RU2258890C1 - Rocket projectile - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: the rocket projectile has a nose fuse, warhead, self-propelled rocket engine with a nozzle junction box with a bell mouth a bladed tail unit a bell mouth, blade surface. The bell mouth of the nozzle junction is made with an outer cylindrical section with a diameter 0.6-0.7 of the projectile caliber, the tail unit blade attachments are made in the form of two rows of lugs located on the surface of the bell mouth. The tail unit blades are made in the form of two rows of lugs positioned on the bell mouth surface. The surface blades are made in the form of flat plates, in the closed position resting with its side surface on the cylindrical surface of the bell mouth. In the open position the blades are installed with a clearance of 0.15 to 0.25 of the projectile caliber between their side chord and the cylindrical surface of the bell mouth.

EFFECT: enhanced combat efficiency of the projectile and improved its aerodynamic characteristics.

4 dwg

Description

The present invention relates to the field of rocket technology, namely to unguided rockets (NURS), and may find application in the development of new samples of NURS for multiple launch rocket systems (multiple launch rocket systems) land, sea and air based.

To ensure the launch of the NURS are equipped with a contact device, usually located in its rear part and providing the docking of electrical circuits of the launcher (PU) and the projectile.

Known NURS described in "9P138 combat vehicle. Technical description and operating instructions", part 3, book 1 M., Military Publishing House, 1986. It consists of a head fuse, warhead, rocket engine of solid fuel (RDTT), plumage and lids with electrical contacts. The cover is fixed to the nozzle block cut and is relieved by pressure in the engine chamber at the beginning of its operation. Through the contacts on the cover, the starting circuits of the PU and NURS are docked.

Such a contact device, simple in design and highly reliable, is widely used in ground-based NURSs, where the mass of the discarded parts does not matter much. At the same time, with aviation or sea-based NURS, the mass of discarded parts becomes of paramount importance, because they can damage the glider of an aircraft carrier (helicopter or plane) or a superstructure of a sea carrier (ship, boat, etc.), which is completely unacceptable.

Thus, the objective of this technical solution (analogue) was the development of the NURS rather simple and reliable design, but not universal in terms of its application from various types of media.

Common signs with the proposed NURS authors are the presence of a head fuse, warhead, solid propellant rocket engine and plate plumage.

The optimal design of the NURS, providing the possibility of its use from various types of carriers, including aircraft and helicopters, would be the design of the NURS, ensuring the absence of discarded parts in the contact device when it is launched.

The closest in technical essence and the achieved technical result is NURS, described in the catalog "Arms of Russia", t.2, p. 328-329, JSC "Military Parade", M., 1996

The NURS contains a head fuse, a warhead, a solid fuel rocket engine, a nozzle block with a bell placed on it with a folding blade-type tail unit (the ratio of the blade length to its width is ≈10) and a sleeve covering the tail unit with contact devices for transmitting an electrical impulse from PU on the electric igniter of the engine and forcing unit.

The attachment points of the blades are located in the area of the outlet section of the socket, and the contact devices on the sleeve are located behind the cut of the nozzle block.

Closed blades are placed in the body of the socket in through radial grooves, and, partially, in the internal volume of the socket, their rear sections protrude beyond the nozzle block.

When an electric impulse is applied to the solid propellant igniter, the latter fires and ignites the fuel charge, the outflow of gases through the nozzle block begins; the engine enters the mode. Upon reaching the engine thrust of a force equal to the force of forcing, the movement of the NURS along the guide begins, the sleeve remains in the guide, and the blades are kept from opening by the walls of the guide.

At the moment of the projectile descent from the action of the gas flow pressure of the working engine on the end surfaces of the blades, they rotate and fix in the open position, while the sections of the blades that were in the internal volume of the nozzle block bell overlap the grooves.

It should be noted that the use of contact devices on the sleeve, which remains in the guide after starting, to transfer the electric pulse from the PU to the NURS launch circuit, eliminated flying parts and ensured the universality of the use of the projectile from various types of carriers, including airplanes and helicopters.

However, the presence of a part of the blades in the gas stream and the presence of through grooves in the socket (albeit overlapped by the blades) lead to a decrease in thrust due to an increase in gas-dynamic losses when gases flow through the nozzle block.

Due to the inevitable and uneven (within the tolerances on the blade thickness and groove width) clearances in the blade-to-groove joints, part of the gas flows out through these clearances, not participating in the creation of traction, but only increasing the gas-dynamic eccentricity. These factors reduce range and accuracy.

In addition, the gases penetrating through the gaps in the grooves during the movement of the NURS along the guide cause increased corrosion of its inner surface, which reduces the service life of the PU.

Being in the gas stream causes the blades to warm up, which impairs their strength characteristics and can lead to their loss of shape or damage due to aerodynamic loading. To compensate for heating, the blades have an increased thickness, which increases the drag of the projectile and its passive mass, thereby reducing the firing range.

