RU2777720C2 - Bullet with reactive launched cartridge - Google Patents

Abstract

FIELD: armament.

SUBSTANCE: invention relates to the field of armament, namely to a bullet with a reactive launched cartridge. The bullet is connected by means of a bouncing cartridge to a reactive accelerating cartridge, along the axis of symmetry of which a rod fixed in the bottom part of the bouncing cartridge passes, on which fuel checkers sequentially strung on each other are located, made of components with a different combustion speed, pressed in the form of tubes, with a sequentially changing diameter, the inner surface of which is coated with a combustible composition, fixed by an aerodynamically profiled support element mounted on the above-mentioned rod, passing further through the Laval nozzle, in the area of a diffusor of which, on the rod, there is a structural element of a streamlined shape, having a lentil or rhomboid shape in the longitudinal section. The reactive accelerating cartridge has holes. Between the inner surface of a case of the reactive accelerating cartridge and fuel checkers, there is a gap fixed by transverse easily combustible partitions. The bouncing cartridge is equipped with a bouncing charge initiator. In the bouncing cartridge, there is a piston actuated by the bouncing charge, the upper part of which corresponds in a shape to a tail of the bullet. A bouncing cartridge case is made in the upper part in the form of aerodynamically profiled lobes in the form of prongs embracing the bullet. Lobes at a site of maximum bending of side surfaces rest on the inner surface of the case of the reactive accelerating cartridge.

EFFECT: increase in a bullet range due to reduction in aerodynamic resistance.

8 cl, 2 dwg

Description

The invention relates to the field of firearms, in particular to ammunition using jet propulsion.

Known Cartridge with a jet bullet (patent RU No. 2 372 581 C1, published on November 10, 2009 Bull. No. 31) including a cartridge case with a primer and a bullet having a nozzle with an internal cavity in which there is a propellant charge, consisting of several parts having different speeds combustion, placed sequentially along the axis of symmetry of the bullet. This bullet has an internal cavity in which the propellant is located, and a hole in the form of a nozzle. The disadvantage of this bullet is that when parts of the propellant charge burn out, with this variant of their placement, the tail of the bullet becomes lighter, the center of mass of the bullet is significantly shifted, which leads to a deterioration in its ballistics, a decrease in the accuracy of fire.

Also known is a guided active-rocket projectile with a ramjet engine, launched when the fuel is ignited by powder gases generated during firing, developed by Nammo, having movable control rudders in its front part and fixed stabilizers in its rear part.

(The biggest invention since the jet engine [electronic resource]. - URL: https://www.mynewsdesk.com/no/nammo/new/the-biggest-invention-since-the-jet-engine-384591

(Date of access 03/17/2020)). The disadvantage is additional aerodynamic drag from protruding aerodynamic surfaces - rudders and stabilizers, as well as the fact that the design of the engine of this projectile determines that at low altitudes it will work with overexpansion, and at high altitudes - with underexpansion of the jet stream, with the formation of shock waves ( at low altitudes), or rarefaction (at high altitudes) in the diffuser area of the Laval nozzle, as a result of which this nozzle will not work optimally.

Known corrective artillery ammunition "Krasnopol", having a jet engine, or a bottom gas generator, as well as aerodynamic rudders, in particular, armed with a self-propelled howitzer "Coalition-SV", with caseless modular loading, which uses microwave ignition propellant charge. (Double-barreled self-propelled artillery mount (howitzer) 2S36 "Coalition-SV" [electronic resource]. - URL: https://vpk.name/library/f/2c36-koaliciya-sv.html (accessed 13.03.2020)).

Flaws. In the Krasnopol artillery ammunition, as already in the active-rocket projectile discussed above, protruding aerodynamic surfaces - rudders, create additional aerodynamic resistance, which reduces the effective firing range, and the installation of a gas generator (or jet engine) reduces the payload of the projectile - combat weight parts.

The BLAM (Barrel Launched Adaptive Munition) project is known for the development of a universal nozzle for the head of bullets and projectiles - a homing system in which the drive of a controlled aerodynamic surface, which is piezoceramic rods located around a circle at an acute angle to the axis of symmetry of the projectile, a target detector, located inside the head of the bullet (projectile).

