RU2674407C1 - Direct-flow rocket projectile - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: invention relates to the ammunition production and use, and can be used in any firearms (infantry, artillery), in the electromagnetic accelerators, as well as for the underwater use. This technical result is achieved by the fact that in a device comprising a housing that externally has a barrel-shaped (oval) shape, inside it has a profiled through hole with two critical sections 1 and 3, between which there is section 2 with the largest expansion. Solid fuel 7 is placed along the walls of the hole, propellant charge 8 and combustible wad 9 after input critical section 1 are placed inside the cavity. Input critical cross section 1 is smaller than output critical cross section 3. Combination of sections 4, 1, 2, 3, 5 forms two opposite Loval nozzles.

EFFECT: technical task of the proposed direct-flow rocket projectile is to increase the range and stability of the projectile’s flight by reducing its aerodynamic resistance and increasing its reactive power, simplifying its design and manufacturing technology.

1 cl, 2 dwg

Description

The invention relates to the production and use of ammunition, and can be used in any firearm (small arms, artillery, etc.), in electromagnetic accelerators, as well as for underwater use.

It is known [1] that in order to increase the projectile range with limited propellant power, it is necessary to reduce the aerodynamic drag of the medium. The scientific and technical literature widely covers the problems of overcoming the resistance forces and improving the aerodynamic characteristics of moving bodies in the environment. One of the components of the resistance forces acting on a moving object is bottom resistance. Bottom resistance arises due to the fact that during the flight of a shell, bullet, rocket, etc. on the passive section of the trajectory in the bottom, a vacuum appears, tending to vacuum. Such a discharge occurs due to blowing (injection) by a stream of medium from the bottom, which leads to a swirl of the stream and to an increase in the drag force. At subsonic speeds of a bullet, projectile, bottom resistance can reach 90% of the total resistance. To reduce bottom resistance, either narrowing the tail of the moving object, that is, reducing the area of the bottom, or installing a gas generator in the tail of the moving object, is used.

The well-known patent RU 2527250, published on 08.27.2014 [2], on “a method for reducing bottom drag and suction of the boundary layer of movable, for example, propelled, bodies in the form of a projectile or bullet with a predominantly lively or pointed nose and a body in the form of a projectile or bullet with a predominantly animated or pointed nose "comprising at least one channel connecting the lateral surface and the bottom of the moving body. The decrease in the bottom resistance of the body in the form of a projectile or bullet is ensured by the suction of the medium, including the boundary layer, from the side surface of this body to its bottom through the said channel. However, the known device does not eliminate the cause of bottom drag, complicates the design and manufacturing technology of the projectile (bullet), and can also lead to a decrease in its flight stability.

Known patent RU 2372581, published 10.11.2009 year [3] on the "cartridge with a reactive bullet." In this patent, a reactive bullet consists of an all-metal body and a propelling charge, which is all located in the cavity of the bullet, and the bullet is mounted in a sleeve. The cavity has the shape of a truncated cone with a pilot hole-nozzle for igniting a propellant charge, which additionally plays the role of a nozzle apparatus. The known device does not eliminate the cause of bottom resistance when a propellant burns out and is not sufficiently stable in flight.

Closest to the invention in design is the patent RU 2497065, published on 10.27.2013, [4], for a “throwing body and wad” comprising a housing that externally has a cylindrical or barrel-shaped and inside has a through hole in the form of a Laval nozzle, consisting of confuser and diffuser. Such a body has a small aerodynamic drag of the shape, on the outside the body flows around tangentially (for a cylinder) or very smoothly (for a “barrel”), and inside the body there is first adiabatic compression in the confuser, and then expansion in the diffuser, which is almost not accompanied by a loss of energy flow. For flight stability, it is proposed to use folding stabilizers. The reasons that impede the achievement of the specified technical result when using the known device include an insufficient decrease in drag and low stability in flight.

The technical task of the invention is to increase the range and stability of the flight of the projectile by reducing its aerodynamic drag and increasing reactive power, simplifying its design and manufacturing technology.

The specified technical result in the implementation of the invention is achieved by the fact that in the device containing the housing, which on the outside has a barrel-shaped (oval) shape, and inside has a profiled through hole with two critical sections 1 and 3, between which there is a section 2 with the greatest expansion. Solid fuel 7 is placed along the walls of the hole, a propellant charge 8 and a combustible wad 9 are placed inside the cavity after the input critical section 1. The input critical section 1 is smaller than the output critical section 3. The combination of sections 4,1,2,3,5 form two onward Loval nozzles .

The device operates as follows. When the propellant charge 8 is ignited, the energy of the compressed gas is transferred to the projectile (bullet). Combustible wad 9 closes the front inlet and accelerates the projectile to muzzle speed. The combustion of wad 9 occurs when a projectile leaves the barrel and at the same time, solid fuel 7 ignites.

During the flight of a projectile (bullet) in the region of section 2, a vacuum appears that tends to vacuum. Such a discharge occurs due to blowing (injection) by a flowing stream of medium (air) through the central part of the channel. A flying projectile in the presence of a vacuum cavity works as a suction turbine, and the grooves 6 in the head part, ensuring its rotation, like an impeller, which ensures an increase in the flow rate of the medium. Thus, the projectile continues to accelerate as a ramjet, which provides a longer flight range.

The proposed invention is illustrated by drawings (Fig. 1, Fig. 2) explaining the device of a direct-flow projectile.

The stabilization of the projectile in flight can be carried out by rotation. In this case, the projectile may have ready-made rifling 6 in the head of the hull. Additional stability in flight is also provided by the interaction of the projectile with the through flow at two spaced points in space (critical sections 1 and 3).

The center of gravity of the projectile is close to the warhead and is located no further than 1/3 of the length of the projectile from its leading edge. For air, the length of the projectile is 2.5-4 caliber, and for the aquatic environment - from 3 to 10 calibers.

The material for the projectile may be metal or ceramic for firearms and / or plastic for an electromagnetic accelerator.

The advantages of the invention are as follows: the range and stability of the projectile are increased, the possibilities of using cartridgeless cartridges both when firing from smoothbore and rifled weapons are expanded; the technology of manufacturing cartridges is simplified, money and raw materials are saved, environmental pollution is reduced.

The claimed technical solution can be implemented in industrial production at the enterprises of the military-industrial complex through the use of well-known standard technical devices and equipment. This meets the criterion of "industrial applicability" presented to the invention.

USED SOURCES

1. S.G. Gubin, S.A. Mount. Ballistics. Electronic textbook. - 562 p.

2. RF patent RU 2527250, IPC B64C 23/00 F42B 10/34, F42B 10/32. Priority from 09/18/2012. Published August 27, 2014. Description of the patent.

3. RF patent RU 2372581, IPC F42B5 / 10 F42B 5/067. Priority from 11/26/2008. Published November 10, 2009. Description of the patent.

4. RF patent RU 2497065, IPC F42B 10/34. Priority from 11/22/2011. Published October 27, 2013. Description of the patent.

Claims (2)

1. A ramjet containing a shell, which is externally barrel-shaped and has a profiled through hole inside, characterized in that the through hole has two critical sections, the input of which has a section smaller than the output, between which there is a section with the greatest expansion, solid fuel is placed in the hole walls, an accelerating charge is placed in the cavity, and a combustible wad is placed after the critical entrance section. 2. The direct-flow missile under item 1, characterized in that its center of gravity is close to the warhead and is located no further than 1/3 of the length of the projectile from its leading edge.

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