RU2291376C1 - Rocket - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the rocket has an elongated with a nose fuze, including a body with a spherical head filled with a fluid detonating mixture and a cross diaphragm fastened on it, axial detonator and a jet solid-propellant engine. The rocket is provided with carrier shells and a disk membrane made of a set of leaf springs aligned on the screening cap of the axial detonator lug provided with a propellant charge, an ignition pyrotechnical composition is coaxially positioned inside the propellant charge. The elongated warhead with the nose fuze is installed on one of the shells, and the spherical head resting on the disk membrane is fastened on the other shell. The spherical head is made thin-walled and filled with a condensed explosive. From the inside the body is made channeled.

EFFECT: enhanced power of the rocket.

2 cl, 4 dwg

Description

The invention relates to ammunition, and more particularly to aircraft missiles 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 patent RU 2219481, F 42 B 12/20, 2003, containing a thin-walled corrugated housing, fluid flow filling, which is a detonation-free suspension of metal powder in a combustible liquid, where an axial detonator is mounted, the shell of which equipped with crushing concentrators made in the form of intersecting grooves.

In this munition, the geometrical ratios of the propellant charge of the detonator and the fragmentation shell are optimized, as well as the density of the combustible suspension of the filling dispersed upon rupture of the shell for maximum efficiency of volume detonation of the aerosol cloud formed in this case, which is many times larger than the caliber of the munition.

The striking high-explosive action of the described ammunition is determined by the formation of a powerful shock wave during volume detonation of the resulting aerosol cloud of a fuel-air mixture from a liquid-fuel combustible filling of the body dispersed by a propellant charge.

However, the disadvantage of this munition is the irrational axial dispersion of the propelling impulse and the unsatisfactory fragmentation effect, since the shell of the high-explosive munition, even in the presence of destruction concentrators in the form of a mesh of grooves, has to be made thin-walled.

The expansion speed of the fragments generated during crushing of the body of shells, thrown by the energy of the axial detonator through a mass of viscous filling, is low, which determines an insignificant slaughter distance.

In addition, fragmentation in the direction of flight of the ammunition to the target is practically absent, since the expansion of the damaging elements occurs radially.

The noted disadvantages are eliminated in the rocket described in patent RU 2156953, F 42 B 12/20, 2000, selected by the technical nature and the number of matching features as the closest analogue of the proposed rocket, which contains an elongated warhead mounted on a supporting shell with fuse head and solid-fuel jet engine.

The warhead of a missile includes a powder filled with a fluid detonating mixture of metal (aluminum, magnesium or a mixture of them) with a combustible liquid, an internal corrugated housing having a spherical head, an axial detonator with a propelling charge and a transverse diaphragm mounted on the housing.

The transverse diaphragm, permeable to fluid flow, is an additional support for the elongated warhead, increasing its structural strength, and serves as a reflector of the shock wave that occurs when initiating a propelling charge of the axial detonator, which is sent to destroy the centering belt of the housing located in front of the reflector.

The centering thickening of the shell increases the rigidity of the shell of the ammunition and its fragmentation mass.

The placement of the shock wave reflector in the form of a transverse diaphragm in the body filling behind the centering bulge is aimed at increasing the number of slaughter fragments formed at a given crushing, since as a result of applying the pressure of the shock wave reflected from the diaphragm to the pressure from the direct wave during detonation of the propelling charge, the deformation of the body increases its embrittlement and crushing of the centering thickening material.

The diaphragm windows create a pressure gradient in the radial direction of the housing, which also contributes to the fragmentation of the centering thickening.

The spherical shape of the head of the munition improves its aerodynamic characteristics and ballistics, when crushed, a beam of fragments is formed, directed along the axis of the munition toward the target, which increases the damaging fragmentation effect.

However, a continuation of these advantages is an inherent disadvantage, which is expressed in the unsatisfactory fragmentation effect of the volume-detonating munition.

High-explosive ordnance, by definition, has a thin-walled casing, which does not allow for the formation of damaging elements with its given crushing with a shape coefficient close to unity, so plate-like fragments are obtained that fly apart and are quickly decelerated in the air. In addition, fragments formed during crushing of the body receive a low initial speed, since their throwing is carried out by means of fluid flow.

