RU2286531C1 - Jet projectile - Google Patents

Abstract

FIELD: ammunition with a high-explosive fragmentation warhead.

SUBSTANCE: the projectile has a solid-propellant engine and an elongated warhead with a nose fuse interconnected by a bearing shell, an axial detonator provided with a cross diaphragm is installed in a channeled body that is closed with a bottom cover and filled with a detonable mixture. An expansion chamber is formed in the bottom part of the body made with an ogival nose section, it is formed by means of a filling skirt on the bearing shell, and an ignition pyrotechnical charge is coaxially installed in the axial detonator fastened on the cross diaphragm through a set of plates.

EFFECT: enhanced power of the projectile.

3 cl, 5 dwg

Description

The invention relates to ammunition, and more particularly to rockets with a high-explosive fragmentation warhead, the shell of which has grooves for uniform crushing into fragments, which is volume-detonating.

The level of this technical field is characterized by the volume-detonating munition described in US Pat. No. 3,995,550, F 42 B 13/14, 1976, which contains a thin-walled housing, a fluid flowing combustible filler with a central propellant charge placed in the shell of a detonator equipped with a foam damping insert.

The striking high-explosive action of this munition is determined by the formation of a powerful shock wave during the detonation of a cloud of fuel-air mixture from a liquid-fuel combustible filling dispersed by a propellant charge.

The disadvantage of the described ammunition is the low fragmentation effect on durable protected targets, since small fragments are formed when the thin-walled case is crushed.

To increase the effectiveness of the fragmentation damaging effect of ammunition on the inner surface of the hull, a grid of semi-finished striking elements is performed by intersecting grooves (corrugations), weakening the wall for its predetermined fragmentation and organization of directional expansion of fragments having the necessary mass and configuration, ensuring the defeat of targets easily protected by obstacles (see for example, US 6,484,642, F 42 B 12/22, 2002).

An ammunition in which both of the above technical solutions are combined is presented in the invention according to the patent RU 2219481, F 42 B 12/20, 2002, which comprises a body with a liquid flowing filler (detonation-sensitive mixture) and a central shell with a propelling charge initiated by a head fuse, while on the inner surface of the body formed by corrugations distributed semi-finished striking elements.

In this munition, the geometric ratios of the propellant charge and the fragmentation shell of the projectile are optimized, as well as the density of the combustible mixture dispersed during the explosion for maximum efficiency of volumetric detonation of the filling.

The disadvantage of the described ammunition is the unsatisfactory effectiveness of the main action, firstly, due to the axial loss of part of the energy of the explosion of the propellant charge, which is transmitted to the ballast jet for the damaging effect, and secondly, irregular crushing of the shell, as a result of which conglomerates of several semi-finished fragments and longitudinal elongated (saber) fragments.

The latter circumstance is the cause of local jet emissions of fluid filling, which does not completely burn out and detonate, distorting the shape of the aerosol cloud of the detonation-fuel-air mixture, and massive irregular fragments are quickly decelerated in the air.

The noted disadvantages are eliminated in the rocket projectile according to the patent RU 2156953, F 42 B 12/20, 14/00, 2000, which by most of the matching features is selected as the closest analogue to the proposed one.

The known missile contains an interconnected engine shell and an elongated warhead with a fuse, in the corrugated inside of which is filled with a detonation mixture, an axial detonator is installed, equipped with a transverse diaphragm of the shock wave, the housing being screwed into the technological bottom hole the lid.

The fluid flowing combustible filling composition is a suspension of aluminum powder in a combustible liquid, which with a strong film is adhesively bonded to the powder particles, forming a detonation mixture. Particles of this filling composition do not stick together during storage and pulsed loading during an explosion.

The transverse diaphragm, through the windows of which a shock wave is transmitted along the charge of the charge, located behind the axial detonator, reflects the direct shock wave generated during detonation of the propellant charge, as a result of which the body experiences an increased stepwise deformation upon application of these waves, becomes brittle and crushed (see F. A. Baum et al. Explosion Physics, Vol. 2, revised, M., Nauka, 1975).

