RU2247932C1 - Method for launching of jet projectile and complex of armament for its realization - Google Patents

Abstract

FIELD: armament, in particular, methods for launching of the jet projectile.

SUBSTANCE: the method consists in firing of the projectile from the launching tube and subsequent starting of its rocket engine by ignition of the solid propellant charge. A volume isolated from the solid propellant charge and the chamber walls is formed in the chamber of the rocket engine. A charge of pyrotechnical compound is installed and ignited simultaneously with the solid propellant charge. The time of burning of the charge of pyrotechnical compound exceeds the time of burning of the solid propellant charge. A complex of armament for realization of the given method is also offered.

EFFECT: enhanced range of fire of jet projectiles and enhanced reliability of functioning in critical meteorological conditions.

2 cl, 6 dwg

Description

The invention relates to military equipment, and in particular to methods of launching rockets of artillery and missile systems of weapons.

A known method of launching a rocket projectile [1], adopted by the authors as a prototype, comprising ejecting a projectile from a launch tube and then turning on its rocket engine by thermogasdynamic effects of the igniter combustion products on the solid fuel input charge, which is implemented by an armament complex including an launch tube with a launch tube placed in it a rocket engine projectile containing a solid fuel charge, an ignitor and a rocket engine start device. An engine with a face combustion charge, having the highest possible volumetric filling coefficient, provides a missile with an increase in flight range.

However, the specified increase in range is insignificant, because due to the rigid overall-mass restrictions imposed on the projectile as a whole, the charge mass of the rocket engine is quite small, which, as a rule, does not exceed 5-10% of the total mass of the projectile, and its increase under the conditions of these restrictions it is not possible.

Based on practice, it is known that when firing both unguided and guided missiles, after the rocket engine is finished, the aerodynamic drag component sharply increases due to bottom discharge, which leads to a decrease in the flight speed of the projectile in the passive section of the trajectory. At the same time, uncontrolled shells from the influence of crosswind and trajectory disturbances increase dispersion and, as a result, the accuracy of fire, which is one of the main characteristics of the projectile, decreases sharply. In guided missiles, the use of a rocket engine allows you to compensate only for aerodynamic losses that occur when the rudders are deflected, which does not significantly increase the firing range, but increases flight time due to the need for constant formation and passage of compensation commands for trajectory disturbances. In addition, when firing guided missiles in mountainous conditions due to a rarefied atmosphere, the velocity head after the rocket engine stops operating is insufficient to ensure reliable control of the projectile, which ultimately leads to failure and non-fulfillment of the task.

The task of the invention is to increase the firing range of rockets at the same time as preserving the specified overall mass characteristics and increasing the reliability of operation in critical weather conditions.

The solution to this problem is achieved by a method of launching a rocket, including firing a projectile from the launch tube and then turning on its rocket engine by igniting the charge of solid rocket fuel, in which the volume in which the charge is installed is formed in the chamber of the rocket engine in a chamber of the rocket engine from the pyrotechnic composition and ignite it simultaneously with the charge of solid rocket fuel, while the burning time of the charge from the pyrotechnic stavas provide longer burning time of the charge of solid rocket fuel.

The proposed method is implemented by an armament complex, including a launch tube with a rocket engine projectile containing solid rocket fuel in it, an igniter and a launch device, in which the rocket engine is equipped with a pyrotechnic charge made in the form of end-burning checkers placed in metal glasses with a blank bottom, which are placed with emphasis in cylindrical bushings made of composite material, and the charge of solid rocket fuel is made in the form of cylindrical their single-channel checkers.

The formation in the combustion chamber of a rocket engine of a volume isolated from the charge and the walls of the chamber and the placement of a charge from the pyrotechnic composition in it allows preserving the specified overall dimensions of the projectile.

The presence of a charge from the pyrotechnic composition, made in the form of end-burning checkers, the length of which in this case can be selected from the condition:

where L is the length of the end-face checker from the pyrotechnic composition;

D is the outer diameter of a cylindrical single-channel solid rocket fuel charge checker;

d is the channel diameter of the solid rocket fuel charge checkers

на рулях), при этом пиротехнический заряд не создает при горении в камере сгорания ракетного двигателя давления и тяги, что позволяет исключить ветровое рассеивание снарядов и силовое воздействие на элементы их конструкции, а заряд твердого ракетного топлива, выполненный в виде цилиндрических одноканальных шашек, за малое время горения создает высокую тягу, обеспечивая тем самым дополнительный разгон снаряда без существенного отклонения снаряда от действия бокового ветра и воздействия траекторных возмущений.provides a burning time that significantly exceeds the burning time of a solid rocket fuel charge, and when its combustion products are thrown into the atmosphere through the nozzle block of a rocket engine, it allows practically eliminating bottom rarefaction and reducing the aerodynamic drag coefficient of the projectile, which provides a significant increase in flight range. The decrease in the velocity of the projectile due to the action of aerodynamic drag forces is minimal in this case, which ensures the normal operation of the aerodynamic rudders in a rarefied atmosphere (the velocity head increases

on the rudders), while the pyrotechnic charge does not create pressure and traction when burning in the combustion chamber of a rocket engine, which eliminates the wind dispersion of shells and force impact on their structural elements, and the charge of solid rocket fuel, made in the form of cylindrical single-channel checkers, for small the burning time creates high traction, thereby providing additional acceleration of the projectile without a significant deviation of the projectile from the side wind and the impact of trajectory disturbances.

