RU2082930C1 - Method of rocket shot firing and rocket shot for its realization - Google Patents

Abstract

FIELD: military equipment, in particular, rocket and artillery shots. SUBSTANCE: powder charge gets actuated in launching tube, part of powder charge combustion products is discharged into the atmosphere around the edges of inert mass, and inert mass is separated from launching tube exit section. Rocket shot has launching tube and rocket with engine, launching tube is made with bellmouth on the rear end, and inert mass in the form of rear cover is worked deeper in launching tube. EFFECT: facilitated procedure. 3 cl, 1 dwg

Description

 The invention relates to the field of military equipment, specifically to missile (especially wearable) and artillery weapon systems, including guided ones.

 Known manual anti-tank grenade launcher "Armbrust" [1] the principle of which is as follows. In the central part of the launch tube between the two pistons is a powder charge. In the front of the pipe there is a grenade, and in the rear there is an inert mass of synthetic material, which acts as the energy absorbers of powder gases. During the shot, both pistons move in opposite directions. The front throws a grenade, and the rear pushes an inert mass. When the pipe sections are reached, the pistons stop, preventing the outflow of powder gases. This provides a significant reduction in the sound power of a shot affecting the shooter. However, this grenade launcher, and therefore the method of launching shells, implemented in it, do not meet modern requirements for the range of combat use, since the speed and mass of the projectile being thrown is limited. This is because only half the barrel length is used to disperse the projectile, since the opposite half of the barrel length is used to disperse the inert mass. Moreover, the effective length of the acceleration of the projectile is less than half the length of the barrel due to the area on which the piston is braked and trapped. In addition, the barrel of the grenade launcher is loaded with internal pressure from the actuation of the powder charge and axial forces acting during braking and trapping of the pistons. The mass of the barrel as well as its length for portable weapon systems is limited, since they are subject to the requirements of the minimum weight and dimensions.

 Also, a feathered rocket with a launch tube [2] is also known. The rear end of the launch tube is covered by a lid ejected under the influence of gas pressure from a rocket engine. This device is a missile shot, which implements a method of firing, including the ejection of a projectile and separation (knocking out) of a pipe of inert mass (back cover) from products of charge combustion. In this device, in comparison with the device [1], the entire length of the launch tube is used to disperse the projectile (rocket). However, this missile shot and the firing method implemented therein, when opening the back cover, are a source of a significant shock wave affecting the shooter.

 Satisfying modern requirements for armor penetration and range of combat use, as well as their further increase, require the use of more powerful knock-out charges or pulsed starting engines, from the operation of which the back cover (inert mass) is opened. The resulting shock wave in its characteristics is close to the maximum permissible levels of overpressure and affects the safety and psychophysical state of the shooter and other personnel interacting with him in battle. The problem to which the invention is directed is to increase the safety of the shot by reducing the shock wave that affects the calculation.

 The problem is achieved in that in the method of firing a rocket shot, including projectile discharge and separating the inert mass from the pipe inert mass by the combustion products of the charge, before separating the inert mass from the pipe cut, some of the combustion products are vented to the atmosphere along the inert mass perimeter. The firing method is implemented, for example, by a rocket shot containing a launch tube, a rocket with an engine and a rear cover, in which an expanding bell is made at the rear end of the pipe, while the rear cover is buried in the pipe.

 In addition, the back cover may be located in the inlet section of the socket.

 The drawing shows a diagram of a rocket shot.

 A missile shot includes a launch tube 1 (PT), a rocket with a solid fuel engine 2 (or with a powder charge charge), a back cover (inert mass) 3. At the rear end of the PT, an expanding bell 4 is made, the input section of which is indicated by 5. Some products combustion 6 of the propellant charge of the rocket engine, vented into the atmosphere through an expanding annular gap δ to separate the back cover (inert mass) 3 from the cut 7 of the pipe 1. The extension angle of the bell is marked a. The bursting elements of the cover fastening are indicated by the number 8. The dotted line shows the position of the back cover 3 when it moves in the socket 4.

