RU2551868C1 - Housing of jet projectile cassette-type warhead - Google Patents

Abstract

FIELD: weapon and ammunition.

SUBSTANCE: housing of jet projectile cassette-type warhead contains a shell, a frame. The frame is designed as a central pipe connected to a front disk and a piston contacting with the internal surface of the shell and connected by means of rupture bolts to the base disk which is rigidly fastened to the shell. In the front disk evenly equidistantly from the centre the through inclined gas passages are made at an angle 25°…45° to the longitudinal axis of the central pipe. The centres of inlet holes are located along a circle with the diameter 0.4…0.7 from the internal diameter of the shell. Exhaust outlets of gas passages are placed in intervals between places of fastening of combat elements. On the piston, in its peripheral part, the sealing-damping device made of elastic material is mounted with a possibility of interaction with the shell.

EFFECT: improvement of combat efficiency and reliability of functioning of cassette-type combat units.

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Description

The invention relates to the field of rocketry, and in particular to rockets with a cluster warhead.

The object of the invention is a cassette of a warhead of a missile projectile of increased combat effectiveness and operational reliability.

The combat effectiveness of a rocket launcher with a cluster warhead (CBC) to a large extent depends on the number of warheads in the warhead hull, styling and orientation relative to each other and the longitudinal axis of the hull, the design of the components of the hull to ensure the delivery of warheads to the target, the reliability of the fuse Before ejection, reliable ejection with the required dispersion characteristics in the target area.

In addition, the casing of the CBC must ensure reliability and safety during transportation, long-term storage in various conditions.

The well-known housing of the missile defense shell according to the patent of the Russian Federation No. 2156428 from 09/20/2000, the housing contains a shell, a container in the form of a coil consisting of a central rod, front and rear discs, front and rear covers. The back cover is made movable in the axial direction with holes through which the container fixation elements in the shell pass.

This technical solution allows to provide rigidity and strength of the housing, to provide a radial dispersion of cassettes with elements, to use it in large-sized KBCH.

However, this technical solution does not allow it to be used to deliver to the target combat elements, submunitions with gas-dynamic cocking of fuses in working position before dropping them from the housing.

Thus, the objective of the known technical solution was to increase the strength and rigidity of the structure, the placement of submunitions for various purposes.

Common features of the design of the design of the casing gearbox proposed by the authors is the presence of a shell, a container (or in other words a frame) in the form of a central rod, front and rear disks.

Known case cassette warhead of a rotating rocket of solid fuel according to the patent of the Russian Federation No. 2238696 class. IPC F42B 12/58, publ. July 10, 2008. The housing contains a shell, a container (frame) in the form of a coil consisting of a central rod, front and rear disks, between which longitudinal ribs are fixed on the outer surface of the central rod, contacting their outer edges with the inner surface of the shell.

In the central zone of the ribs and at the places of their connection with the bar, perforating windows are made connecting the internal radial cavities with each other. The analogue materials show the relationship between the area of the windows and the longitudinal ribs for the distribution of gas in the entire internal volume of the housing.

The objective of the known technical solution was to develop the design of the shell of the missile-propelled shell of a rocket, providing conditions for gas-dynamic cocking of fuses of submunitions in all internal cavities of the shell.

The presence of longitudinal ribs with windows makes it possible to increase the rigidity of the structure and solve the problem. Such a constructive solution is applicable to large-sized KBK large-caliber and elongated cases.

Common features of the design of the design of the casing gearbox proposed by the authors is the presence of a shell, a container (or in other words a frame) in the form of a central rod, front and rear disks.

The closest in technical essence and the achieved technical result is the design of the shell of the missile defense shell with a cluster head according to the patent of the Russian Federation No. 2435130 in class. IPC F42B 12/58, publ. 11.27.2011, the head housing, adopted by the authors for the prototype, contains a shell, a frame in the form of a central pipe connected to the front disk and a piston in contact with the inner surface of the shell and connected by means of bursting bolts to a support disk rigidly attached to the shell.

The specified design of the body of the warhead allows for the laying of a large number of combat elements, the strength and rigidity of the warhead.

