RU2333454C2 - Fighting unit and device for delivery thereof to target - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: group of inventions refers to military equipment, mainly to the antiweapon with rigid targets, e.g. thickwalled protective works and/or flight landing strips. The fighting unit includes anterior and posterior blocks with bursting explosives and base detonating. The anterior block is made thickwalled, sub-calibered relative to the posterior one and with the front section of a penetrating type, the posterior one being thinwalled. The front section of the anterior block is made as two conjugate cones of the total length of 2.4-5.0 calibres of the anterior block with the vertex angle of the anterior cone being equal or more than 100 and less than 180 degrees. The device includes all-solid rocket engine with a cylindrical body with protrusions on its inner surface, anterior bottom, nozzle block, channel charge of the solid fuel, bushing and ignition device. The engine is additionally equipped with the posterior diaphragm made in the form of glass with lateral long slots and bottom ports.

EFFECT: improved reliability of fighting unit delivery to the target point and performance at the approach angle to the target surface of 28-90 degress without ricochet.

4 cl, 3 dwg

Description

The present invention relates to military equipment, mainly to means of dealing with tough targets, for example: thick-walled defenses and / or runways.

Recently, local military conflicts that have arisen are highly transient and aviation is often used to achieve an operational advantage. To eliminate the loss of the carrier aircraft, they fly to its flight over the target at an extremely low altitude and at maximum speed. Therefore, the urgent problem is the accuracy of hitting the warhead at the target and the reliability of its destruction.

Of all the known technical solutions to achieve a similar goal, we selected as a prototype the warhead according to the FRG patent No. PS 3408113 of 03/06/1984, class. 3 F42B 13/12. The specified warhead contains the front and rear blocks, a bursting charge, an ignitor located in front of the bursting charge, fuses located in both blocks, and a moderator, the front block being made thick-walled and subcaliber, and the rear one thin-walled and caliber. Moreover, an additional bursting charge with an igniter is placed before the bursting charge. Fuses are located in each block and operate independently of one another in time, and between them is a moderator to prevent detonation of the neighboring fuse.

The disadvantages of the known technical solutions are: 1) accuracy is not provided as a goal; 2) the use of the animated shape of the head of the front block allows punching reinforced concrete barriers only at angles of more than 45 degrees from the target surface, otherwise there will be a rebound; 3) the revival form of the over-caliber (with respect to the front block) head part of the rear block does not allow to effectively use the peripheral fracture zone left in the wake by the front block after it is separated from the back to increase the penetration depth (penetration thickness); 4) the absence of a weakened cross-section in the interface between the blocks (front sub-caliber) and the connection unit of the rear unit with the front bottom of the delivery vehicle makes the position of the separation section of the blocks in the barrier unpredictable, while the destruction of the tail of the front unit and the release of the fuse before it fires ( detonation pulse).

The problem solved by the invention is the creation of such a design that allows for reliable delivery of the warhead to a given point and the task at angles of meeting with the target surface of 28-90 degrees without rebound.

This object is achieved in that the proposed design of the warhead includes front and rear units with their own explosive charges by ground fuses, the front unit being thick-walled and subcaliber relative to the rear with the penetrating type head part, and the rear unit thin-walled, the units are autonomous and connected coaxially low-strength mount, and the head of the front block is made in the form of two conjugated cones with a total length of 2.4-5.0 of its caliber with the angle of the front a cone, equal to 100-180 degrees, and a diameter of its base of 0.45-0.90 caliber of this block, and the rear block of one and / or more independent subunits in the form of cylindrical cups, each of which is equipped with its own explosive charge and a bottom fuse , and the warhead itself is equipped with a device for its delivery to the target in the form of a solid fuel rocket engine, made with the possibility of its axial twist and connected to the warhead by a fastening unit with a weakened cross section. Each low-strength mounting unit is made in the form of coaxially mounted and interconnected plastic dampers in the form of a stepped sleeve, a union nut, an external thrust ring on the side surface of the rear of the housing of the previous unit and / or subunit and the weakened front of the subsequent unit or subunit. A threaded connection is made between the union nut and the weakened front of the subsequent unit or subunit. The caliber of the subsequent subunit is equal to 1-2 calibers of the previous one.