In addition, the central axial initiation of the aerosol cloud formed during the detonation of the warhead, the air-fuel mixture, including heated metal powder dispersed into the atmosphere, does not provide detonation at once in its entire volume, which significantly reduces the effectiveness of the munition in terms of thermobaric damaging effect, the main destination.

The problem to which the present invention is directed is to increase the power of the proposed warhead of an aircraft missile due to structural improvements of the ammunition to provide a pronounced fragmentation damaging effect in addition to the main thermobaric, more powerful one.

The required technical result is achieved by the fact that in a known rocket containing an elongated warhead mounted on a carrier shell with a head fuse and a solid rocket engine, the warhead includes a detonation-capable mixture of metal powder with combustible liquid filled with a fluid flow, an internal corrugated body having a spherical head , axial detonator with a propelling charge and a transverse diaphragm mounted on the housing, according to the invention, the spherical head is made thick it is filled with condensed explosive and mounted on an additional supporting shell, relying on a disk membrane made of a set of leaf springs centered on the shield cap of the axial detonator protrusion, inside the propellant charge of which an igniter pyrotechnic composition is coaxially placed, while the supporting membrane is installed in the supporting shell with the formation of a damping chamber, and a central communication window is made in the shielding cap.

Distinctive features provided an increase in basic technical characteristics, that is, indicators of the purpose of the warhead of an aircraft missile, namely: fragmentation and high-explosive (thermobaric) damaging effect.

At the same time, the proposed warhead is a constructive unity of functionally different structural components: the high-explosive section itself with a thin-walled body having fluid flow and a thick-walled spherical head filled with condensed explosive.

For a given crushing of a thick-walled shell of a spherical head, having spiral multi-way corrugations of the opposite direction from inside, forming a grid of semi-finished fragments, aerodynamic-shaped striking elements are formed in the form of a kinetic beam directed towards the target along the flight path of the rocket.

The condensed explosive of the spherical head as a propellant charge of the striking elements, the predetermined formation of which is provided by the crushing concentrators along the riffles, gives the compact fragments a multiple higher initial velocity with an increase in the slaughter interval.

In addition, the equipment of the warhead with condensed explosives is much more technologically advanced than liquid, pasty.

Strengthening the spherical head on an additional supporting shell creates a constructive and functional separation of both sections of the warhead, while increasing its longitudinal stiffness and bearing capacity. The bearing shells form an autonomous high-explosive section, in the high-explosive section they serve as reflectors of shock waves that occur when the axial detonator is triggered, to localize the destructive pulse inside the section, directing it to crush the corrugated body.

Placing a spherical head on a bearing shell through a disk membrane ensures the transmission of axial load from the shock wave during detonation of its filling directly to the shell of the high-explosive section. This distributed load, transmitted through the ends of the thin-walled housing of the high-explosive section, together with the counter-action of the inertial pressing mass of the rocket engine, compresses the housing longitudinally on both sides, which at the same time radially deforms into a barrel-shaped shape until fluid flow is initiated.

Preliminary mechanical loading of a thin-walled corrugated casing leads to cracking in the directions specified by spiral grooves, which significantly reduces the efforts required to crush it and reduces the loss of propellant high explosive charge.

The implementation of the disk membrane from a set of leaf springs clamped around the periphery, which are elastically deformed counter in compression-tension mode, allows you to dampen the action of the shock wave in the longitudinal direction to fill the high-explosive section, preventing its premature initiation.

The shielding cap on the protrusion of the axial detonator of the high-explosive section located inside the spherical head prevents the action of detonation of the condensed explosive through the influence on the propellant charge of fluid flow.

The detonation pulse from the condensed explosive is transmitted to the propellant charge of the axial detonator directly, through the communication window of the shielding cap, which ensures the functional unity of the sections of the warhead during their autonomous sequential action after a predetermined delay time.

The screened protrusion of the detonator and the fastening of the spherical head on the dividing bearing shell through the plate shock absorber form a time delay for the filling of the high-explosive section to operate, which is necessary for preliminary mechanical loading and deformation of its thin-walled body.

