RU2751311C1 - Method for increasing the flight range of active-reactive projectile and active-reactive projectile with monoblock combined engine unit (versions) - Google Patents

Abstract

FIELD: weaponry.SUBSTANCE: group of inventions relates to a method for increasing the flight range of an active-rocket projectile and to variants of an active-rocket projectile. Disclosed is a method for increasing the flight range of an active-rocket projectile containing a propulsion system with a solid fuel charge located in the rear part of the projectile, a bottom with nozzle inserts located in a circle around the longitudinal axis of the projectile, and a shell of the afterburner chamber. The method consists in the fact that the movement of an active-rocket projectile in the gun barrel is carried out under the influence of the pressure of the combustion products of the propellant charge. Some propellant charge combustion products are passed through the bottom nozzle liners into the cavity of the propulsion system to ignite the solid fuel charge. Further, after the projection of the active-rocket projectile from the bore of the gun barrel, the products of the primary combustion of solid fuel flow through the support tube-gas pipe into the space formed by the diaphragm and the bottom, and then through the nozzle inserts into the volume limited by the bottom and shell of the afterburner chamber, which forms the afterburner and is open from the side of the bottom cut of the projectile. The nozzles of the nozzle inserts are profiled tapering towards the center from their both ends with the possibility of creating thrust during the outflow of the products of the primary combustion of the solid fuel and passing part of the products of the combustion of the propellant to ignite the charge of the solid fuel. Afterburning of the primary combustion products of the fuel flowing out through the nozzle inserts nozzles is carried out in the air flow entering the afterburning chamber from the vortex flow formed during the supersonic flow around the active-rocket projectile in flight.EFFECT: technical result consists in providing conditions for creating thrust by the propulsion system while reducing the force of the aerodynamic resistance of the projectile and, as a consequence, in increasing the range of the projectile.5 cl, 7 dwg

Description

The invention relates to ammunition, in particular to long-range artillery projectiles equipped with a propulsion system (active-rocket projectiles).

The known design of an active-rocket projectile with a ramjet engine for guns with a rifled barrel (patent RU 2711208, 01/15/2020). In the known design, an emphasis is placed on providing tractive effort due to the afterburning in the atmospheric air of the primary combustion products of a solid fuel charge coming from the gas generator to the afterburner, which is equipped with a system that changes its geometry and increases the useful volume of the afterburner after the active-reactive projectile is ejected from the barrel. tools. At the same time, it has a number of characteristic features aimed at maximizing the completeness of the afterburning of the products of the primary combustion of solid fuel in order to ensure the most complete use of the energy stored in the fuel and to maximize the thrust of the propulsion system. These design features include: an elongated afterburner, formed after the launch of an active-rocket projectile from the gun; an annular air intake device that supplies atmospheric air to the afterburner; perforation on the wall of the shell of the afterburner chamber, which provides additional air flow due to the ejection effect of jets of primary combustion products of solid fuel flowing out of the gas generator.

The disadvantages of this design are, firstly, high complexity and a large number of elements in the engine. The presence of moving parts in a projectile subject to high G-forces when fired makes it less reliable, because in the process of firing, deformation and jamming of moving elements are possible. Secondly, since an active-rocket projectile is an aircraft with a dominant passive trajectory segment, special attention should be paid to its aerodynamic appearance. The presence of protruding parts, such as an air intake, inevitably leads to an increase in the aerodynamic drag force acting on the projectile. In addition, the weighting of the tail section of the gyroscopically stabilized projectile can lead to its imbalance and loss of gyroscopic stability, especially when the moving elements of the afterburner chamber are displaced backward relative to the center of mass of the projectile.