 The method of firing a rocket shot is as follows.

 When the rocket engine 2 is activated, its nozzles open and the products of the combustion of the powder charge rush to the back cover 3. When the pressure acting on the cover reaches a certain value, the fastening elements of the back cover 3 on the launch tube 1 are destroyed (cut off, torn, snap out), the cover opens and begins to move towards the cut 7 of the pipe 1. The cover 3, passing along the expanding bell 4, opens an annular gap d, gradually expanding as the cover 3 moves along the bell 4. The combustion products of the porous ovogo rocket motor charge rush into this annular gap d, outperform the cover 3 and pitted symmetrically about its perimeter to the atmosphere. In this case, the combustion products, bleed through the annular gap d, interacting with the atmosphere, accelerate the fixed layers of air adjacent to the annular gap. After separation of the cover 3 from the slice 7, a complete cross section of the pipe 1 opens and the main mass of the combustion products of the rocket engine interacts with the atmosphere. This interaction is carried out through pre-accelerated layers of air, which reduces the amount of excess pressure in the resulting shock wave.

 In addition, the smooth bleeding of some of the products of combustion from the projectile space before the back cover 3 passes through the cut 7 of the pipe 1 reduces the pressure of the combustion products at the moment of opening the full cross section of the pipe. It is known that the magnitude of the overpressure of a shock wave is proportional to the pressure of the combustion products interacting with the atmosphere. Reducing the pressure of the combustion products by bleeding part of them before the cover is separated from the pipe cut allows you to reduce the excess pressure in the shock wave propagating beyond the rear cut 7 of the pipe 1, and also to reduce the excess pressure in the shock wave reflected from the inner surface of the cover 3 and directed along the pipe to the side of the shooter’s head when firing from man-portable missile systems.

 In addition, at the moment of opening the back cover 3 in the combustion products of the powder charge of the rocket engine there are fine particles of the products of combustion of the igniter of the powder charge. As a rule, to ignite the powder charges, smoke gun powder is used, the combustion products of which contain up to 50% of solid particles, or pyrotechnic compositions, the combustion products of which also contain a significant amount of solid and liquid particles. When bleeding combustion products containing finely dispersed particles through an annular gap d in the atmosphere adjacent to a pipe section, an annular aerosol layer (cloud) is formed. After the cover 3 is separated from the section 7 of the pipe 1, when its full section is opened, the products of the combustion of the powder charge affect the atmosphere through a layer of medium whose adiabatic index due to the presence of aerosol in it is less than the air adiabatic index, which leads to a drop in the overpressure in the shock wave propagated through a medium containing fine particles.

When making the bell conical to ensure an uninterrupted flow of combustion products when etching along the perimeter of the cover, the angle of the bell should be selected in the range of 20 40 ^o . The bell can be made in the form of a body of revolution, the generatrix of which represents, for example, a part of the parabola branch (paraboloid of revolution).

 Not specified in the description of the operation and structural elements necessary for the operability of a rocket shot are similar to those described in the prototype.

Thus, the proposed method of firing and a missile shot that implements it, allow:
to improve the security of the use of the missile system by reducing the pulse overpressure that affects the combat crew during the shot;
to increase the effectiveness of the use of the complex, especially guided missile weapons, by reducing the psychological stress of the operator after the shot, i.e. during control while aiming a rocket at a target.

Claims (3)

 1. A method of firing a rocket shot, which consists in triggering a powder charge in the launch tube, separating the inert mass from the cut of the pipe, the effect of the combustion products of the powder charge on the atmosphere, characterized in that some of the combustion products are vented to the atmosphere around the perimeter before the inert mass is separated from the pipe cut. inert mass.  2. A missile shot containing a launch tube with a rear cover, a rocket with an engine, characterized in that an expanding bell is made at the rear end of the launch pipe, and the rear cover is buried in the launch pipe.  3. Rocket shot according to claim 2, characterized in that the back cover is installed in the input section of the socket.