The damping air chamber between the spring disk membrane and the bearing dividing shell serves as the interface and serves to dampen the shock wave reflected from the shell.

Equipping the propellant charge of the axial detonator with an igniter pyrotechnic composition is aimed at creating numerous point centers of initiation in an aerosol cloud from a metal powder of fluid flow filling, which detonates in the volume at once, significantly increasing the thermobaric damaging effect of the munition.

Therefore, each essential feature is necessary, and their combination is sufficient to achieve a novelty of quality that is not inherent in the signs of disunity, that is, the technical problem posed in the invention is solved not by the sum of the effects, but by a new super-effect of the sum of the essential features.

The invention is illustrated by the drawing, which serves a purely illustrative purpose and does not limit the scope of the claims of the formula, and where are shown:

figure 1 - General view of the rocket;

figure 2 is a view of figure 1;

figure 3 is a view of B in figure 1;

figure 4 is a cross section of the shell of the shell of the warhead.

The missile contains a two-section elongated warhead mounted on the carrier shell 1 and a jet engine 2, equipped with a leading belt 3 and blade means 4 for longitudinal stabilization on the flight path to the target.

The warhead includes a head fuse 5 mounted in a spherical shape with a thick-walled head 6 filled with condensed explosive 7.

The spherical head 6 is fixed in the bearing shell 8 and rests on a disk membrane 9.

On the opposite side, a high-explosive section of the warhead is adjacent to the shell 8, a thin-walled body 10 of which is fixed at the ends to its bearing shells 8 and 1.

The shell 1 is equipped with a sealed cover 11 of the filling technological window, through which the filling of the housing 10.

The membrane 9 is a set (figure 2) of disk leaf springs 12, clamped around the perimeter by a head 6 in the shell 8. The disk membrane 9 is installed in the shell 8 with an annular gap forming a damping chamber 13, and is centered on the shielding cap 14, which is mounted on protrusion of the axial detonator 15.

In the shielding cap 16 there is a central through window 16 for communication of the filling 7 of the head 6 and the propellant charge 17 of the detonator 15, placed coaxially with the housing 10 of the high explosive section, where it is mounted on a transverse diaphragm 18 connected with the housing 10 and provided with windows 19 (Fig. 1). The diaphragm 18 is rigidly connected with the housing 10 and represents an additional supporting support of the elongated warhead.

Inside the propellant charge 17 of the detonator 15, an igniter pyrotechnic composition 20 is axially placed.

The housing 10 is filled with a suspension of metal powder in liquid fuel, which form a liquid flowing detonation-filling filling 21, poured into the housing 10 in the position of the warhead with the spherical head 6 down on the vibration-impact technological installation, with the cover 11 of the shell 1 open.

When the high-explosive section is equipped, the mixture 21 through the windows 19 of the diaphragm 18 enters the volume between the detonator 15 and the body 10, filling the latter, after which the cover 11 is tightly screwed into the shell 1.

The shell of the spherical head 6 and the housing 10 of the high-explosive section from the inside are made with intersecting multi-helical spiral corrugations 22 (Fig. 3) of a triangular profile (Fig. 4) with an angle at the apex of 60 degrees, forming a grid of semi-finished fragments 23. On this, the step and depth the corrugations 22 on the shell of the spherical head 6 and the housing 10 are different and the conditions for the formation of the striking elements weighing 2.3-2.6 g of compact and lamellar shape, respectively, are selected.

The corrugations 22 are formed in two reduction operations on a spiral mandrel by alternately pulling the tubular workpiece through the calibration matrices on both sides. When the tool holder is fed back, the processed semi-finished product is screwed up along the formed spiral corrugations 22, which are inclined to the longitudinal axis at an angle of 30 degrees for this purpose.

The semi-finished product of the head 6 after reduction operations, with the spiral intersecting grooves 22 applied, is crimped in a die tool, forming its spherical profile.

The ammunition operates as follows.

The pulse of the detonated fuse 5 initiates filling 7 of the head 6, the thick-walled shell of which is evenly crushed along the concentrators - flutes 22 with the formation of compact striking elements 23 of a rhombic shape, dense beam oriented along the flight path of the rocket toward the target.