Known artillery projectile equipped with a combined propulsion system, consisting of a bottom injection gas generator and a solid-propellant rocket engine, operating sequentially on the ascending branch of the projectile trajectory, thereby achieving an increase in the flight range (CN000102155879A. 17.08.2011). In this case, the bottom injection gas generator provides a decrease in the aerodynamic resistance of the projectile by increasing the pressure on its bottom cut, and the rocket engine creates a thrust. The advantage of this design over the previous one is the absence of protruding parts and, therefore, less aerodynamic drag. The disadvantage of this design is the use of two power plants in series: first to reduce aerodynamic drag, then to create thrust. This leads to increased requirements for the internal volume of the projectile to accommodate a combination of two power plants, and, consequently, a decrease in the volume for the payload with fixed projectile dimensions.

The closest technical solution to the claimed invention is an artillery projectile using a bottom injection gas generator to reduce aerodynamic drag and increase the flight range (JP000H06147798A, 05/27/2004). In this case, one of the versions of this design implies the use of a gas generator in combination with a relatively short afterburner with holes of a sufficiently large area in the side wall, through which air is supplied to the products of the primary combustion of the gas generator charge and their completeness of afterburning increases, and, consequently, the pressure on bottom cut of the projectile. Air enters these holes under the action of a vortex flow formed when a supersonic air stream flows around the side wall of a projectile with a hole. The advantage of this design is the structurally simple design of the air supply system to the products of the primary combustion of solid fuel due to a known physical phenomenon.

The disadvantages of this design are the absence of a traction force created by the power plant, and the high probability of a reverse flow of combustion products through the air intake openings into the atmosphere as the pressure in the chamber increases, i.e. high risk of surge. The use of the bottom blowing gas generator (bottom gas generator) provides the supply of the products of the primary combustion of the solid fuel charge to the area behind the projectile. In this region, with a supersonic air flow around the projectile, a vortex rarefaction zone is formed, in which the pressure is significantly lower than atmospheric. The bottom injection gas generator is designed to fill this rarefaction zone with hot gas in order to increase the pressure on the bottom of the projectile and, as a result, reduce its aerodynamic resistance, while the bottom injection gas generator does not create thrust as such. In JP000H06147798A, a conventional bottom injection gas generator is supplemented with a chamber with side windows, through which air must flow to the fuel combustion products, while their afterburning and additional heat release must be ensured, as a result of which the pressure on the bottom cut of the projectile must increase.

The technical problem solved by the group of inventions is to increase the flight range of an artillery projectile using a propulsion system, which simultaneously reduces the aerodynamic resistance of the projectile and creates thrust.

The claimed method of increasing the flight range of an active-rocket projectile containing a propulsion system with a solid fuel charge, located in the aft part of the projectile, a bottom with nozzle inserts and a shell of the afterburner chamber, consists in the fact that the movement of an active-rocket projectile in the gun barrel is carried out under the influence of pressure combustion products of the propellant charge, while part of the combustion products of the propellant charge is passed through the nozzle liners of the bottom into the cavity of the propulsion system to ignite the solid fuel charge, then after the release of the active-jet projectile from the bore of the gun, the products of the primary combustion of the solid fuel flow through the support tube-gas duct into the space formed by the diaphragm and the bottom, and then through the nozzle liners into the volume bounded by the bottom and the shell of the afterburner chamber and open from the side of the bottom cut of the projectile, and the nozzle liner nozzles are profiled tapering towards the center from both ends with the possibility creating thrust during the outflow of the primary combustion products of solid fuel and passing part of the combustion products of the propellant to ignite the solid fuel charge, and the afterburning of the primary combustion products flowing through the nozzle insert nozzles is carried out in the air flow entering the afterburner from the vortex flow formed during supersonic flow around an active-rocket projectile in flight.

The technical result, provided by the method of increasing the flight range of the active-rocket projectile, is to provide conditions for creating thrust by the propulsion system while reducing the force of the aerodynamic resistance of the projectile and, as a consequence, increasing the flight range of the projectile due to this.

