear end portion (in the direction of the anvil portion).

In addition, even when a screw fastening method is applied, an O-ring made of rubber is additionally provided at an engagement portion of the igniter body 132 and the igniter 134, so that the screw of the igniter body 132 and the igniter 134 It is needless to say that the sealing force according to the fastening method can be supplemented.

The drag reduction unit 140 is provided at the rear end of the rocket propelling unit 120 to reduce the drag generated from the ankle of the flying object to increase the range of the rocket propulsion unit 120 and includes the injector body 142, An ejection opening 146, and the like.

Here, the rocket propulsion unit 120 and the drag reduction unit 140 may be formed in a cylindrical shape, and the injector body 142 may be formed in a boat-tail shape to reduce the drag force .

The cross-section of the drag reducing agent 144 may be provided in a shape that can be injected into the injection port 146 during the combustion. Here, the injection port 146 may be provided at the center of the anisotropic surface of the injector body 142 of the drag reducing section 140.

With reference to FIGS. 6 and 7, a description will be made as to a separation deviation between the gun-type flash unit according to the embodiment of the present invention and the conventional gun-type flash unit according to the present invention, Of the ignition device 134 and the standard deviation of the ignition device 134 from the igniter body 132 through the test firing 10 times with respect to the carbon material projecting body of the assembling ring system of the present invention and the screw- As a result of the measurement, it can be said that the separation phenomenon starts at a point where the igniter 134 is pushed and becomes the maximum load (kgf) due to the inner combustion space pressure of the rocket propellant 124, as shown in FIGS. 6 and 7 It can be seen that not only the maximum load is uniformly measured in the screw fastening method of the present invention but also the standard deviation thereof is relatively low as compared with the conventional assembling ring method And it can be seen that uniform separation performance can be realized in the case of the foam gun type flash material applying the screw fastening method according to the embodiment of the present invention.

8 and 9, the combustion pressure of the rocket propellant (the maximum pressure on the pressure line) is measured uniformly according to the separation force in the case of the screw- And the phenomenon that the combustion pressure is excessively increased does not occur.

As a result, according to the embodiment of the present invention, uniform discharge performance can be achieved in the case of a foam gun type flashgun employing a screw fastening method, and stable combustion of a rocket propellant can be induced.

Accordingly, in the present invention, the separation force (or tightening force) of the igniter during the combustion of the rocket propellant is uniformly applied to the rocket propellant, It is possible to prevent the unexposed portion of the projected object, thereby improving the accuracy of the projected projectile.

In addition, the present invention can maintain the fastening performance and the sealing performance realized in the assembling ring coupling system by assembling the igniter body and the igniter directly by using the screw fastening method without using the assembly ring fastening method which is difficult to provide a uniform separation force The igniter can be uniformly separated from the specific rocket propellant combustion pressure.

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 embodiments, but, on the contrary, It will be readily apparent that such substitutions, modifications, and alterations are possible.

110: Chambers 120: Rocket propulsion unit
130: ignition delay unit 140: drag reduction unit

Claims (4)

A new body, a body part with high explosives,
A rocket propulsion unit including a rocket body and a rocket propellant,
An ignition delay unit provided at a rear end of the rocket propulsion unit including an igniter body and an igniter and igniting the rocket propulsion unit to be ignited when a lapse of a predetermined time after the fireball is fired;
And a drag reduction unit provided at a rear end of the rocket propulsion unit to reduce a drag force generated from an ankle of the rocket propulsion unit to increase a range,
Wherein the igniter body and the igniter are coupled by a screw fastening method.
The method according to claim 1,
Wherein the new tube and the trunk are each formed in a streamlined conical shape.
The method according to claim 1,
Wherein the elastic body and the rocket propelling unit are provided with a disk-shaped auxiliary plate so as to maintain a state of engagement between the two bodies.
4. The method according to any one of claims 1 to 3,
Wherein the igniter body and the igniter have an O-ring made of a rubber material at a joint portion to complement a sealing force.

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