The execution of the warhead from autonomous blocks connected by low-strength attachment points in the form of a set of a plastic damper, a union nut and an external thrust ring, a threaded connection and a weakened front of the subsequent block / sub-block facilitates the disengagement of these blocks from each other and the successful completion of the task.

The implementation of the specified length of the head of the front block, consisting of two conjugated cones, the angle of the opening angle of its front cone and the diameter of its base provides the optimal penetration of the front block into a rigid reinforced concrete barrier in a wide range of angles of approach to the target without the risk of rebound, which greatly facilitates the execution of tasks.

The execution of the warhead from autonomous blocks and the rear block from one or more independent subunits in the form of cylindrical cups with its own explosive charge and a bottom fuse expands the function of the warhead by using various forms of payload in these blocks / subunits.

The use as a device for delivering the warhead to the target of a solid propellant rocket engine connected to the warhead by a fastening unit with a weakened cross section and made with the possibility of axial twisting, improves the accuracy of hit, provides the desired speed and angle of penetration into a rigid reinforced concrete barrier, separation blocks / subunits when breaking through the obstacle, which ensures the fulfillment of the task.

As a result of the patent information search, we did not identify any well-known technical solutions that would use all the above essential features for the same or similar purpose. Therefore, the proposed design of the warhead meets the criterion of "inventive step".

The invention is shown schematically in FIG. 1, and FIGS. 2 and 3 show the principle of its operation.

The proposed design (see Fig. 1) is a warhead consisting of a front 1 and a rear 2 blocks interconnected by a low-strength attachment unit, including a plastic damper in the form of a stepped sleeve 3, a union nut 4, an external thrust ring 23 on the side surface the tail of the previous block and the weakened front 24 of the subsequent block. Moreover, between the last and the union nut a threaded connection 25 is made. In the cavity of the front block there is a bursting charge 7 and a bottom fuse 5. In the rear block, respectively, charge 8 and fuse 6.

The proposed design is equipped with a device for delivering the warhead to the target in the form of a solid fuel rocket engine, the design of which will be described below.

The proposed warhead and the solid-propellant rocket engine (hereinafter, the rocket) connected to it operate as follows.

Acceleration of the warhead as part of a rocket to the speed necessary to break through an obstacle is performed by a solid fuel rocket engine (solid propellant rocket engine). At the moment of entering the obstacle of the next block, subunit or solid propellant rocket with a caliber larger than the previous one, the front block / subunit is separated from the missile structure by a cut-off outer thrust ring or a weakened section. Until the front of the sub-caliber block / sub-block enters the obstacle along its length, part of the kinetic energy of the subsequent block / sub-block and solid propellant rocket motor is transmitted through plastic inserts and attenuated sections. When separating blocks / sub-blocks, the liner of plastic material does not create tensile loads. Thereby, the bottom part of the front block / subunit, in which the bottom fuse is installed, is preserved from destruction. Since this eliminates additional resistance to movement from subsequent blocks / subunits or solid propellant rocket motors, the front block / subunit is capable of breaking through a greater thickness of the barrier than without separation. In addition, the front block / subblock, moving ahead, leaves behind a channel in the reinforced concrete barrier with the material of the barrier destroyed by the discharge waves along the periphery (see Fig. 2). Due to this, subsequent blocks / subblocks having calibers greater than the previous one by 1.3-1.4 times, and the head part in the form of a cylindrical cup, are able to penetrate beyond the barrier that the previous block / subblock has overcome. But their exit speed from the obstacle is significantly lower than the exit speed of the previous block / subblock. This allows in the case of autonomous charges of explosives and fuses with a given deceleration time to receive spaced areas of detonation (see Figure 3), significantly increasing cross-target damage.