However, the known ammunition has the following disadvantages arising from the design.

It is difficult to objectively visually control the filling of the housing with a combustible mixture, while there is no guarantee that a technologically free volume is not formed for the thermal expansion of the fluid flowing filling mixture at an operating temperature of up to plus 60 degrees C.

As a result of possible thermal deformation of the threaded connections of the case with the screw cap and the bearing shell, the leak is broken, and as a result, the filling leakage, which is unsafe in general for the volley fire system and is unacceptable.

The head part of a spherical fragmentation shell directing the shock wave along the charge along the shell leads to aerodynamic drag of the projectile in flight and to a narrowly focused beam of damaging elements, which noticeably reduces the total fragmentation field.

The cantilever mounting of the detonator under transverse dynamic loading during transportation is unsatisfactory in reliability.

The high-explosive effect of the ammunition is reduced due to the almost instantaneous detonation of the combustible filling mixture during crushing of the shell by the energy of the propellant charge from the center.

The ignition of the aerosol in the cloud of the dispersion of the filling of the warhead body occurs due to the hot products of the propellant charge, which are rapidly cooled in air, therefore, the proton volume detonation is characterized by incomplete combustion of the detonation-friendly mixture at the periphery, which reduces the efficiency of the thermobaric projectile damage.

The problem to which the present invention is directed is to eliminate the noted drawbacks in order to increase the functional reliability and effectiveness of the complex damaging effect of the munition.

The required technical result is achieved by the fact that in the known rocket containing a solid-fuel engine coupled to each other with a supporting shell and an elongated warhead with a fuse, in the corrugated inside of which, closed by a bottom cover and filled with a detonation-friendly mixture, an axial detonator equipped with a transverse diaphragm is installed, according to the invention, an expansion chamber is formed in the bottom of the housing made with the ogival head part by means of a refueling skirt on a real shell, and in an axial detonator mounted on a diaphragm through a set of plates, an igniter pyrotechnic charge is coaxially installed, while the triangular profile corrugations, with an angle at an apex of 60 degrees, are made on the inner surface of the body in the form of intersecting multi-helixes, forming a grid of semi-finished striking elements , the material of which is reinforced around the perimeter by the forming plastic deformation of the reduction of the shell of the housing on the central tool holder, and to the refueling ortsu bearing shell adjacent caul vvintnoy cover housing with flowable content.

Distinctive design features provided the ammunition with the maximum possible increase in the damaging effect of a high-explosive and fragmentation fragment, including due to the technology of shaping by reduction of semi-finished striking elements on the shell of the shell.

The implementation of the head part of the body of an elongated reactive projectile of a lively form improves the aerodynamic characteristics of the product, which contribute to increasing the flight range when forming a given fragmentation field with an optimal declination angle of expansion of the striking elements.

An expansion chamber in the bottom of the casing, formed by a filling skirt on the supporting shell, is guaranteed to remain free from the filling mixture, which equips the casing in a vertical position. At the same time, the skirt serves as a visual technological measure of filling the body with a liquid flowing combustible mixture, which simplifies this labor-intensive operation carried out on a vibro-shock installation.

The estimated free volume of the expansion chamber of the housing provides thermal expansion of the filling composition without deformation of the connecting nodes of the projectile elements in the entire temperature range of the product.

The implementation of the bottom cover in the form of a screw seal in the filling window of the bearing shell provides reliable isolation of the volume of the shell of the shell filled with a fluid suspension of a detonation mixture during storage and operation.

Attaching an axial detonator to the transverse diaphragm increases the rigidity of the structure and the reliability of the projectile.