Given that the pyrotechnic compositions have low mechanical strength, the end-burning checkers from the pyrotechnic composition are placed in thin-walled metal cups with a blank bottom, which ensures the efficiency of the pyrotechnic charge under the influence of pressure arising from the combustion of a solid rocket fuel charge. In turn, the placement of metal glasses with an emphasis in cylindrical bushings made of composite material provides protection of the metal walls of the glass from burnout and ease of assembly, since in this case there is no air compression in the closed volume that occurs when the checkers are installed.

The formation of an isolated volume in the combustion chamber of a rocket engine can be performed, for example, by dividing it into separate sectors by blank walls, eliminating the mutual contact of the charge of solid rocket fuel and pyrotechnic charge, which ensures the reliability of the latter. In addition, in this case, only part of the bearing walls of the rocket engine is exposed to the thermal effect of the combustion products of the pyrotechnic composition.

The charge of the pyrotechnic composition is installed in the combustion chamber of a rocket engine with an open end towards the nozzle block. When placing the igniter at the open end of the pieces of pyrotechnic composition, reliable ignition of the charge of solid rocket fuel by a sample of a smaller igniter is ensured, since the pyrotechnic compositions have better flammability than solid rocket fuel, and the pieces of pyrotechnic composition themselves serve as a kind of igniter, which reduces the mass hitch igniter and, as a result, reduce the pressure when you turn on the rocket engine and axial shock overload.

The invention is illustrated in graphic materials. Figure 1-6 presents a diagram explaining the method of firing and the design of the complex and the projectile that implement the proposed method.

Shell 3 (figure 4) consists of a payload and an engine containing a combustion chamber 12, a nozzle block 9 with a sealing plug 10. In the combustion chamber there is a charge of solid rocket fuel 7, made in the form of cylindrical single-channel checkers, and a charge of a pyrotechnic composition 8 made in the form of end-burning checkers placed in metal cups 13 with a blind bottom, which are placed with emphasis in cylindrical bushings 14 of composite material. Checkers 7 charge of solid rocket fuel and checkers of pyrotechnic composition 8 are isolated from each other by partitions 15 (figure 5).

Ignition of the charge is carried out by the igniter 11. From the premature start of the engine when the projectile moves in the launch tube, the igniter and charges are protected by a sealing plug 10.

The number and dimensions of the solid rocket fuel charge checkers and the charge from the pyrotechnic composition are determined in each case by calculation and are specified as a result of experimental testing of the projectile.

The proposed method is implemented as follows. A missile 3 (Fig. 1) is fired from a launch tube 1 (transport and launch container or an artillery gun barrel) mounted on a base 2 (artillery gun carriage, turret of a combat vehicle) using a propelling charge 4 or a launch rocket engine reporting the projectile 3 initial speed. On trajectory 5 (6), a marching or accelerating rocket engine is switched on, which additionally accelerates a rocket (view A, figure 2). After the rocket engine ceased to operate without a pyrotechnic charge, the projectile would continue to fly along trajectory 6. In the proposed method (type B), an igniter 11 (Fig. 4) ignites the charge of solid rocket fuel 7, made in the form of cylindrical single-channel pieces, and the charge of the pyrotechnic composition 8 made in the form of end-burning checkers. The combustion products of the charge of solid rocket fuel 7 and the charge of the pyrotechnic composition 8 are emitted into the atmosphere through the nozzle block 9 of the rocket engine. In this case, the combustion products of the charge of solid rocket fuel create thrust R, providing additional acceleration of the projectile. After combustion of the charge of solid rocket fuel 7, the charge from the pyrotechnic composition 8 continues to burn (the burning time is limited by the value L = (Dd) / 4 (Figs. 2, 3) determined experimentally, where L is the initial charge length, D is the outer diameter of the cylindrical single-channel solid rocket fuel charge checkers, d is the diameter of the solid rocket fuel charge checkers channel) and its combustion products, expiring through the nozzle block 9 of the rocket engine (type B, figure 3), eliminate bottom rarefaction and reduce the projectile resistance coefficient, that increases the flight distance by an amount ΔL ⁺ (trajectory 5, Figure 1).

Thus, the proposed method and complex of weapons for its implementation allows to increase the firing range of rockets, while maintaining their specified overall mass characteristics and the reliability of their operation in critical weather conditions.

Sources of information

1. Patent RU No. 2167385 dated March 6, 2000; Published on May 20, 2001, bull. No. 14 is a prototype.

Claims (2)

1. A method of launching a rocket projectile, including firing a projectile from the launch tube and then turning on its rocket engine by igniting a charge of solid rocket fuel, characterized in that a volume in which the charge is installed is formed in the chamber of the rocket engine and is isolated from the charge of solid rocket fuel and the chamber walls from the pyrotechnic composition and ignite it simultaneously with the charge of solid rocket fuel, while the burning time of the charge from the pyrotechnic composition is provided in excess of m burning time of the charge of solid propellant. 2. An armament complex, including a launch tube with a projectile with a rocket engine containing a solid rocket fuel charge, an igniter and a launch device, characterized in that the rocket engine is equipped with a pyrotechnic charge placed in an isolated chamber volume and made in the form of checkers end combustion, placed in metal cups with a blank bottom, which are placed with emphasis in cylindrical bushings made of composite material, and the charge of solid rocket fuel is fulfilled nen in the form of cylindrical single-channel checkers.

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