For a given geometry of the head of the front block, typical rocket speeds, a restoring moment acts on the warhead from the side of the obstacle from the resistance forces, exceeding or equal to about 28 degrees to the approaching angle to the target’s surface. This eliminates the rebound.

When the runways are destroyed at angles to their surface of 28-30 degrees in the absence of a rebound, separation of blocks / subblocks and separated explosive charges in the ground under a reinforced concrete coating, destruction zones of this coating are created 1.5-2.0 times larger in area, than in cases of using a single-unit warhead with an equivalent explosive mass and optimal fuse deceleration.

By the design of the device for delivering the warhead to the target, we identified analogues, but by the combination of essential features, we chose the following as a prototype.

The solid fuel rocket engine according to the patent of the Russian Federation 2221159 dated 01/14/2002, class 7 F02K 9/22, which includes a cylindrical body with protrusions on its inner surface and front bottom, nozzle block, channel charge of solid fuel burning along the outer surface and inner channel and hinged to the front bottom of the metal sleeve, as well as an ignitor.

The disadvantages of the known technical solutions are: 1) the known design, including a single nozzle unit, requires special devices for twisting the rocket around the longitudinal axis in the launch tube; 2) for more effective acceleration of the rocket in the launch tube, as well as for holding it from axial movements until the moment of launch, a special device is required, for example, a launch cup connected to a solid propellant rocket motor with a low-strength connection. In the known technical solution, such a glass is absent, which leads to the failure (subsidence) of the rocket after it leaves the launch tube; 3) the protrusion on the inner surface of the housing, located closer to the nozzle block, has the shape of a lampshade and is made of fireproof material. Its connection with the metal body is carried out by a bonding material, for example, glue. Such a connection is unreliable during long-term storage of missiles at ambient temperature differences within ± 40 degrees.

As indicated above, the problem solved by the present invention is the creation of such a design of the warhead and device for its delivery to the target, which would allow the warhead to penetrate through rigid obstacles, for example, guards for hangars and the like, with high accuracy of hit and the probability of hitting the target .

This goal is achieved by the fact that in the proposed design of the device for delivering the warhead to the target in the form of a solid fuel rocket engine, including a cylindrical body with protrusions on its inner surface and front bottom, nozzle block, channel charge of solid fuel burning on the outer surface and inner the channel and a metal sleeve pivotally hinged with the front bottom, as well as an igniter, an additional cup with side gas-dynamic holes is additionally placed, the above sleeve with united with the charge of solid fuel with a layer of binder material in the form of a truncated cone with a large base located at the front bottom of the engine, equipped with a grip in contact with a holder having side and axial holes, mounted on the front bottom of the engine and containing an igniter, a tape is made on the outer surface of the sleeve thread, for the possibility of creating its axial twist and nozzle nozzle (at least two) at its exits, beveled at an angle of 70-85 degrees to its own longitudinal axis and unfolded planes and a bevel relative to each other by an angle equal to 360 / n degrees (where n is the number of nozzles, but not less than two), the nozzle block is additionally equipped with a drop-down plumage with blades made with beveled front edges, and the engine is additionally equipped with a rear diaphragm made in the form glasses with lateral longitudinal slots and bottom holes.

The use of a launch cup with lateral gas-dynamic holes in combination with beveled nozzles and a drop-down plumage with blades made with beveled front edges guarantees a reliable exit of the device from the launch block, the desired axial spin speed and, therefore, accurate and timely delivery of the warhead to the target.

The fastening of the channel charge of solid fuel of the specified type in combination with the use of the rear diaphragm with the corresponding slots and holes guarantees reliable fastening of the charge, a predictable mode of its burning and, therefore, the fulfillment of the task.

We have not identified a similar design in known technical solutions, therefore, in the engine part, the alleged invention meets the criterion of "inventive step".