The rigid fixed position of the axial detonator on the transverse diaphragm relative to the structural elements of the warhead ensures the formation of a symmetrical fragmentation field and a cloud of the fuel-air mixture of the correct form, in which pyrotechnic igniter charge fragments are the initiators of volumetric detonation of dispersed projectile filling.

The coaxial placement of an igniter pyrotechnic charge inside the detonator ensures its dispersion in the form of numerous localized foci of initiating volumetric detonation of the fuel-air mixture of the formed aerosol cloud, which exceeds the projectile caliber by 80-150 times.

Burning in the deflagration mode during the detonation of the propellant charge, the liquid component of the projectile filling heats the metal powder dispersible at the same time, which ensures the completeness of combustion of the filling and increases the sensitivity of the detonation-sensitive aerosol.

Volumetric detonation of the fuel-air mixture of an aerosol cloud forms a sharp shock wave, which has a high explosive effect, carrying out thermobaric damage.

In the event of a projectile firing in an enclosed volume of buildings, structures, military equipment, structural load-bearing elements destroyed by a shock wave are additionally affected by an oncoming wave of collapse from the vacuum created by the explosion inside the aerosol cloud, which completes the destruction and defeat of the baric nature.

The set of plates at the end of the axial detonator serves to compensate for technological gaps when setting the predetermined distance of the head fuse to the axial detonator, and also dampens the mechanical effect of the shock wave on the diaphragm.

The plates in the shock absorber set are characterized in that they are made of alternating different elastic and plastic materials to compensate for the destructive action of the shock wave at the interfaces and damping of the reflected wave inside, respectively.

A high-tech method of press forming a grid of semi-finished striking elements with hardening of the material along their perimeter organizes a given crushing of the body into aerodynamic fragments.

The triangular cross-section of screw grooves (grooves), with an angle at the apex of 60 degrees, is optimal under friction conditions for automatically screwing tool holders, and also minimizes the energy costs of crushing the shell by means of the so-called gas wedge formed in these grooves for plastic shearing of its metal, ensuring the adequacy of the division of the body into fragments according to the technological formation of localizers of destructive deformations.

The formation of a grid of semi-finished striking elements by intersecting multi-helical spiral grooves that are inclined to the longitudinal texture of the material of the tubular body ensures its uniform crushing under radial loading with propellant charge energy, as a result of which the maximum speed of the striking elements and equal fragmentation field density are achieved.

Consequently, each essential feature is necessary, and their combination is sufficient to achieve the novelty of quality in the form of the effect of the sum of features that are not inherent in their disunity.

A comparative analysis of the proposed technical solution with the identified analogues of the prior art, from which the invention does not explicitly follow for an ammunition specialist, showed that it is not known, and taking into account the possibility of industrial serial production of missile shells, we can conclude that the patentability criteria are met.

The essence of the invention is illustrated by the drawing, which has purely illustrative purposes and does not limit the scope of the claims of the formula and where is schematically depicted:

figure 1 - General view of the projectile;

figure 2 is a view a in figure 1, is rotated to the filling position of the filling;

figure 3 is a section along BB in figure 2;

figure 4 is a view In figure 1;

figure 5 is a section along G-D in figure 4.

A rocket for a multiple launch rocket system includes an elongated warhead 1 and a solid fuel engine 2, rigidly interconnected by an adapter 3.

The fragmentation case 4 of the warhead 1 is mounted in the bearing head sleeve 5 and the bottom shell 6. In the sleeve 5, coupled with the animated part of the case 4, a fuse 7 and a thin-walled shell 8 of the axial detonator 9 are installed, which performs the function of a propellant charge.

The shell 8 of the detonator 9 is mounted on the transverse diaphragm 10 with the windows 11 (figure 3). Axial detonator 9 to the diaphragm 10 is adjacent through a set of plates 12.

Inside the detonator 9, a igniter charge 13 of a slowly burning pyrotechnic composition is coaxially mounted.