(Barrett, Ron. (2011). Adaptive Fight Control Actuators and Mechanisms for Missiles, Munitions and Uninhabited Aerial Vehicles (UAVs). 10.5772/13796. [electronic resource]. - URL: https://www.researchgate.net/figure /Barrel-Launched-Adaptive-Munition-BLAM-Configuration-2311-Setback-Accelerations_fig5_221911988 (Accessed 03/17/2020)). Flaws. The projectile accelerates only in the bore, as given in the above patent RU No. 2 372 581 C1, this acceleration principle gives an efficiency of no more than 30% of the total charge energy used, while the piezoceramic rods are subjected to sharp critical peak loads, which can cause them to be damaged, which can affect the controllability of the projectile.

The objective of the present invention is to create a hypersonic bullet (projectile) with a reactive accelerating cartridge case, superior in terms of performance characteristics to the above analogues. In particular: increasing the flight range of a bullet (projectile) by reducing aerodynamic drag and engineering solutions aimed at optimizing the operation of the Laval nozzle. Also, the solution to the problem of reducing the cost of ammunition when using cheaper materials compared to those used by analogues.

The essence of the invention. A hypersonic bullet (projectile) 2 connected by means of an expelling cartridge with a reactive booster sleeve, along the axis of symmetry of which a rod 11 passes, on which there are fuel cartridges 12 sequentially strung on top of each other, pressed in the form of tubes, with a successively changing diameter, fixed by an aerodynamically profiled support element 8, installed on the above rod 11, passing further through the Laval nozzle 9, in the area of the diffuser of which on the rod 11 there is a structural element of a streamlined shape 10. When the extreme layer of rocket fuel is burned, holes are released in the upper part of the jet booster sleeve, switching the mode of operation of its engine from rocket to air-jet. Fuel pellets 12, in addition to the diameter, may differ from each other in that they are made of components with different burning rates. There may be a gap between the inner surface of the body of the reactive accelerating sleeve 1 and the fuel checkers 12, into which a charge of gunpowder is filled, fixed by transverse easily combustible partitions 7. The means of ignition 6 of the expelling charge 5 in the expelling charge can be a pyrotechnic retarder; mechanical remote tube; an electric igniter or electric detonator powered by a thermal chemical current source, or from a thermoelectric generator battery. The lower part of the knockout cartridge may have a conical shape. The expelling cartridge may have a piston 4 driven by an expelling charge 5, the upper part of which corresponds to the shape of the tail of the bullet (projectile) 2. The bullet (projectile) 2 can be shaped like a wavelet. The inner surfaces of the fuel pellets 12, pressed in the form of tubes, can be coated with metal powders or combustible compositions based on them. A streamlined structural element 10, mounted on a rod 11 in the area of the diffuser of the Laval nozzle 9, may have helical grooves or helical blades on the surface. The body of the booster sleeve 1 and the Laval nozzle 9, in its lower part, can be made of heat-resistant dielectrics. Laval nozzle 9 jet booster sleeve can be made of cermet materials. The initiation of propellant can be carried out by its ignition by electric igniters located around the circumference of the inner surface of the booster case 1, or by electric detonators connected to the contact elements on the outer surface of the rocket case 1; ignition by powder gases generated during firing; microwave radiation. The sleeve of the expelling cartridge can be made in the upper part in the form of aerodynamically profiled petals (prongs) 3, covering the bullet (projectile) 2, while these petals 3, in the place of maximum inflection of the side surfaces, rest on the inner surface of the body of the booster sleeve 1. The rod 11, passing along the axis of symmetry of the reactive accelerating sleeve, can be fixed with its upper end in the bottom part of the expelling cartridge. This bullet (projectile) 2 may have a controlled airfoil drive located inside and a target detector (Barrel-Launched Adaptive Munition (BLAM)). The invention is illustrated by drawings.