To accommodate the blades in the body of the bell, its diameter is increased almost to the caliber, which leads to the need to place contact devices on the sleeve outside the nozzle block, and this increases the size and weight of the sleeve and nozzle block and reduces the similar parameters of the warhead.

Thus, the well-known NURS (prototype) has significant disadvantages:

- the placement of the blades in the through grooves of the body of the socket affects the ballistic characteristics of the engine and increases the gas-dynamic eccentricity due to the outflow of part of the gas through the gaps between the grooves and the blades, which negatively affects the firing range and accuracy;

- the presence of part of the blades in the gas stream increases gas-dynamic losses, which degrades the characteristics of the engine and also negatively affects the range and accuracy of fire;

- an increase in the thickness of the blade and its mass (to compensate for heating) leads to an increase in the drag of the NURS and a decrease in the firing range;

- the presence of through grooves in the socket and the expiration of part of the gases through them leads to increased corrosion of the guide and reducing its service life;

- the placement of the blades in the body of the bell leads to an increase in its diameter and the need to place contact devices on the sleeve behind its slice, which (for given dimensions and weight) leads to a decrease in the mass of the warhead and a decrease in the combat effectiveness of the NURS.

Thus, the objective of this technical solution (prototype) was to provide the possibility of use in multiple launch rocket systems placed on various carriers, including airplanes and helicopters, but not possessing sufficiently high characteristics and combat effectiveness.

Common signs with the proposed NURS authors are the presence of a head fuse, warhead, solid fuel rocket engine with a nozzle block and a bell with attachment points for the plumage, folding blade empennage and closing the tail unit with contact devices and forcing unit.

Unlike the prototype in the proposed NURS, the nozzle block bell is made with an outer cylindrical section with a diameter of 0.6 ... 0.7 caliber of the projectile, the blade attachment points are made in the form of two rows of protrusions located on the surface of the bell, the tail blades are made in the form of flat plates , in the closed position, resting on the cylindrical surface of the socket, and the contact devices of the sleeve are located in diametrically opposite segments formed by the outer surface of the blades and the inner surface of the sleeve, is in the open position the blades are installed with a gap of 0.15 ... 0.25 caliber projectile chord between their sides and the cylindrical surface of the socket.

It is this that 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 results.

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

The objective of the invention is to increase the combat effectiveness of the NURS by increasing the mass of the warhead by reducing its passive mass, improving the ballistic characteristics of the engine and the aerodynamic characteristics of the projectile.

A new set of structural elements, as well as the presence of connections between the details of the proposed NURS allow by:

a) socket nozzle block with a cylindrical section with a diameter of 0.6 ... 0.7 caliber projectile:

- to exclude the influence of unsteady turbulent disturbances in the boundary layer on the bearing capacity of the plumage blades due to the rotation of the flow into the lowering and the "discharge" of the boundary layer into the lower part;

- reduce the diameter of the socket, and thereby ensure sufficient volume to accommodate the blades and their attachment points, not exceeding the dimensions of the nozzle block;

- to reduce the gas-dynamic eccentricity and losses in the socket due to the exclusion of through grooves in it and the placement of the plumage blades in the gas stream;

- eliminate increased corrosion and wear of the guides;

b) the attachment points of the blades in the form of two rows of protrusions located on the surface of the bell and the tail blades in the form of flat plates, in the closed position resting their side surface on the cylindrical generatrix of the bell:

- increase the side chord of the blade and distribute the aerodynamic load on the blade between the attachment points, thereby reducing the dimensions and weight of these nodes and the thickness of the blade itself, thereby reducing drag and increasing the firing range;

- to locate the contact devices of the sleeve in diametrically opposite segments formed by the outer surface of the blades and the inner surface of the sleeve, which reduces its dimensions and weight, increase the mass of the warhead and increase the combat effectiveness of the NURS;

c) the installation of the feathering blades in the open position with a gap of 0.15 ... 0.25 caliber of the projectile between their side chord and the cylindrical surface of the bell:

- to remove the blades from the boundary layer, which reduces the dispersion of the aerodynamic and ballistic characteristics of the projectile and increases its combat effectiveness;

- reduce the dimensions of the blades without deterioration of their bearing capacity.

Changes in the claimed ratios (the diameter of the cylindrical section of the socket and the gap between the blade and the surface of the cylindrical section) lead to a deterioration in the characteristics of the NURS:

a) the implementation of a cylindrical section with a diameter greater than 0.7 gauge leads to incomplete "drain" of the boundary layer into the lowering, while it is not possible to place the contacts of the liner above the blades;

- the implementation of this section with a diameter of less than 0.6 caliber dramatically increases the drag of the projectile, which reduces the firing range;

b) the presence of a gap between the blades in the open position and the cylindrical section of the bell of less than 0.15 caliber increases the impact on the blades of turbulent pulsations of the boundary layer, as a result of which their bearing capacity decreases and the dispersion of the aerodynamic and external ballistic characteristics of the projectile increases and the accuracy of fire is worsened;

- an increase in this gap in excess of 0.25 caliber leads to a drop in the bearing capacity of the plumage, deterioration of accuracy and a decrease in firing range.