However, during a long flight of a long-range missile with the specified design of the head shell, external influences on its shell (aerodynamic heating, vibration from engine operation and other structural elements, etc.) in some cases lead to an increase in the gap between the piston and the inner shell surface , the occurrence of vibrations and undesirable bending stresses in the explosive bolts, which reduces the reliability of the operation of the head. In addition, the peculiarity of the air flow around the front of the frame in the form of a disk after departure from the shell leads to a delay in the time of ejection of combat elements.

Common features of the design of the cassette warhead shell proposed by the authors are the presence of a shell in the prototype, a frame in the form of a central tube connected to the front disk and the piston in contact with the inner surface of the shell and connected via bursting bolts to a support disk rigidly fastened to the shell.

In contrast to the prototype, in the proposed case of the cluster warhead of the rocket projectile in the front disk uniformly through the same distance from the center, through inclined gas ducts are made at an angle of 25 ° ... 45 ° to the longitudinal axis of the central pipe, the centers of the inlet openings of which are located on a circle with a diameter of 0.4 ... 0.7 of the inner diameter of the shell, and the outlet openings of the gas ducts are placed in the spaces between the attachment points of the combat elements, while on the piston, in its peripheral part, it is mounted with the possibility of interaction with a hermetic sealing-damping device made of an elastic material.

This allows us to conclude that there is a causal relationship between the totality of the essential features of the claimed technical solution and the achieved technical result.

These signs, distinguishing from the prototype, and to which the requested amount of legal protection applies, in all cases are sufficient.

The objective of the invention is to create a housing for a cluster warhead of a rocket, providing increased reliability and combat efficiency by significantly reducing the impact on the structural elements of aerodynamic heating, vibration during the flight of the projectile with an increased range, ensuring a given uniform dispersion of small-sized warheads in the area by increasing the reliability of ejecting them from the frame after it leaves the shell.

The specified technical result is achieved by the fact that in the cassette of the warhead of the rocket containing the shell, the frame is in the form of a central pipe connected to the front disk and the piston in contact with the inner surface of the shell and connected by explosive bolts to a support disk rigidly fastened to the shell, according to the invention in the front disk uniformly at the same distance from the center there are made through inclined gas ducts at an angle of 25 ° ... 45 ° to the longitudinal axis of the central pipe, the centers of the inlet openings which are located on a circle with a diameter of 0.4 ... 0.7 of the inner diameter of the shell, and the outlet openings of the gas ducts are located in the spaces between the attachment points of the combat elements, and a sealing-damping device is mounted with the possibility of interaction with the shell on the piston in its peripheral part, made of elastic material.

A new set of structural elements, as well as the presence of connections between the parameters of the claimed housing of the cluster warhead of a rocket projectile, allowed, in particular, due to the following:

- in the front disk uniformly at the same distance from the center of the through inclined gas ducts at an angle of 25 ° ... 45 ° to the longitudinal axis of the central pipe, the centers of the inlet openings of which are located on a circle with a diameter of 0.4 ... 0.7 of the inner diameter of the shell - to increase the reliability of the ejection of combat elements from the frame after it leaves the shell through the use of high-speed pressure of the incoming air flow passing through the gas ducts, change the structure of the flow around the front disk and exclude the pressing of warheads to the central th tube frame. Performing a circle diameter of less than 0.4 of the inner diameter of the shell reduces the impact of air jets flowing from the outlet openings of the gas ducts on the process of ejection of combat elements from the hull. An increase in the circle diameter of more than 0.7 of the inner diameter of the shell leads to a decrease in the effect of air jets on the process of ejection of combat elements. Performing the angle of inclination of the gas ducts within the specified limits allows for a uniform and orderly effect of the air flow on the ejection of combat elements from the frame after it leaves the shell, to reduce initial disturbances on the dynamics of the movement of combat elements, and to provide a given uniform dispersion of them on the ground. The implementation of the angle of the gas ducts less than 25 ° changes the nature of the flow around the combat elements only in the longitudinal direction and does not affect the process of their ejection in the radial direction. An increase in angle above 45 ° does not affect the process of ejection of combat elements from the frame;

- gas outlets in the spaces between the attachment points of the combat elements - to increase the reliability of the ejection of combat elements in the radial direction from the longitudinal axis of the Central pipe through the use of high-speed pressure of the incoming air flow;

