RU2357200C2 - Missile - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention concerns military equipment, particularly missiles and jet missiles of fuel/air explosive effect. Missile includes payload with detonating charge placed in case, bottom fuse and firing explosive charge positioned in tubular case. Fuel/air explosive charge features liquid components, and payload case is elongated. Front payload end at propulsion motor side is closed by cover on cap shape mounted in payload case with concave side oriented towards fuel/air explosive charge. Seam sealing elements in the form of rubber rings in annular grooves on cover are positioned between cover and payload case. Annular lug is made at inner surface of payload case around cover in sealing element location, and cover features through axial orifice for cover installation onto bottom fuse and firing explosive charge case. External surface of bottom fuse and firing explosive charge features annular lug, and cover rests against the lug and is tightened rigidly to it by nut screwed to bottom fuse and firing explosive charge case. Firing explosive charge is tightened to annular lug of the tube in front of bottom fuse at propulsion motor side by nut screwed into its case.

EFFECT: high efficiency and sensitivity of actuated fuel/air explosive charge.

3 dwg

Description

The invention relates to military equipment, namely to missiles and rockets, mainly controlled by anti-tank, equipped with space-detonating warheads.

The well-known "guided projectile" (see patent RU No. 2125230, IPC F42B 15/00, publ. 01.20.1999), selected as an analogue. In a guided projectile, the cumulative warhead occupies an intermediate position between the head compartment containing the head fairing with a steering gear and the leading cumulative charge and ending with a marching jet engine with an axial through channel for the passage of the cumulative jet of the main warhead smoothly interfaced with a recess in the rear engine march and a tail compartment, which includes, as a rule, a starting jet engine, tail unit and a number of other structural elements necessary for control trolled projectile and fired at targets in a given mode.

The disadvantage of the analogue is that with an intermediate arrangement of the volume-detonating charge (DLD) in such a projectile, the head compartment will screen the damaging factors of the DLD, i.e. reduce its brisant and high-impact directly on the target.

A known method of generating control signals of a rotating munition roll and a method for its manufacture (see patent RU No. 2235284, IPC F42B 15/00, published on 08.27.2004), selected as an analogue.

The missile consists of a head compartment ending with a marching jet engine with a through axial channel smoothly interfaced with a recess in the rear bottom of the marching jet engine, a warhead with a hull, a special detachment, including liquid components, a bottom fuse and an ignition-burst charge installed in the central cup, recessed in a special-purpose cylinder and fastened to the bottom of the warhead’s hull, a starting jet engine and the communications of the warhead with neighboring compartments in the form of hollow cylinders. Marching and starting jet engines form the generators of vibration-wave effects on the ODZ. The glass, ground fuse, ignition-explosive charge and the bottom of the warhead hull form a generator of shock-wave impacts on the DDZ, as well as a waveguide-cavitator for it. The glass, the case of the warhead and its connections with neighboring compartments form cavitational waveguides, for this connection are made of the same material as the case of the warhead, and with a thickness greater than or equal to its thickness.

In an analogue, the activation of DLD due to the creation of cavitational bubbles in its mass from its own liquid combustible and explosive components (bubbles of their vapor) occurs both at the launch and on the march of a rocket under the influence of vibration-wave processes in the launch and marching jet engines, and on the target under the influence of shock-wave processes when the bottom fuse and ignition-explosive charge are triggered, which significantly increases the blasting and high-explosive power of the ODZ and its sensitivity to the initiating pulse, i.e. allows the level of activation of the DLD at the time of the end of the operation of the marching jet engine to significantly reduce the mass of the ignition charge, therefore, this takes place at sufficiently large firing ranges.

The disadvantage of the analogue is that the increase in the number of cavitation bubbles in the DLD occurs gradually, and therefore the mass of the explosive explosive charge for more effective firing at short distances is forced to be selected according to the level of activation of the DLD at the end of the starting jet engine, i.e. in the prototype, only a small part of the large positive effect of the activation of the DLD was used.

A known method of hitting a target with a missile, mainly guided, and a missile (see patent RU No. 2197708, IPC F42B 15/00, published on January 27, 2003, selected as a prototype. A missile contains a head compartment ending in a marching jet engine with an axial through channel smoothly interfaced with a recess in its rear bottom, a warhead with a special-purpose cylinder, partially or completely filling its body, along the axis of which a glass is fastened, fastened with a neck with the bottom of the body. a body-explosive charge and a bottom fuse, while the main engine and the warhead body are connected by a bond that is crushed when they hit the target — a perforated cylindrical shell, under which an injector is formed between the head compartment and the warhead, formed on one side by a channel and a recess in the rear bottom marching jet engine, and on the other - partially or fully recessed in this recess in the front of the warhead. When a projectile collides with a target, under the action of the pressing mass of the warhead and the tail compartment, the connection between the head compartment and the warhead is crushed and the latter is centered in the recess of the rear bottom of the marching engine. At this point, after a time delay, the bottom fuse detonates and detonates the ignition-explosive charge, which scatters its own shock wave and initiates the main mass of the detachment radar in the radial direction, and its part in front of the warhead glass and partly in the recess of the sustainer engine’s bottom is pushed through its channel in the direction goals. In this case, the ODZ in the channel is intensively compressed, i.e. activates and, upon exiting it, detonates when it encounters oxygen.