The proposed design of the device for delivering the warhead to the target is schematically depicted in FIG. 1, where the cylindrical body 9, the protrusions 26 on its inner surface, the front bottom 14 of the body, the channel charge 10 of solid fuel, a metal sleeve with a tape thread 11, an ignitor 20, a starting glass 17 with gas-dynamic holes 19, nozzle block 15, 16, gripper 22, holder 12, rear diaphragm 13 with slots and holes. Moreover, the sleeve is connected to the charge 10 by a layer 21 of binder material in the form of a truncated cone with a large base located at the front bottom of the engine, and is equipped with a grip in contact with the holder with side and axial holes. The nozzles 16 in the nozzle block at their exits are made beveled at an angle of 70-85 degrees to their own longitudinal axis and are turned by bevel planes relative to each other at an angle equal to 360 / n (where n is the number of nozzles, but not less than two). The plumage blades 18, which open upon the rocket leaving the launch block, are made with bevels at the leading edges 29, which create a positive twist moment from the incoming air flow.

The proposed technical solution operates as follows (see Figure 1).

The warhead with a solid fuel rocket engine (rocket) is installed in the launch tube before launch by launch cup 17 into the lock of the launch block.

The launch of the solid propellant rocket motor is carried out by supplying a pyroimpulse to the igniter 20 installed in the front bottom 14 of the housing under the holder 12. Hot gases from the igniter 20 through the side and axial holes made in the holder 12 enter the internal channel of the charge of solid fuel 10 through the hole in the sleeve 11 and ignite charge 10. Due to the intracameral pressure, the membranes installed in the nozzles open and a thrust is created from the outflow of gas products through the nozzles 16. When the thrust is exceeded, the failure of the launch canister 17 from the nozzle block 15, the launch cup and the solid propellant rocket are separated and the rocket starts. Under the action of axial acceleration created by jet thrust, the charge 10 is held by a holder 12, mounted on the front bottom 14 of the housing 9, a grip 22, bonded to a sleeve 11 of non-combustible material, which in turn is bonded to a charge 10. To increase the reliability of the connection of the sleeve 11 with the charge 10 on its surface is made of an external tape thread 29, which is filled with a binder material 21 connected to a charge 10. The layer of binder material is made in the form of a truncated cone 21 with a large base located at the front bottom 14 of the housing 9, in order to increase the reliability of fastening during technological gluing.

When the rocket moves inside the launch tube, the main part of the gas flow from the combustion of the charge leaving the nozzles rushes through the axial hole of the launch cup 17, and the rest - into the gap between the outer side surface of the launch cup and the inner surface of the launch tube. At the same time, in the bottom part, this gap is tightly closed by the tail part of the launch cup, pressed by the lock to the end (rear) surface of the launch tube. In this gap, braking pressure is created, and the wall of the launch cup experiences an external pressure drop of the combustion gases of charge 10. Due to the flow of gases through the gas-dynamic holes 19 in the side wall of the launch cup, this pressure drop is significantly reduced. This achieves an increase in the reliability of the action of the launch cup without loss of stability (loss of shape or collapse) and the exclusion of its ejection from the lock of the launch block.

Due to the outflow of hot gases through beveled nozzles, of which there are at least two, a gas-dynamic moment arises (twisting the rocket around its longitudinal axis. At the moment of its exit from the launch tube and the tail unit opening, the rocket acquires the initial angular velocity, as well as linear enough to overcome initial perturbations after exiting the launch tube.After opening, the tail unit stabilizes the rocket, dampens the initial perturbations, due to the bevels of the leading edges of the blades, creates an additional aerodynamic sky time twist missiles around its longitudinal axis. This significantly reduces the dispersion of the individual vehicle and increases its accuracy hitting small targets.

Due to the hydraulic resistance created by the rear diaphragm 13 and the front side protrusions 26 on the inner surface of the housing, the gas flow from the combustion of the charge is redistributed. The main part of it passes through the holder 12 and the sleeve 11 and the internal channel of the charge, the rest with reduced speed through the annular gap between the outer surface of the charge and the inner housing through the diaphragm 13 into the nozzle block. Due to this, the heat stress of the housing is reduced, which allows to reduce the thickness of its wall and increase the coefficient of structural perfection of the engine.