The declared active-rocket projectile, eliminating the disadvantages of the closest analogue, contains a warhead with a payload, a propulsion system located in the aft part of the projectile and containing a fuel charge, a leading belt, a support gas pipe, a diaphragm, a bottom with nozzle inserts and a shell of the afterburner ... The above technical problem within the framework of the claimed invention - the projectile is solved due to the fact that the propulsion system, which, during operation, provides a simultaneous decrease in aerodynamic resistance and the creation of thrust, consists of a solid fuel charge, a support gas pipe, a diaphragm, a bottom, nozzle inserts and a chamber shell afterburning, while the propulsion system combines the properties of both a bottom injection gas generator (reducing aerodynamic drag by increasing pressure on the bottom of the projectile) and a solid fuel rocket engine (creating thrust due to the outflow of high-speed jets from the combustion chamber), while both of these properties manifest themselves during the operation of the propulsion system at the same time, and the propulsion system itself has one single source of the working fluid (charge of solid fuel). Thus, the claimed invention can be attributed to active-rocket projectiles with a monoblock combined propulsion system.

The technical result achieved when using the claimed design of an active-rocket projectile is to increase the flight range of the artillery projectile while reducing the aerodynamic resistance of the projectile and creating thrust due to the outflow of high-speed jets from the combustion chamber.

The specified technical result is achieved due to the fact that when fired from a gun with a rifled barrel in the process of movement along the barrel, an excess pressure of high-temperature combustion products of the propellant charge acts on the bottom of the projectile, which through the nozzle liners enter the combustion chamber of the propulsion system and ignite the solid fuel charge. Excessive pressure of the propellant charge combustion products provides a supersonic initial velocity of the projectile. Ignition of the solid fuel charge leads to the outflow of the products of its primary combustion through the nozzle inserts into the space behind the bottom cut of the projectile. Due to the supersonic speed of the projectile at the initial stage after departure from the bore, the vortex air flow arising behind the bottom cut of the projectile tends to fill the volume between the shell of the afterburner chamber and the bottom, which serves as an afterburner through which jets of primary combustion products of solid fuel pass. Once in the rarefied space of the afterburner, the jets of the primary combustion of solid fuel are blurred, while the part of the jet closest to its axis continues to move in the direction opposite to the direction of flight, and the peripheral part of the jet mixes with air entering the afterburner from the vortex flow after by the bottom cut of the projectile, it is burned out and fills the space of the afterburner chamber, providing an increase in the bottom pressure and a decrease in the total aerodynamic resistance of the active-rocket projectile. Part of the products of the primary combustion of solid fuel is retained in the afterburner, forming, together with the atmospheric air entering from the periphery of the afterburner, a vortex flow in which the afterburning takes place. This is facilitated by the location of the nozzle inserts around the circumference at a certain distance from the axis of the active-rocket projectile, which ensures that the area of the bottom cut of the projectile is filled with jets of solid fuel primary combustion products and the formation of vortex zones in which the products of the primary combustion of solid fuel are burned out, mixing with air, in contrast from a design with one central nozzle, which allows the products of the primary combustion of a solid fuel charge to occupy a relatively small fraction of the area of the bottom cut of an active-rocket projectile. The combination of these effects (creation of thrust with a simultaneous decrease in aerodynamic drag) provides an increase in flight range.

Essential features that ensure the achievement of the specified technical results for the method and the projectile is the implementation on the bottom of the nozzle inserts located circumferentially around the longitudinal axis of the projectile, while the nozzles of the said nozzle inserts are profiled tapering towards the center from both ends with the possibility of creating thrust when the products of the primary solid fuel combustion and passing part of the propellant charge combustion products to ignite the solid fuel charge, and the afterburning of the primary fuel combustion products flowing through the nozzles of the nozzle liners is carried out in the air flow entering the afterburner from the vortex flow formed during supersonic flow around an active jet projectile in flight.