The disadvantages of the prototype are

- the need to have a sufficiently strong warhead body and rear bottom of the mid-flight engine to prevent their deformation when meeting with the target, especially at significant angles, to ensure their good mutual alignment;

- the need to have a sufficiently powerful ignition-explosive charge for the destruction of a strong body of the warhead.

The complete elimination of these shortcomings, ceteris paribus, will lead to a significant reduction in the mass of the DLD, and partial to its unstable efficiency under various conditions of the projectile meeting with the target.

This circumstance is substantially aggravated by the fact that an insignificant part of the SPS is thrown directly at the target through the channel in the marching engine.

The technical task of the present invention is to increase the efficiency of guided missiles with a special target range.

The technical result obtained by carrying out the invention consists in high efficiency, as well as high sensitivity of the activated DLD to the initiating pulse, which allows providing a substantial part of this pulse with a thermal pulse created during forced explosive destruction of the hull and powder charge of a jet propulsion engine.

The specified technical result is achieved by the fact that in a missile, mainly guided, containing a warhead with a volume-detonating charge placed in the housing, a bottom fuse and an ignition-explosive charge placed in the housing in the form of a pipe fastened to the bottom of the warhead housing, marching jet engines associated with the warhead through hollow cylinders, the new is that the volume-detonating charge is made with liquid components, the warhead housing is elongated, the front end b on the main part of the main engine is covered with a cap made in the form of a cap and installed in the warhead body with a concave side to the volume-detonating charge, sealing elements of their joint in the form of rubber rings mounted in annular grooves are installed between the cap and the warhead body cover, on the inner surface of the warhead housing around the cover in the area of the joint sealing elements, an annular protrusion is made, a through axial hole is made in the cover for mounting it on the case of the bottom fuse and the explosive-explosive charge, while on the outer surface of the case of the bottom fuse and the explosive-explosive charge an annular protrusion is made, and the cover is mounted abutting the said protrusion and tightly pressed against it by a nut screwed on the case of the bottom fuse and the ignition-explosive charge, and the ignition-bursting charge from the side of the sustainer engine is tightened by a nut screwed into its housing to an annular protrusion made in the aforementioned pipe in front of the bottom fuse.

Technical solutions with features distinguishing the claimed solution from the prototype are not known and do not follow explicitly from the prior art. This suggests that the claimed solution is new and has an inventive step.

The essence of the invention is illustrated by drawings, where figure 1 shows a missile, mainly guided; figure 2 - node a in figure 1, illustrating the relative position of the mid-flight engine and the closest elements of the warhead; figure 3 - the relative position of the mid-flight engine and the same elements of the warhead immediately before its detonation.

The missile consists of a head compartment 1 (see Fig. 1), including including a marching engine 2, a tail compartment 3, including a starting engine 4 and a tail unit 5, located between them and fastened to them by the connections of the warhead 6. At the rear bottom 7 main engine 2 (see figure 2) from the side of the warhead 6 made local bosses in which nozzles 8 are formed for the expiration of powder gases from the combustion of the powder charge 9, which occurs almost all the time the rocket flies to the maximum firing range and is a source of food linear and transverse vibrational wave disturbances.

The warhead 6 (see figure 2) consists of a housing 10 having the shape of a cylinder from the side of the mid-flight engine 2 and a truncated cone - to the tail compartment 3, with which it is connected, for example by a thread. The cylindrical part of the housing 10 is mounted on the main engine 2 and fastened with it in the area of its bottom 7 in front of the nozzles 8 with screws 11. In the same part of the housing against the nozzles 8 there are openings for the free flow of powder gases into the atmosphere.

On the axis of the housing 10 of the warhead 6, a shock-wave generator is mounted, formed by its body in the form of a pipe fastened to the housing 10, inside of which there is a bottom fuse 13 and an ignition-bursting charge 14, which is pressed by the nut 15 from the main engine 2 to the ring ledge 16, placed inside the pipe 12 between them. The nut 15 is installed in the pipe 12 on the thread. The cylindrical part of the housing 10 in front of the main engine 2 is covered with a cap 17 made in the form of a cap, installed a hollow part to the tail compartment 3 and having an axial hole with which it is worn on the pipe 12.

An annular protrusion 18 is made on the pipe 12, to which the cover 17 is pressed by a nut 19 screwed onto the pipe 12.

