RU2670463C1 - Artillery projectile firing range increasing method - Google Patents

Abstract

FIELD: ammunition.SUBSTANCE: invention relates to the ammunition and, in particular, to the artillery shells. Device includes the aft compartment body with the stabilizers unit and the bottom gas generator, the air intake device. Aft compartment body is composed of telescopically located outer and inner shells. After the projectile departure performing the atmospheric air intake for the gaseous mixture afterburning. Transforming the aft compartment body immediately after the projectile departure from the barrel bore. This is performed by the outer shell extension to form the rocket-ramjet engine. Then dumping the outer shell together with the main stabilizers unit and the body part. Opening the additional stabilizers. Their bearing surface is determined taking into account the change in the projectile total mass and the projectile center of mass position after the rocket-ramjet engine operation completion.EFFECT: technical result is increase in the artillery projectile firing range.1 cl, 4 dwg

Description

The invention relates to ammunition, namely: to methods of increasing the flight range of artillery shells and can be used in the development of methods for increasing the flight range and projectiles with increased flight range.

There are two ways to increase the range of artillery shells.

The first of these is to place on board an artillery projectile of a booster engine [R. Oosthuizen, J.J. duBuission, G.F. Botha. Solidfuelramjet (SFRJ) propulsionforartilleryprojectileapplications - conceptdevelopmentoverview // 19th International SymposiumofBallistics, Interlaken, Switzerland, 2001. P. 403-410].

This method allows you to increase the range of artillery projectile by increasing the speed of its flight due to the energy stored in the fuel. Placing onboard a ramjet engine allows air to be used as an oxidizer, however, in this case, a post-combustion chamber of a certain size is required on board the projectile, thereby limiting the amount of payload with a constant projectile dimensions.

Known aerodynamically stabilized projectile, which implemented a telescopic transformation of the airframe during the flight. (application number WO 2001SE0133220010613 "Fin stabilized shell").

This device allows you to increase the volume of the projectile during the flight and due to the shift back block stabilizers to increase the degree of static stability while maintaining the dimensions of the regular projectile during storage. However, the additional free volume obtained during the telescopic transformation remains passive and is not used at all.

Known artillery shell, which implements a method of reducing the bottom resistance. This projectile has a body of tail section of excessive strength for flight regimes with a stabilizer unit and a bottom gas generator producing gaseous products with an oxidizer deficiency. The method of reducing the bottom resistance is realized by supplying additional oxygen due to ejection of the incident flow through the flow regulator, which provides the amount of air ejected into the central zone, proportional to the velocity of the artillery projectile, which allows increasing the interaction area of the gas flows and increasing the efficiency of afterburning of the condensed phase in non-stationary flight conditions . The gas generator in this case is designed to increase the pressure in the area of the bottom cut and thereby reduce the bottom resistance, which ultimately leads to an increase in the range of the projectile. At the same time, a large area of interaction of gas flows contributes to a more complete afterburning of the products formed in the gas generator. Generated jet thrust in this case is negligible (Patent RF №2225976 of 02.12.2002, IPC: F42B 15/00).

The disadvantages are that afterburning of a part of the pyrotechnic composition occurs behind the bottom section of the projectile, which leads to an incomplete use of the energy stored in the pyrotechnic composition, as well as the chemical energy of the air involved in the afterburning process. Also, the projectile on the trajectory has an excessive margin of safety of the body, due to the high level of starting overloads in the bore.

Thus, the energy of the fuel charge of the gas generator is far from being fully utilized, and the capabilities of the shell of the projectile from the standpoint of the strength of the structure is incommensurately higher than is necessary in flight.