At the end of the active section of the flight, the rocket develops a speed sufficient to break through typical reinforced concrete barriers and / or runways by the proposed design of the warhead at meeting angles to the target surface of 28-90 degrees without a rebound.

Thus, the proposed design of the warhead and device for its delivery to the target has the following technical advantages: 1) it provides increased reliability of delivery and accuracy of hitting small-sized targets such as reinforced concrete structures, the required speed for breaking through them and an increased likelihood of hitting target targets; 2) the use of the indicated design of the launch cup guarantees reliable launch of the rocket from the launch block, excluding the collapse and ejection of the specified glass from the launch block; 3) the use of the proposed design of the warhead provides at standard speeds of approach of the missiles to the target a reliable penetration of both typical reinforced concrete shelters and runways at angles to the target surface of 28-90 degrees; in addition, it allows to increase the area of the destruction zone of runways at typical approach angles by 1.5-2.0 times compared with the equivalent mass of explosives single-unit warhead; 4) due to the use of a different design (compared to that described in the prototype) of the composite warhead, a different mechanism for overcoming a rigid reinforced concrete obstacle is implemented and a significant increase in the thickness of the penetrated obstacles is achieved, spaced-apart zones of blasting of blocks (subunits) are created and the effectiveness of the backgrad action is increased; 5) the use of the proposed designs of the rear diaphragm and fastening the charge to the front bottom of the solid propellant rocket motor reduces the heating temperature of the wall of the housing by 150-200 degrees, thereby increasing the reliability of the solid propellant rocket motor with its higher structural perfection.

A prototype of this design was tested at the test site and confirmed the required reliability of operation of all blocks.

Claims (4)

1. The warhead, including the front and rear units with explosive charges and ground fuses, of which the front unit is made of thick-walled, subcaliber relative to the rear and with the penetrating type head, and the rear is thin-walled, characterized in that the front of the front unit is made in the form two conjugated cones with a total length of 2.4-5.0 caliber of the front block with an angle of opening of the front cone equal to or greater than 100 and less than 180 °, and a diameter of its base of 0.45-0.90 caliber of the front block, and the rear block from one or more its independent parts in the form of cylindrical cups, each of which is equipped with its own explosive charge and a bottom fuse, the caliber of the independent part of the rear block is equal to 1-2 calibers of the front block or the previous independent part of the rear block, and the front and rear blocks, as well as independent parts of the rear block coaxially connected by low-strength connection nodes. 2. The warhead according to claim 1, characterized in that the low-strength connection node is made in the form of coaxially mounted and interconnected plastic dampers in the form of a stepped sleeve, a union nut, an external thrust ring on the side surface of the tail of the front unit housing or the previous independent part of the rear unit and the weakened front of the rear block or the subsequent independent part of the rear block, and between the union nut and the weakened front of the rear block or its independent part, threaded connection. 3. A device for delivering a warhead to a target, comprising a solid fuel rocket engine having a cylindrical body with protrusions on its inner surface, a front bottom, a nozzle block, a channel charge of solid fuel burning along the outer surface and the inner channel, and hinged to the front the bottom is a metal sleeve, and an igniter, characterized in that it is equipped with a diaphragm and a launch cup with side gas-dynamic holes, and the metal sleeve is connected to the charge of solid fuel by a layer binder material made in the form of a truncated cone with a large base located at the front bottom of the engine and provided with a grip in contact with a holder having side and axial holes fixed to the front bottom of the engine and containing an igniter, and a tape thread is made on the outer surface of the sleeve ensuring the possibility of axial twist of the engine, in the nozzle block the nozzles at their exits are beveled at an angle of 70-85 ° to their own longitudinal axis and deployed by the bevel planes relative to each other on goal of 360 / n degrees, where n - the number of nozzles, but at least two, and is provided with a drop-down soploblok tail blades, made with bevelled front edges. 4. The device according to claim 3, characterized in that the diaphragm is made in the form of a glass with lateral longitudinal slots and bottom holes.

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