Between the cylindrical part of the housing 10 and the cover 17, their joint sealants are installed in the form of rubber rings 20 located in the annular grooves on the cover, and a local annular protrusion 21 is made on the housing against these rings. This protrusion can be formed by compressing the housing 10 in the radial direction and necessary to prevent damage to the rings 20 when installing the cover 17 in the housing 10.

The cavity of the body of the warhead 6, formed by its body 10, tube 12 and cover 17, is filled with a volume-detonating warhead 22, represented, for example, by a liquid, paste-like or structured thermobaric mixture containing liquid components.

The device operates as follows. When fired, the starting jet engine 4 is triggered and accelerates the rocket along the length of its guide. In this case, the longitudinal and transverse vibration-wave effects arising from the burning of its powder charge and the expiration of powder gases through the waveguides-cavitators formed by the engine body, body 10 of the warhead 6, tube 12 and cover 17 are transferred to the volume-detonating charge 22 and activate due to the formation of vapor bubbles in it from liquid components in layers adjacent to cavitating waveguides.

When the marching jet engine 2 is triggered, longitudinal and transverse vibration-wave effects arising from the burning of its powder charge 9 and the expiration of the powder gases are transmitted through the waveguides-cavitators formed by the engine body, body 10 of the warhead 6, pipe 12 and cover 17 to volumetric detonating charge 22 and continue the process of its activation, which ends only at the time of combustion of charge 9.

When meeting a rocket with a target at any distance

 crumpled the front of its head compartment 1 to the marching jet engine 2;

 the housing 10 of the warhead 6 under the action of the pressing masses of all elements of the rocket behind the screws 11 is deformed in the radial direction and shortened;

 the cover 17, under the action of the pressing mass of the volume-detonating charge 22 moves to the main engine 2, collapses or is re-stamped in the form of its rear bottom 7 and, freeing the pipe 12 from communication with itself, is snapped out of the seal between the annular protrusion 18 and the nut 19;

 the pipe 12 sticks into the bottom 7 of the marching engine 2 and at this moment the bottom fuse 13 and the ignition-explosive charge 14 are sequentially activated, forming an additional generator for activating the volume-detonating charge 22 — shock wave;

 under the influence of a detonation wave from the operation of the ignition-explosive charge 14, the volume-detonating charge 22 is scattered in the lateral direction and is initiated, at the same time this detonation destroys the bottom 7 of the marching engine 2 and its powder charge 9, which is accompanied by the explosion and emission of a sufficiently powerful heat pulse to expand - detonating charge, contributing to its fuller initiation even with a small mass of ignition-explosive charge.

From the description of the device and the operation of the rocket it can be seen that there is a fairly clear relationship between the degree of activation of the volume-detonating charge and the pulse initiating this charge: the greater the firing distance (higher than the degree of activation of the volume-detonating charge), the smaller the initiating pulse from the ignition explosive charge due to the increase in it of the share of the explosion remaining in the marching engine part of the powder charge.

This circumstance makes it possible to reduce the mass of the explosive-explosive charge by 10-12% and, accordingly, increase the mass of the volume-detonating charge, i.e. increase the effectiveness of the missile on the target in any conditions of their meeting.

In addition, the forced explosive destruction of the marching engine, including the use of its powder charge energy for this, significantly reduces the negative impact of the former on the target’s destruction - the engine shields the target less from the damaging factors of the volume-detonating charge, and with its fragments can cause additional damage .

From the description of the device and the operation of the rocket it also follows that the main engine in it may not have a through axial channel and a recess in the rear bottom, with which it smoothly mates, and this will not affect its effectiveness on the target.

Claims (1)

A missile, mainly guided, containing a warhead with a volume-detonating charge placed in the hull, a bottom fuse and an explosive-explosive charge placed in the hull in the form of a pipe fastened to the bottom of the warhead, launch and marching jet engines associated with the warhead by means of hollow cylinders, characterized in that the volume-detonating charge is made with liquid components, the warhead body is elongated, the front end of the warhead from the main engine side is covered with made in the form of a cap and installed in the warhead housing with the concave side to the volume-detonating charge, sealing elements of their joint in the form of rubber rings mounted in annular grooves made on the cover on the inner surface of the combat housing are placed between the cover and the body of the warhead parts around the cover in the area of the joint sealing elements are made an annular protrusion, in the cover there is a through axial hole for mounting it on the bottom fuse and ignition-burst housing about the charge, while on the outer surface of the bottom fuse housing and ignition-explosive charge an annular protrusion is made, and the lid is mounted with a stop in the said protrusion and is tightly pressed by a nut screwed on the bottom fuse and ignition-explosive charge, and the ignition-explosive charge the charge from the side of the mid-flight engine is tightened by the nut screwed into its housing to the annular protrusion made in the said pipe in front of the bottom fuse.

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