The essence of the invention is illustrated by drawings, where:

in fig. 1 shows a general view of an active-rocket projectile with a monoblock combined propulsion system;

in fig. 2 shows the propulsion system itself;

in fig. 3 is a rear view of a monobloc combined propulsion system showing the location of the nozzle inserts around the longitudinal axis of the projectile;

in fig. 4 shows a schematic diagram of the afterburning of the products of the primary combustion of solid fuel in a propulsion system.

in fig. 5 shows an embodiment (modification) of a monoblock combined propulsion system, in which the diameter of the afterburner in the area of the bottom is smaller than in the area of the end of the projectile, and the change in diameter is made in the form of a series of step transitions.

FIG. 6 shows an embodiment (modification) of an active-rocket projectile with a monoblock combined propulsion system using stabilization by the tail.

FIG. 7 shows a fragment of a variant of an active-rocket projectile, in which the plumage is opened after the projectile has left the bore.

In the drawings, the numbers indicate:

1 - head part;

2 - leading belt;

3 - monoblock combined propulsion system;

4 - the body of the monoblock combined propulsion system;

5 - charge of solid fuel;

6 - support tube-gas conduit;

7 - diaphragm;

8 - bottom;

9 - nozzle inserts of the monoblock combined propulsion system;

10 - shell of the afterburner chamber;

11 - step transitions of the afterburner chamber;

12 - obturating belt;

13 - deployed plumage;

14 - mounting places for the deployed tail.

The reactive projectile (Fig. 1) consists of a head part 1, which houses a payload (for example, an explosive charge, a fuse, a trajectory correction unit, etc.), a leading belt 2 and a monoblock combined propulsion system 3.

Monoblock combined propulsion system (Fig. 2) consists of a body 4 of the propulsion system, a solid fuel charge 5, a support tube-gas conduit 6, a diaphragm 7, a bottom 8, nozzle inserts 9 and a shell 10 of the afterburner chamber. The charge of solid fuel 5 is installed on the support tube-gas conduit 6 and inside the housing 4 with the smallest possible gap.

Diaphragm 7, bottom 8 and shell 10 of the afterburner chamber are connected to the body 4 by means of threaded connections. The nozzle inserts 9 are made of heat-resistant material and are installed in the bottom 8 using threads or glue-sealant. The nozzle inserts are located around the circumference at a certain distance from the longitudinal axis of the projectile (Fig. 3). Such an arrangement, according to the numerical simulation of the mixing of the products of the primary combustion of solid fuel with air and their afterburning in the afterburning chamber, carried out according to the known technique, provides the necessary operating mode for the monoblock combined propulsion system. The studies were carried out in the ANSYS CFX computational fluid dynamics package with simulation of the outflow of jets of primary combustion products into the space behind the projectile and taking into account their afterburning according to the one-stage one-parameter combustion model Eddy Dissipation Model.

The declared active-rocket projectile functions as follows.

When fired from a gun with a rifled barrel, the combustion products of the propellant charge affect the bottom of the active-rocket projectile, consisting of the head part 1, the leading belt 2 and the monoblock combined propulsion system 3 (Fig. 1). Under the influence of the pressure of the combustion products of the propellant charge, the active-rocket projectile receives accelerated forward movement along the bore. In this case, the leading belt 2, rigidly connected to the projectile, when interacting with the grooves in the bore of the gun, imparts to the projectile a certain angular acceleration required for gyroscopic stabilization of the projectile in flight.