There is a method of increasing the range of the artillery projectile, which consists in the fact that after the departure of the projectile containing the body of the aft compartment with a block of stabilizers and a bottom gas generator producing gaseous products with an oxidizer lack, atmospheric air is taken from the bore, which combusts the combustible gaseous oxygen with oxygen, obtained in the gas generator, while the body of the aft compartment is made of a composite of telescopically folded outer and inner shells in flight twice transforming: the first time a transformation is carried out immediately after the projectile leaves the barrel by extending the outer shell with a stabilizer block, ensuring the formation of a rocket-ramjet engine with an afterburner chamber, a gas generator fuel charge, an air intake device and a nozzle, the second time the transformation is performed after the gas generator burns out by returning the outer shell of the hull of the aft compartment to its original position and at the same time close the air intake device (RF Patent No. 252269 9, application No.2012152897 dated December 10, 2012, IPC: F42B 15/00 - a prototype).

This method is implemented as follows.

The artillery projectile includes a body of the aft compartment (KKO) with a block of stabilizers and a bottom gas generator, an air intake device. The hull of the aft compartment is composed of telescopically folded outer and inner shells. After the departure of the projectile, atmospheric air is taken for the afterburning of the gaseous mixture, it is transformed by the ECC immediately after the projectile departs from the bore by extending the outer shell to form a rocket-ramjet engine, then transform the OCC by returning the outer shell to its original position and closing the intake device.

The main disadvantage of this method is the complexity of the design of the projectile, due to the need for a mechanism to return the outer shell to its original position, which leads to a deterioration of its mass-dimensional characteristics. In addition, to stabilize the flight of the projectile as in the initial section, with the charge of the gas generator, and at the final, when the charge has already been used, and with different positions of the center of mass, the same stabilizer unit is used, which worsens the flight characteristics of the projectile.

Technical problem on which the invention is directed, is to increase the range of the artillery projectile by optimizing the design of the projectile, reducing its mass during the flight and selecting the optimal characteristics of the stabilizer block for each flight segment with a working and non-working rocket-ramjet engine.

The solution of this task is achieved by the fact that, in the proposed method of increasing the range of the artillery projectile, containing a hollow body with a block of main stabilizers and aft compartment, a partition is made inside the said body, dividing its cavity into two isolated from each other parts parts of it, place the explosive, and in the second part place the fuel composition with a lack of oxidizer, thus forming the bottom gas generator, consisting of part of the hollow shell of the projectile and the nozzle block, and producing gaseous products with an oxidizer lack, the body of the aft compartment is made of composite telescopically arranged outer and inner shells, and the block of the main stabilizers is placed in the output part of the outer shell, which means that after the projectile is ejected from the barrel, the aft compartment is transformed by axial extension of the outer shell relative to the inner one, ensuring the formation of a rocket-ramjet engine with an afterburning chamber, a gas charge The generator, the air intake device and the nozzle, at the same time, atmospheric air is taken from the surrounding atmosphere, the oxygen of which is burned by the combustible gaseous mixture obtained in the gas generator, after which the resulting combustion products are sent to the said nozzle, thus creating a jet thrust according to the invention, projectile perform with the possibility of undocking its parts between themselves, and the connector node is placed in the second part of the body, while in the second part of the block is placed additional stabil Atorov, which is fixed in the folded state on the partition between the parts, at the same time, after the rocket-ramjet engine ends, the outer shell of the aft compartment is dropped together with the main stabilizers and the inner shell part / the whole of the second part, and then / simultaneously with the discharge a block of additional stabilizers, the bearing surface of which is determined taking into account the change in the total mass of the projectile and the position of the center of mass of the projectile after the rocket-ramjet engine ends.

The invention is illustrated by the drawings, where in FIG. 1 shows a schematic diagram of an artillery shell before exiting the barrel; in fig. 2 shows a cross section in the region of the air intake devices in FIG. one; in fig. 3 shows a diagram of an artillery shell after the first transformation of the corps; in fig. 4 is a diagram of the artillery shell after the outer shell is dropped.

The proposed method can be implemented using a projectile having the following structure.