In FIG. 1 shows a longitudinal section of a hypersonic bullet (projectile) with a jet fired cartridge case;

In FIG. 2 shows a cross section A-A in FIG. 1 hypersonic bullet (projectile) with a reactive fired cartridge case,

where: 1 jet accelerating sleeve body;

2 bullet (projectile);

3 aerodynamically profiled petals (prongs) of the expelling cartridge case, covering the bullet (projectile);

4 expelling cartridge piston;

5 expelling charge;

6 means of ignition (initiation) of the expelling charge in the expelling cartridge;

7 transverse combustible partitions;

8 aerodynamically profiled support element;

9 Laval nozzle;

10 a structural element with a streamlined shape;

11 rod passing along the axis of symmetry of the reactive accelerating sleeve;

12 fuel checkers.

According to the invention (Fig. 1-2), a hypersonic bullet (projectile) 2 is connected to a reactive accelerating cartridge case by means of an expelling cartridge, from which it is separated after it has run out of rocket fuel, leading to the termination of the rocket engine. Upon reaching the end of the accelerating section of the flight, the expelling cartridge is activated, the charge 5 of which is initiated by the ignition means 6: a pyrotechnic retarder; mechanical remote tube; an electric igniter or an electric detonator powered by a thermal chemical current source, or from a thermoelectric generator battery. This battery is located in the center of the bottom part of the expelling cartridge and its heating is carried out only when the extreme layers of rocket fuel are burned out, which are fuel pellets 12 strung on top of each other, pressed in the form of tubes, with a successively changing diameter. This assembly of fuel pellets 12 is located on the rod 11, passing along the axis of symmetry of the reactive booster sleeve, in the lower part they are fixed by a transverse aerodynamically profiled (diamond-shaped, or lenticular, in cross section) support element 8 in the form of a cross, resting with its ends on the inner walls of the booster jet housing sleeves 1. This cross is installed on the above rod 11 in front of the confuser of the Laval nozzle 9, while the upper part of the rod 11 can be fixed at the bottom of the expelling cartridge, which makes it possible to ensure structural rigidity, which can be increased if the sleeve of the expelling cartridge in the upper part is made in the form of an aerodynamically profiled (diamond-shaped, or lenticular, in cross section) petals (prongs) 3, covering the bullet (projectile) 2, while these petals 3, in the place of the maximum bend of the side surfaces, must rest on the inner surface of the body of the reactive accelerating sleeve 1.

This solution allows you to create a design of a solid-fuel ramjet engine with an axisymmetric input device, where the function of the central body will be performed by a bullet (projectile) 2 located in the expelling cartridge and the assembly of fuel pellets 12 located below, mounted on the rod 11, and the input device is formed by the head part of the bullet (projectile) 2 and the walls of the body of the booster sleeve 1. To ensure reliable obturation in the bore, as well as to bring the ramjet engine to operating power, it is necessary to pre-accelerate the booster sleeve in the rocket engine mode. For this purpose, it is provided that the holes that change the operating mode of the booster sleeve engine from rocket to air-jet are released only when the outermost layer of rocket fuel is burned. Also, it is proposed to use for the manufacture of fuel blocks 12, sequentially strung on top of each other, components having different burning rates. As a solid propellant booster, when launching a reactive booster sleeve in rocket engine mode, colloidal rocket powders or mixed solid propellants with a dibasic binder can be used. For this, a gap is left between the inner surface of the body of the reactive booster sleeve 1 and the fuel checkers 12, into which the charge of gunpowder is poured, fixed by transverse easily combustible partitions 7 that prevent the powder from spilling out (the partition 7 in the lower part of the reactive booster sleeve at the entrance to the Laval nozzle 9, it is advisable to process an igniter composition used to ignite solid rocket propellants, applied as a paste along the contour of the outer layer of fuel (to ensure the sequence of combustion of checkers 12)). As for the fuel pellets 12 pressed into the form of tubes, with a successively changing diameter, it is possible to change the burning rate of the pellets 12, making them from components having different burning rates. Thus, the outermost fuel pellet 12 can be made from mixed propellant with a dibasic binder, modified with an elastomer, which does not crack during long-term storage, and the inner pellets 12 can be made from a composition based on aluminum diboride and dodecaboride, characterized by a higher burning rate and combustion heat.

Korotkikh, A.G. Ignition and combustion of high-energy materials containing aluminum, boron and aluminum diboride / A.G. Korotkikh A.G., V.A. Arkhipov, I.V. Sorokin, E.A. Selikhov // Chemical physics and mesoscopy, vol. 20. - 2018. - No. 1. - S. 5-14.