In the process of movement along the barrel, an excess pressure of the high-temperature combustion products of the propellant charge acts on the bottom of the projectile. In this case, the nozzle liners 9, which are part of the monoblock combined propulsion system 3, play the role of gas reducers, passing part of the combustion products of the propellant charge into the cavity of the propulsion system, providing a level of temperature and excess pressure inside the propulsion system sufficient to ignite the solid fuel charge 5, but insufficient for its destruction or off-design burnout. After the departure of the active-rocket projectile from the bore of the gun, further combustion of the solid fuel charge 5 occurs with the outflow of the primary combustion products through the support tube-gas conduit 6 into the space formed by the diaphragm 7 and the bottom 8, and then through the nozzle inserts 9 into the volume bounded by the bottom 8 and shell 10 of the afterburner chamber and open from the side of the bottom cut of the projectile. The nozzle inserts 9 are shaped so that the jets of the products of the primary combustion of solid fuel, flowing out through them, accelerate and create a certain thrust force. Since the projectile begins to move at a high supersonic speed, a vortex air flow is formed behind its bottom cut, tending to occupy the volume limited by the shell 10 of the afterburner chamber and the bottom 8, which forms, in fact, the afterburner through which jets of primary combustion products of solid fuel pass. Once in the rarefied space of the afterburner, the jets of the primary combustion of solid fuel are blurred, while the part of the jet closest to its axis continues to move in the direction opposite to the direction of flight, and the peripheral part of the jet mixes with air entering the afterburner from the vortex flow after by the bottom cut of the projectile, it is burned out and fills the space of the afterburner chamber, providing an increase in the bottom pressure and a decrease in the total aerodynamic resistance of the active-rocket projectile.

An illustration of this effect based on numerical simulation data is shown in FIG. 4. It is shown that a part of the products of the primary combustion of solid fuel is retained in the afterburner, forming, together with the atmospheric air entering from the periphery of the afterburner, a vortex flow in which the afterburning takes place. This is facilitated by the location of the nozzle inserts 9 at a certain distance from the axis of the active-jet projectile, i.e. with a displacement relative to the longitudinal axis of the projectile, mainly along the circumference, which ensures filling the area of the bottom cut of the projectile with jets of the primary combustion of solid fuel and the formation of vortex zones in which the products of the primary combustion of solid fuel are burned out, mixing with air, in contrast to the design with one central a nozzle that allows the products of the primary combustion of a solid fuel charge to occupy a relatively small fraction of the area of the bottom cut of an active-rocket projectile.

The combination of these effects (creation of thrust with a simultaneous decrease in aerodynamic drag) provides an increase in the flight range of an active-rocket projectile.

One of the important features of the described active-rocket projectile is the presence of vortex zones near the bottom 8 (see Fig. 4), in which the afterburning of the products of the primary combustion of solid fuel, which increases the pressure on the bottom 8 of the projectile. It is known that vortex zones are formed in the area of a sharp change in the cross-sectional area of the afterburner. In this regard, the proposed modification of the monoblock combined propulsion system (Fig. 5). In this modification, the diameter of the afterburning chamber in the bottom area is smaller than in the area of the end of the projectile, and the change in diameter is made in the form of a number of step transitions 11. In the places of these step transitions 11, stagnant vortex zones are formed, in which a mixture of primary combustion products of solid fuel and air is retained , which provides an increased completeness of afterburning in comparison with the design shown in FIG. 2. An increase in the completeness of afterburning means a further increase in pressure on the bottom 8 of the active-rocket projectile and a greater increase in the flight range.

The above-described designs of an active-rocket projectile with a monoblock combined propulsion system refer to projectiles fired from guns with a rifled barrel and stabilized by rotation. However, the monoblock combined propulsion system itself can also be used on projectiles stabilized by the empennage. A variant of the claimed invention can be a modification of the active-rocket projectile with a monoblock combined propulsion system 3, using stabilization by the tail (Fig. 6). The plumage is revealed after the projectile leaves the bore (Fig. 7).