- in the peripheral part of the piston of a sealing-damping device mounted with the possibility of interaction with the shell and made of elastic material - to exclude the flow of hot gas from the cavity between the piston and the supporting disk into the internal volume of the shell during the ejection of the frame from the shell and exclude its effect on combat elements , provide the required longitudinal force for reliable ejection of the frame, reduce the impact on the structural elements of the body (piston, frame, burst bolts, etc.) of the aerodynamic nical shell heating, to carry out possible transverse vibration damping during flight of the projectile with increased range, improve reliability of the head portion and the cassette bomblets, to increase their combat effectiveness.

The invention is illustrated by the drawing of FIG. 1, which shows a General view of the body of the cluster warhead of a missile.

The cassette of the warhead of a missile shell consists of a shell 1, frame 2, consisting of a central pipe 3 connected to the front disk 4 and the piston 5.

The piston 5 is connected by means of bursting bolts 6 to a support disk 7, rigidly fastened to the shell 1. On the piston 5, in its peripheral part, a sealing-damping device 8 made of elastic material is mounted with the possibility of interaction with the shell 1.

In the front disk 4, uniformly through the inclined gas ducts 9 are made uniformly at the same distance from the center at an angle α = 25 ° ... 45 ° to the longitudinal axis of the central pipe 3. The centers of the gas inlet openings 9 are located on a circle with a diameter of d = (0.4 ... 0.7 ) D of the inner diameter of the shell 1, and the outlet openings of the gas ducts 9 are placed in the spaces between the attachment points of the combat elements.

The functioning of the proposed housing cluster warhead missile is as follows.

At a predetermined point in the flight path of the rocket, a burst charge signal is applied, which creates pressure in the cavity between the piston 5 and the supporting disk 7. After the bolts 6 break, the piston 5 begins to move along the shell 1 and pushes out of it a frame 2 consisting of a central pipe 3, front disc 4 and piston 5.

The sealing-damping device 8, made of elastic material and mounted in the peripheral part of the piston 5, prevents the flow of hot gas from the cavity between the piston 5 and the supporting disk 7 into the internal volume of the shell 1 during the movement of the piston 5, eliminates its impact on combat elements. The lack of flow of hot gas allows you to provide the necessary longitudinal force for reliable ejection of the frame with combat elements from the shell. In addition, the impact on the structural elements of the body (piston, frame, explosive bolts, etc.) of the aerodynamic heating of the shell is reduced, damping of possible transverse vibrations during the flight of the projectile occurs, which together increases the reliability of the cassette head of the rocket and its combat effectiveness .

Due to the proposed design of the warhead housing, a directional departure of the frame with combat elements with zero angles of attack is ensured, initial disturbances affecting the dynamics of the movement of elements are excluded. After the frame 2 leaves the shell 1, the incoming air stream passes through the through inclined gas ducts 9 of the front disk 4, changes the nature of the flow around the disk, affects the combat elements by increasing the pressure inside the shell and contributes to their expansion in the radial direction from the longitudinal axis of the central pipe 3.

By choosing the optimal geometric parameters of the gas ducts 9, the reliability of ejection of combat elements from the frame 2 is increased, a uniform and orderly effect of the incoming air flow on the ejection of combat elements is ensured, which reduces the initial disturbances on the combat elements and ensures their predetermined dispersion on the ground.

The specified positive effect is confirmed by flight design tests of samples of the shell of the cluster warhead of a missile shell, made in accordance with the invention.

Claims (1)

A cassette warhead housing of a rocket containing a shell, a frame in the form of a central tube connected to the front disk and a piston in contact with the inner surface of the shell and connected by means of bursting bolts to a support disk rigidly attached to the shell, characterized in that the front disk is uniformly at the same distance from the center, through inclined gas ducts are made at an angle of 25 ° ... 45 ° to the longitudinal axis of the central pipe, the centers of the inlet openings of which are located on a circle with a diameter of 0.4 ... 0.7 in morning shell diameter, and the outlet openings gazovodov placed in between the attachment locations of submunitions, with the piston in its peripheral portion is mounted to engage sealingly with the shell-damping device made of elastic material.