Starting a rocket engine, for example, in the case of a hypothetical application of the presented invention by a self-propelled howitzer "Coalition-SV", with a caseless modular loading, with a system of microwave ignition of a propellant charge, can be performed in two ways: using a caseless modular propellant charge for additional acceleration, upon initiation of which the resulting powder gases penetrating through the Laval nozzle 9 ignites the propellant inside the body of the rocket booster sleeve 1; another option is that the body of the booster sleeve 1 can be made of heat-resistant dielectrics, for example, polyamide-imide (PAI) or polyetheretherketone (PEEK), while the Laval nozzle 9 can be made of cermet. In the second presented version, the initiation of the extreme layer of rocket fuel can be directly carried out by the microwave ignition system of the howitzer propellant charge, without the use of an additional charge, by microwave radiation penetrating through the walls of the booster case 1, and in order to protect the underlying layers of the missile from premature ignition by microwave radiation. fuel, the inner surfaces of the fuel pellets 12, pressed in the form of tubes, are covered with metal powders, or combustible compositions based on them, shielding microwave radiation. For multiple launch rocket systems, it is provided for the initiation of rocket fuel by its ignition by electric igniters or electric detonators located around the circumference of the inner surface of the rocket cartridge case 1, or electric detonators connected to the contact elements on the outer surface of the rocket cartridge case 1.

Upon actuation of the booster sleeve engine, in rocket mode, the jet stream in the area of the Laval nozzle diffuser 9 is optimized by a streamlined structural element 10 mounted on a rod 11 passing along the axis of symmetry of the above sleeve. This structural element 10 (taking into account the specifics of the nature of its flow, has a lenticular or diamond-shaped (preferably) shape in longitudinal section), allows minimizing shocks (or rarefaction) in the supersonic part of the nozzle 9, which increases its thrust. The above element may have on the surface helical rifling, or helical blades, due to the jet blowing of which the present invention is given rotation around the longitudinal axis, which allows it to be gyroscopically stabilized. After the combustion of the extreme layer of fuel in the upper part of the booster sleeve, holes are released, transferring the operating mode of its engine from rocket to air-jet. The oncoming air flow flows around the protruding pointed head of the bullet (projectile) 2 and then rushes into the annular channel formed by the gap between the expelling cartridge and the inner surface of the body of the reactive accelerating cartridge case 1 (under the condition of using the expelling cartridge having petals (prongs) 3 in the upper part, covering the bullet (projectile) 2, while these petals 3, in the place of maximum bending of the side surfaces, must rest on the inner surface of the body of the reactive accelerating sleeve 1). As a result, the oncoming flow is decelerated and air is compressed, which then enters the combustion chamber (the gap between the inner walls of the body of the booster sleeve 1 and the assembly of fuel blocks 12 mounted on the rod 11), and then the gaseous combustion products of rocket fuel enter the Laval nozzle 9. The assembly of fuel pellets 12 will decrease its diameter more and more during the combustion process, therefore, in order to improve the flow process, the bottom of the knockout cartridge can be given a conical shape. Also, this solution prevents premature operation of the expelling cartridge from being heated by burning fuel cartridges 12, providing heating of only the center of its bottom part.

As discussed above, upon reaching the end of the accelerating section of the flight, the bullet (projectile) 2 is separated from the reactive accelerating cartridge case when the expelling cartridge is fired, the charge 5 of which is initiated by the ignition means 6: a pyrotechnic retarder; mechanical remote tube; an electric igniter or an electric detonator powered by a thermal chemical current source, or from a thermoelectric generator battery. If the bullet (projectile) 2 has a complex shape of the tail, then in the expelling cartridge there may be a piston 4 driven by the expelling charge 5, the upper part of which corresponds to the shape of the tail of the bullet (projectile) 2, while between the bullet 2 and the piston 4 there may be a helical coil spring, which ensures their separation at the exit from the knockout cartridge.