Between the housing 4 of the warhead 1 and the thin-walled shell 8 of the detonator 9, a detonation filling 14 is placed, which is a fluid fuel mixture in the form of a suspension of metal powder, in particular a mixture of aluminum and magnesium powders, in a combustible liquid, forming a strong adhesive film on the powder particles. The consistency of the filling 14 provides the simentational stability of the mixture.

The filling 14 is equipped on a vibro-shock installation with the vertical position of the housing 4 with its head oriented downward (FIG. 2) through the open filling center hole of the shell 6 equipped with the skirt 15. The fluid flow filling 14 through the windows 11 of the diaphragm 10 fills the annular volume between the housing 4 and the shell 8 an axial detonator 9, and then the bottom of the warhead 1 behind the diaphragm 10. In this case, a free volume is technologically formed in the housing 4 at the level of the refueling skirt 15, which forms an expansion annular chamber 16.

The level of filling 14, equipped through the filling hole of the shell 6, is located above the formed chamber 16 and is visually controlled by the technological mark on the skirt 15, which simplifies the time-consuming process and the design of the sealed equipment unit.

The presence of the camera 16 technologically ensures the normative filling of the volume of the housing 4 by 95%.

After the casing 4 is equipped with a filling 14, a cover 17 is screwed into the central hole of the shell 6 through the gland 18, reliably isolating the volume of the casing 4 with the filling 14.

On the inner surface of the housing 4 there is a grid of semi-finished fragments 19 (Fig. 4) formed by multi-helical spiral grooves 20 (Fig. 5) of a triangular profile with an angle at the apex of 60 degrees and a depth of 1 / 4-1 / 3 of the wall thickness of the housing 4, inclined to the axis of the warhead 1 at an angle of 30-45 degrees.

The corrugations 20 are formed by reducing the tubular billet of the housing 4 to a multiple helical mandrel in two operations of counter-pulling through the calibration matrix. Moreover, due to the hardening of the metal of the casing 4 during plastic deformation during the reduction operation, the strength of the striking elements 19 along the periphery significantly increases, which, together with the weakening of the cross section of the casing 4 along the flutes 20, determines the crushing structure when it is radially plastic loaded with detonation products of the propellant through filling 14.

The lively head part of the housing 4 is obtained by crimping in die tooling.

The ammunition operates as follows. When the head fuse 7 is triggered, a propellant-incendiary charge of the detonator 9 is initiated, which destroys its shell 8 and causes elastic compression by the detonation products of the powder suspension of the filling 14.

At the same time, a shock pulse is formed in filling 14, and then with a noticeable delay - a detonation front, as a result of which plastic body 4 is loaded, embrittled in places of stress concentrators (along riffles 20) and uniformly breaks into aerodynamic rhombic fragments 19.

Under the action of expanding detonation products, a fine finely dispersed filling 14 is sprayed, which, mixing with atmospheric air, forms a suspension - a detonation-friendly cloud of a fuel-air mixture.

The shock front provides heating of the components of the filling mixture 14 during the combustion of the liquid fuel component and the occurrence of cavitation processes on the wetted surface of particles of metal powder, which is chemically activated.

The shock front causes the mixture 14 to compact and the housing 4 to swell with the beginning of the formation of damaging elements 19 along the corrugations 20, which eliminates finer crushing under the action of the detonation front, which destroys the thin-walled shell 8, ignites the charge 13 and pressures the filler 14, elastically compressing the particles of metal powder.

The shock front through the windows 11 of the transverse partition 10 extends along the filling 14 into the bottom of the warhead 1, and in the plates 12 it is elastically damped, which prevents the premature destruction of the diaphragm 10.

The shock pulse is reflected stepwise from the diaphragm 10 and is transmitted through the housing 4 in the opposite direction, enhancing the deformation effect of embrittlement of the material. Due to the fact that the corrugations 20 are directed at an angle to the metal texture, the tubular body 4 expands plastic without destruction, which ensures the accumulation of elastic deformation energy in the fluid mixture of the filling 14.