The essence of the invention lies in the fact that in an uncontrolled missile containing a head fuse, a warhead, a solid fuel rocket engine with a nozzle block with a bell, a tail unit that closes the tail unit with contact devices and forcing unit, in contrast to the prototype, according to the invention, a bell the nozzle block is made with an external cylindrical section with a diameter of 0.6 ... 0.7 caliber projectiles, the attachment points of the plumage blades are made in the form of two rows of protrusions located on the surface of the the pipe, the feathering blades are made in the form of flat plates, in the closed position resting their lateral surface on the cylindrical surface of the socket, and the contact devices of the sleeve are located in diametrically opposite segments formed by the outer surface of the blades and the inner surface of the sleeve, while the blades in the open position are installed with a gap 0.15 ... 0.25 projectile caliber between their side chord and the cylindrical surface of the bell.

The invention is illustrated by drawings, where figure 1 shows a General view of the NURS with open feathering blades, figure 2 is a rear view of the nozzle block with a sleeve and closed feathering blades (section AA of figure 1), figure 3 - a local view of the nozzle block with a sleeve and closed feathering blades (section BB of FIG. 2), FIG. 4 is a local section along the fastening and forcing elements of the sleeve (section G-G of FIG. 3).

NURS (figure 1) contains a head fuse 1, warhead 2, rocket engine of solid fuel 3, nozzle block 4 with a bell 5, feathering blades 6, sleeve 7 (figure 3) with contact devices 8 (figure 3).

The bell 5 is equipped with a cylindrical section 9 with a diameter d equal to 0.6 ... 0.7 caliber projectile D (figure 1).

On the cylindrical part of the bell 5 are the attachment points 10 of the plumage blades 6, made in the form of two rows of protrusions 11 and 12 (figure 1).

The plumage blades 6 are mounted on the axes 13 with a clearance a (Fig. 1) between their side chords and the cylindrical section of the bell, equal to 0.15 ... 0.25 caliber of the projectile D.

On the axes 13 are also placed springs "compression-torsion" 14 (figure 1), which serve to open the plumage blades and their fixation in the open position. The sleeve 7 (figure 3) completely closes the feathering blades and through the forcing elements 15 (figure 4) is mounted on the nozzle block 4.

In the closed position, the feathering blades are supported by their lateral surface 16 on the cylindrical surface 17 of the socket 5 (figure 2), and the contact devices 8 of the sleeve 7 are located above the feathering blades (figure 3).

The projectile operates as follows:

Electric voltage through the contact devices 8 of the sleeve 7 and the bundle 18 is transmitted to the igniter 19, which ignites the charge of solid fuel 20 (Fig. 1), after which the outflow of gases through the nozzle block begins and the engine enters the mode. When the engine thrust reaches a value equal to the force of forcing, the elements of forcing 15 (Fig. 4) of the sleeve 7 (Fig. 3) open and the projectile begins to move, the sleeve remains in the guide, and the tail blades 6 (Fig. 1) are kept from opening by the walls guide rail.

When the NURS leaves the guide, under the action of the springs 14, the feathering blades 6 rotate on the axes 13 and, when the locking surfaces 21 and 22 (Fig. 1) coincide, on the blades and protrusions 12 are shifted towards the socket and fixed in the open position.

The proposed design of the projectile allowed to increase the mass of the warhead by ≈20% while maintaining the existing dimensions and mass, as well as to increase the accuracy of fire.

Using the proposed invention, design documentation was developed and a batch of shells for flight tests was made, which confirmed the indicated positive effect.

Currently, flight tests have been carried out, production is being prepared for serial production of the NURS.

Claims (1)

An uncontrolled missile containing a head fuse, a warhead, a solid fuel rocket engine with a nozzle block with a bell, a tail unit that closes the tail unit with contact devices and a forcing unit, characterized in that the nozzle block bell is made with an outer cylindrical section with a diameter of 0 , 6 ... 0.7 caliber projectiles, the attachment points of the plumage blades are made in the form of two rows of protrusions located on the surface of the socket, the plumage blades are made in the form of flat plates, closed the position of their shell resting on their cylindrical surface, and the contact devices of the sleeve are located in diametrically opposite segments formed by the outer surface of the blades and the inner surface of the sleeve, while the blades in the open position are installed with a gap of 0.15 ... 0.25 caliber shell between their side chord and the cylindrical surface of the bell.

Images