For hypersonic speeds, for a given bullet (projectile) 2, the most optimal is the shape of a waveplane, which can be controlled by a controlled airfoil drive located inside its head and a target detector (Barrel-Launched Adaptive Munition (BLAM)). Targeting can be carried out by radar, or by illuminating the target with a laser beam (Barrett, Ron. (2011). Adaptive Fight Control Actuators and Mechanisms for Missiles, Munitions and Uninhabited Aerial Vehicles (UAVs). 10.5772/13796. [electronic resource]. - URL : https://www.researchgate.net/figure/Barrel-Launched-Adaptive-Munition-BLAM-Configuration-2311-Setback-Accelerations_fig5_221911988 (Accessed 03/17/2020)). The piezoceramic rods used to drive the controlled aerodynamic surface are fragile, have poor resistance to tearing and bending forces, but the use of a jet engine can significantly reduce the recoil force when fired, increasing the safety of their integrity, ensuring high accuracy of hitting the target.

Unlike analogues, the presented hypersonic bullet (projectile) 2, which has a reactive accelerating cartridge case, has a number of advantages:

• The presented invention has two modes of operation of the booster cartridge case engine: rocket and air-jet.

• The jet stream is optimized by a streamlined structural element in the area of the diffuser of the Laval nozzle, mounted on a rod passing along the axis of symmetry of the jet booster sleeve, which allows minimizing shocks (or rarefaction) in the supersonic part of the nozzle, increasing its thrust.

• A streamlined structural element mounted on a rod passing along the axis of symmetry of the reactive accelerating sleeve may have helical grooves or helical blades on the surface, due to the blowing of which by a jet stream, the invention is given rotation around the longitudinal axis, which allows it to be gyroscopically stabilized.

• Consistently strung on top of each other fuel pellets, pressed in the form of tubes, with a successively changing diameter, allow you to provide the specified modes of combustion of various solid rocket fuels, and when they burn out, this layout option minimizes the displacement of the center of mass of the bullet (projectile).

• Preliminary acceleration with modular caseless charges, provision of an accelerating section of the flight by the jet cartridge case engine, giving an additional impulse by the expelling charge, allows to bring the speed of the bullet (projectile) to hypersonic values.

The invention can be used as ammunition for firearms, including those having a microwave propellant ignition system.

Claims (8)

1. A bullet having a reactive booster sleeve, characterized in that the bullet is connected by means of a knockout cartridge with a reactive booster sleeve, along the axis of symmetry of which there passes a rod fixed in the bottom of the knockout cartridge, on which there are fuel checkers successively strung on top of each other, made of components with different burning rates, extruded in the form of tubes with a successively changing diameter, the inner surface of which is coated with a combustible composition, fixed by an aerodynamically profiled support element mounted on the above rod, passing further through the Laval nozzle, in the diffuser area of \u200b\u200bwhich the rod has a streamlined structural element, having a lenticular or rhomboid shape in longitudinal section; jet accelerating sleeve has holes; there is a gap between the inner surface of the body of the reactive accelerating sleeve and the fuel checkers, which is fixed by transverse easily combustible partitions; the expelling cartridge is equipped with an expelling charge initiator, in the expelling cartridge itself there is a piston driven by the expelling charge, the upper part of which corresponds to the shape of the tail of the bullet; the expelling cartridge sleeve is made in the upper part in the form of aerodynamically profiled petals in the form of prongs covering the bullet, while these petals, in the place of the maximum bend of the side surfaces, rest on the inner surface of the accelerating cartridge casing. 2. A bullet according to claim 1, characterized in that the means of ignition of the expelling charge in the expelling cartridge is a pyrotechnic retarder. 3. A bullet according to claim 1, characterized in that the expelling charge is initiated by a mechanical remote tube, or an electric igniter, or an electric detonator powered by a thermal chemical current source or a thermoelectric generator battery. 4. Bullet according to claim 1, characterized in that the lower part of the expelling cartridge has a conical shape. 5. A bullet according to claim 1, characterized in that it has the shape of a wavelet. 6. The bullet according to claim 1, characterized in that the streamlined structural element has helical grooves or helical blades on the surface. 7. The bullet according to claim 1, characterized in that the body of the reactive accelerating sleeve and the Laval nozzle, in its lower part, are made of heat-resistant dielectrics. 8. The bullet according to claim 1, characterized in that the Laval nozzle of the reactive accelerating sleeve is made of cermet materials.

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