The shock wave arising from the detonation of the condensed explosive 7 is peripherally transmitted to the adjacent building 10 of the high-explosive section. In this case, the shock wave is almost completely damped in the membrane 9, the adjacent leaf springs clamped around the perimeter of which, compressing and stretching in antiphase, mutually compensate for the deformations arising under axial loading.

In the chamber 13, the transmitted part of the shock pulse is reflected from the shell 8 and completely extinguished in the membrane 9.

Thus, the shock wave practically does not affect the filling 21 of the housing 10, which itself perceives the action of the shock wave directly, through contact with the shell of the spherical head 6.

From longitudinal loading by the shock wave, the housing 10 is deformed radially, despite the fact that it experiences counter inertial loading through the shell 1 by the mass of the jet engine 2.

The radial component of the compressive load "inflates" the thin-walled cylindrical body 10 clamped at the ends, which takes a barrel-shaped shape, which expands the expansion angle of the filling 21 dispersed by the propellant charge 17 and fragments formed during detonation crushing of the body 10. As a result of dynamic deformation of the housing 10, cracking occurs along the corrugation 22.

By this time, the detonation pulse through the window 16 of the cap 14 initiates a propelling charge 17 of the axial detonator 15, which affects the filling 21 of the housing 10.

The constructive organization of a temporary slowdown in the transfer of a detonation pulse from a condensed explosive 7 to a propellant charge 17 of the axial detonator 15 provides dynamic interaction between both autonomous sections of the warhead in a predetermined response sequence, thereby enhancing the damaging factor of a single ammunition.

The necessary delay time is provided by the size of the damping chamber 13 and the size of the communication window 16 of the shielding cap 14.

When initiating a propellant-incendiary charge (17, 20) of the axial detonator 15 with detonation products, the filling 21 of the housing 10 is elastically compressed in the radial direction, as a result of which the plastic housing 10 is loaded, it is embrittlement in the places of stress concentrators along the flutes 22, and uniform destruction on shards 23.

The liquid component of the filling 21, burning in the deflagration mode upon detonation of the propellant charge 17, heats the metal powder dispersed at the same time, which ensures the completeness of combustion of the filling 21 and increases the sensitivity of the detonation-sensitive aerosol formed in the atmosphere.

Under the action of expanding detonation products, finely dispersed spraying of filling 21 occurs with interspersed dispersed particles of pyrotechnic composition 17 of detonator 15, which, mixed with atmospheric air, form an aerosol cloud, a detonative fuel-air mixture.

The red-hot fragments of a fragmented pyrotechnic igniter composition 20, distributed in an aerosol cloud, form numerous foci of initiation of a fuel-air mixture, which ignites when a sufficient oxygen concentration is reached.

The air-fuel mixture detonates in volume, creating a shock wave of enormous destructive force and producing a thermobaric damaging effect.

Thus, the warhead in the proposed aircraft missile is characterized by a complex destructive action of increased power, both high-explosive (thermobaric), and additionally fragmentation, aimed at the target beam of compact striking elements.

A comparative analysis of the proposed technical solution with identified analogues of the prior art, from which the invention does not explicitly follow for an ammunition specialist, showed that it is unknown, and given the possibility of industrial serial production of missiles with a two-section warhead of increased power, we can conclude that patentability criteria.

Claims (2)

1. A missile containing an elongated warhead with a head fuse, including a body filled with a fluid detonating mixture with a spherical head and a transverse diaphragm mounted on it, an axial detonator and a solid propellant rocket engine, characterized in that it is equipped with bearing shells and a disk membrane made of a set of leaf springs centered on the shielding cap of the protrusion of an axial detonator equipped with a propelling charge, inside of which an axially placed ignition Yelnia pyrotechnic composition, wherein one of the elongated shells mounted warhead fuze with the head, while the other spherical head is fixed, based on disk membrane, the spherical head is formed and filled with a thick-walled fused explosive and the housing inside is formed with embossed. 2. The rocket according to claim 1, characterized in that the disk membrane is mounted on the carrier shell with the formation of a damping chamber, and a central communication window is made in the shielding cap.

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