At the first moment of detonation, the fuel mixture of the filling 14 is compressed, being compressed on the body 4 of the warhead 1. At the same time, solid particles of metal powder do not stick together, because a combustible liquid is adhered firmly to their surface.

On the inner surface of the casing 4, a composite gas-permeable shell of compacted filling 14 is formed, which, when crushing the casing 4 along the weakened corrugations 20 by the energy of the explosion of the propellant charge of the detonator 9, is dynamically dispersed into the atmosphere in the form of a cloud of numerous solid metal powder particles heated by the burnt liquid filling component 14.

Passing radially through the gas-permeable filling layer 14, the detonation pulse from the detonator 9 destroys the housing 4 along the corrugations 20, forming striking fragmentation elements 19 of a given configuration, which fly apart over a distance significantly exceeding the zone of thermobaric damage.

The red-hot fragments of the fragmented pyrotechnic composition of the igniter charge 13, distributed in the filling 14, scatter together, forming numerous foci of initiation of the fuel-air mixture, which ignites when a sufficient oxygen concentration is reached.

In this case, the detonation of the aerosol does not occur from the center, as in the prototype, but in the volume of the formed cloud, in which the missile filling 14 of the warhead 1 is completely burned.

The acceleration and formation of the fragments 19 is due to the arrival of the detonation front to the expanding body 4. Multiple loading of the body 4 with a series of shock-wave pulses and a detonation wave, realized under the action of the proposed design of the munition, provides an increase in the speed of throwing fragments 19.

It should be noted that in the proposed ammunition, which has an increased thickness of the fragmentation shell 4 of the warhead 1, the explosion energy is not spent on its destruction, since the shell 4 is weakened from the inside by a third to a quarter of the thickness of the grid of the corrugations 20, which are the centers of destructive stresses. The fragments 19 formed during organized crushing of the body 4 have predetermined mass and size characteristics.

The almost simultaneous destruction of all the corrugations 20 creates the conditions for a symmetrical and distributed expansion of the filling 14 in the atmosphere, forming an aerosol of heated particles of the metal powder.

The radial expansion of suspended particles of filling 14 is 12–15 times larger than axial, therefore, an excess of the length of warhead 1 over its caliber by 6–10 times allows one to relatively align the configuration of the formed aerosol cloud and the reduced area of thermobaric damage.

Volumetric detonation of dispersed in the atmosphere of the filling 14 creates a destructive force shock wave of the gaseous medium.

The accumulation of explosion energy during compaction of the filling mixture on the corrugated warhead body and the volume ignition of a detonation-capable aerosol cloud with a deceleration sufficient to maximize dispersed expansion of the filling in the atmosphere under the influence of the axial detonator propellant charge increase the fragmentation and thermobaric damage zones.

Claims (3)

1. A missile containing a solid-fuel engine interconnected by a bearing shell and an elongated warhead with a head fuse and with a head and bottom parts, in the corrugated case of which, closed by the bottom cover and filled with detonation-filling, an axial detonator and a transverse diaphragm are installed, characterized in that that the head of the hull is made animated, in the bottom of the hull an expansion chamber is formed by means of a refueling skirt made on the bearing shell, and an axial detonator fixed through a set of plates on the transverse diaphragm, while an igniter pyrotechnic charge is coaxially installed in the axial detonator. 2. The projectile according to claim 1, characterized in that the corrugations are made of a triangular profile with an angle at a vertex of 60 ° on the inner surface of the body in the form of intersecting multi-helixes forming a grid of semi-finished striking elements, the material of which is reinforced around the perimeter by a forming plastic deformation of the body reduction on the central tool holder. 3. The projectile according to claim 1, characterized in that the bottom cover is screwed into the opening of the bearing shell through the gland, and the detonation filling is a fluid fuel mixture.

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