In this embodiment of the active-rocket projectile, it consists of a head part 1, an obturating band 12, a monoblock combined propulsion system 3 and a deployable tail 13. From the active-rocket projectile shown in FIG. 1, this embodiment is characterized in that the occluding band 12, in contrast to the leading band 2 shown in FIG. 1, is not rigidly connected to the housing 4 of the propulsion system 3, but is installed on it as a freely rotating ring, which ensures the obturation of the powder gases when fired, but does not impart a high rotation speed to the projectile. In this case, the design of the propulsion system 3 has been modified in such a way as to provide the possibility of installing the obturating belt and its attachment. In addition, in the shell 10 of the afterburner chamber, mounting places 14 are made for the openable tail 13 of the knife type, allowing it to fold into the cavity formed by the bottom 8 and the shell 10 of the afterburner. Thus, the plumage 13 is protected from deformation during storage and transportation of the projectile and does not violate the restrictions on the overall dimensions of the active-rocket projectile.

Claims (5)

1. A method of increasing the flight range of an active-rocket projectile containing a propulsion system with a solid propellant charge located in the aft part of the projectile, a bottom with nozzle inserts located in a circle around the longitudinal axis of the projectile, and a shell of the afterburner chamber, which consists in the fact that the movement is active -reactive projectile in the gun barrel is carried out under the influence of the pressure of the propellant charge combustion products, while part of the propellant charge combustion products are passed through the nozzle liners of the bottom into the cavity of the propulsion system to ignite the solid fuel charge, then, after the active-rocket projectile leaves the gun barrel bore, the products of the primary solid fuel combustion flows through the support tube-gas pipe into the space formed by the diaphragm and the bottom, and then through the nozzle inserts into the volume bounded by the bottom and the shell of the afterburner chamber, which forms the afterburner and is open from the side of the bottom cut of the projectile, and the nozzle is a nozzle outlets are profiled tapering towards the center from their both ends with the possibility of creating thrust at the outflow of the products of the primary combustion of solid fuel and passing part of the combustion products of the propellant to ignite the charge of solid fuel, and the afterburning of the products of primary combustion of the fuel flowing out through the nozzles of the nozzle inserts is carried out in the flow air entering the afterburner from the vortex flow formed during supersonic flow around an active-rocket projectile in flight. 2. Active-rocket projectile containing a warhead for a payload, a propulsion system located in the aft part of the projectile and containing a charge of solid fuel, a leading belt located on the body of the propulsion system, a support tube-gas conduit, a diaphragm, the bottom and a shell of the afterburner chamber, characterized in that the afterburner chamber is formed by a volume limited by the bottom and shell of the afterburner chamber, while the bottom is equipped with nozzle liners located circumferentially around the longitudinal axis of the projectile, communicating the space between the diaphragm and the bottom with the afterburner chamber, and the nozzle liner nozzles are profiled tapering towards the center from both ends with the possibility of creating thrust during the outflow of the products of the primary combustion of the solid fuel and passing part of the combustion products of the propellant charge to ignite the solid fuel charge. 3. The reactive projectile according to claim 2, characterized in that the bottom and shell of the afterburner chamber are articulated with a stepped transition. 4. An active-rocket projectile containing a warhead for a payload, a propulsion system located in the aft part of the projectile and containing a solid fuel charge, an obturating belt, a support gas pipe, a diaphragm, the bottom and a shell of the afterburner chamber, characterized in that the obturating belt made in the form of a ring mounted on the body of the propulsion system with the possibility of rotation; the afterburner chamber is formed by a volume limited by the bottom and shell of the afterburner chamber, while the bottom is equipped with nozzle inserts located circumferentially around the longitudinal axis of the projectile, communicating the space between the diaphragm and the bottom with the afterburner, and the nozzle insert nozzles are profiled tapering towards the center from both ends with the possibility of creating thrust during the outflow of the products of the primary combustion of solid fuel and passing part of the combustion products of the propellant charge to ignite the charge of solid fuel, in addition, the projectile is equipped with a deployable empennage installed in the cavity formed by the bottom and shell of the afterburner chamber, and made with the possibility of discharge through the mounting places , made in the shell of the afterburner. 5. The reactive projectile according to claim 4, characterized in that the bottom and shell of the afterburner chamber are articulated with a stepped transition.

Images