The body of the projectile is made of inner 1 and outer 2 coaxially installed shells. Shell 2 is configured to axially move relative to shell 1. A block of main stabilizers 3 and air intake devices 4 are installed on the outer shell 2. Intake devices 4 together with the outer shell 2 and a nozzle 5 located in the output part of the outer shell 1 form the second circuit rocket-ramjet engine, the principle of which is as follows. The gas formed during the combustion in the bottom gas generator 6 of a special solid fuel containing a significant amount of unburned particles enters the engine chamber and, burning out, mixes with the air flow that enters the chamber through the air intake devices 4. The bottom gas generator 6 with the nozzle unit 7, which is the first contour rocket-ramjet engine installed inside the inner shell 1. The hull is divided into two parts: the first 7 with the explosive charge and the second with the bottom gas generator 6 using partitions 8. Inside the cavity of the second part, a connector assembly of the housing parts 9 is installed. A partition of additional stabilizers 10, which are in the folded state, is installed on the partition 8.

The proposed method can be implemented using the specified projectile as follows.

At the time of the shot, the projectile is dispersed in the barrel of the artillery gun, while the inner and outer shells 1 and 2, respectively, jointly perceive the resulting axial overload. After the projectile leaves the bore, the outer shell 2 is shifted back relative to the direction of the projectile, while the main aerodynamic stabilizers 3 and air intake devices 4 are opened, which together with the outer shell 2 and nozzle 5 form the second circuit of the rocket-ramjet engine.

In the bottom gas generator 6, which represents the first circuit of the rocket-ramjet engine, ignites the fuel composition with the lack of an oxidizer, after which the products of incomplete combustion of fuel begin to flow into the second circuit. Using intake devices 4 produce atmospheric air intake and use it to afterburn in the second circuit the gaseous products coming from the primary circuit, which then expire through the nozzle 5 of the second circuit, creating a jet thrust.

After the end of the bottom gas generator 6, the need for an outer shell 2 and the second part of the body disappears. In this case, a command is given to trigger the mechanism of the connector assembly 9, after which a part of the second part’s body / second part’s body is separated from the body of the projectile along with the outer shell 1 and the main stabilizer unit 3. Simultaneously, additional stabilizers 10 are revealed.

Resetting these parts will increase the speed of the projectile, by reducing its mass, and the exclusion of the mechanism for returning the outer shell 2 to its original position will simplify its design.

The use of the proposed technical solution will allow increasing the range of the artillery projectile by optimizing the projectile design, reducing its mass during the flight and selecting the optimal characteristics of the stabilizer block for each flight segment — with a working and non-working rocket-ramjet engine.

Claims (1)

A method for increasing the range of an artillery projectile containing a hollow body with a block of main stabilizers and a fodder compartment, with a partition inside the said body dividing its cavity into two parts isolated from each other, with an explosive in one of its parts place the fuel composition with a lack of oxidizing agent, thus forming a bottom gas generator, consisting of a part of the hollow shell of the projectile and the nozzle block, and producing gaseous products with a disadvantage lump of oxidizer, while the body of the aft compartment is made of a composite of outer and inner shells located telescopically, and the block of the main stabilizers is placed in the output part of the outer shell, which consists in transforming the body of the aft compartment by axial extension of the outer shell relation to the internal one, ensuring the formation of a rocket-ramjet engine with an afterburning chamber, the fuel charge of the gas generator, the air intake device and the nozzle, while Atmospheric air is collected at atmospheric air, the oxygen of which burns the combustible gaseous mixture obtained in the gas generator, after which the resulting combustion products are sent to the said nozzle, thus creating jet thrust with the possibility of uncoupling its parts , moreover, the connector assembly is placed in the second part of the housing, while in the second part, a block of additional stabilizers is placed, which is fixed in the folded state to the burst Ke between the parts, at the same time, after the rocket-ramjet engine is finished working, the outer shell of the aft compartment is dropped together with the main stabilizers block and the inner shell part / the whole of the second part, after which / simultaneously with the discharge they open the block of additional stabilizers, the bearing surface of which is determined taking into account the change in the total mass of the projectile and the position of the center of mass of the projectile after the completion of the rocket-ramjet engine.

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