RU2217680C1 - Rocket launcher using explosive tubular booster - Google Patents

Abstract

FIELD: military equipment, applicable in designing of rocket launchers. SUBSTANCE: the rocket launcher has a launching barrel in the form of a metal tube, propellant charge, electric primers and a projected body. The propellant charge is positioned in combustion chambers separated by partitions connected by an electric circuit. The electric primers are positioned in the propellant charge, and the last combustion chamber serves as a locking mechanism. The quantity of combustion chambers makes up two and more. A through hollow tube is used as the launching barrel, the tube thickness increases to the place of arrangement of the propellant charge. EFFECT: enhanced range and velocity of rocket flight. 3 cl, 1 dwg

Description

 The invention relates to the field of military equipment and can be used to design grenade launchers in a wide range of tasks.

In determining the level of technology, publicly available information was used that is provided in the following sources of information:
published descriptions of title documents, applications for inventions;
Soviet and other publications available in the library;
messages transmitted via radio, television, cinema, etc.

 The analysis of this information (Copyright certificate of the Russian Federation 2062428, IPC F 41 F 3/045) showed that the well-known, widely used grenade launchers with available specific dimensional and weight characteristics using a jet device allow throwing grenades at a range of several tens to several hundred meters.

 The disadvantages of such grenade launchers include the limited range and accuracy of fire with the established dimensions of the product. In addition, even with significant changes (increases) in the dimensions of grenade launchers, it does not seem technically possible to significantly increase the range of a grenade and, accordingly, the accuracy of fire.

 The problem to which the invention is directed, is the creation of a new type of grenade launchers, which will increase the range and flight speed of the grenade and, accordingly, the accuracy of fire with the existing or reduced dimensions.

 The technical result that can be obtained by using it is that with the previous existing dimensions of grenade launchers, the parameters of the propelled body (weight, volume) increase, i.e. the mass of a throwing grenade increases to the level of widespread use, the throwing speed (up to a thousand meters per second) and the flight range (up to several kilometers) increase; the weight and dimensions of the grenade launcher as a whole are reduced for existing types of grenades with an increase in firing range.

The solution to this problem is achieved by the proposed grenade launcher on a tubular accelerator (hereinafter referred to as Gr VTU K), which includes a launching barrel in the form of a metal pipe, propelling charge, electric igniters and a throwing body, where the propelling charge is placed in partitioned combustion chambers connected by an electric circuit, while electric igniters corresponding to the burning rate condition
n <n (s);
n (s) = V / V (m);
n = n (s) K,
where n is the number of electric igniters;
n (s) is the number of electric igniters corresponding to the explosion;
s is the burning rate corresponding to the explosion;
V (m) is the ignition volume of the propellant charge from one electric igniter per unit time;
V is the volume of the combustion chamber;
K - coefficient from 0.4 ~ 0.9 is set depending on the tasks to be solved, located in a propellant charge, and a hollow pipe is used as a launching barrel, the length of which corresponds to the condition
L = L (zap) N + L (mp) N + L (meth) + PL (met) + L (cgop),
where L is the total length of the channel of the launch tube;
L (zar) is the shell length of the propellant charge;
N - number of combustion chambers from 2 or more;
L (mp) is the thickness of the interchamber partition;
L (meth) is the length of the missile;
P - coefficient from 2 to "C" to stabilize the flight of a missile;
"C" is the pressure of products of complete combustion of a combustible substance from igniters in an amount n, corresponding to the pressure during complete combustion of a given combustible substance from one igniter;
L (cgop) is the channel length corresponding to the complete combustion of a combustible substance,
and the wall thickness is made with increasing to the location of the propellant charge, while the last of the combustion chambers is a locking mechanism. The characteristics of Gr VTU K vary, depending on the tasks to be solved, by changing all the structural elements tied into a single whole.

 In the VTU K Gr offered by us, the grenade is accelerated by filling the launch tube (barrel) with a propellant charge placed in the combustion chambers separated by baffles, while the electric igniters are installed in the propellant charge, the combustion chambers in an amount of 2 or more are connected by an electric circuit, where the latter from combustion chambers is a locking mechanism, which allowed to increase the throwing speed when compressing the propellant charge consumption (reducing the ratio of the weight of the charge of a combustible substance to the weight of a grenade), stitching overall structure size for existing combat performance, increase the weight of garnets, increase the length of the flight path after leaving the launch tube.

 The essence of the invention is shown in the drawing, which shows a General view of Gr VTU K. Starting metal, hollow tube (1) contains a propelling charge in the housing (8), including charges (5) in a metal shell (4) with electric igniters (6), connected electric circuit, combustion chambers (7a, 7b, 7c), separated by inter-chamber partitions (2) under the inner diameter of the pipe (1).

 The grenade (3) is accelerated in the launch tube (1) using a propelling charge (8), including charges (5), the design of which ensures complete combustion of the combustible material from igniters (6), in which the VTU K device does not yet collapse due to an explosion from overload of pressure placed in the combustion chamber (7a, 7b, 7c).

 The proposed device operates as follows.

 After supplying electricity to the VTU K using series-connected electric igniters (6), the combustible substance (5) is simultaneously ignited in the charge housing (4) in the combustion chambers (7a, 7b, 7c). Inside the combustion chambers (7a, 7b, 7c) a pressure is created corresponding to the condition of the burning rate. The combustion products of a combustible substance, which is a gas compressed to a high density, expanding, press on the launch tube (1) and inter-chamber partitions (2). Under the pressure of the gases in the combustion chambers (7a, 7b, 7c), the interchamber baffles (2) are set in motion, while: in the combustion chamber (7a) the interchamber baffle (2) pushes in front of itself a throwable body (3), the other (adjacent to 7b ) presses on the combustion chamber (7b); in the combustion chamber (7b), an interchamber partition (adjacent to 7a) (2) presses on the combustion chamber (7a), another (adjacent to 7c) presses on the combustion chamber (7c); in the combustion chamber (7c) the inter-chamber baffle (adjacent to 7b) (2) presses on the combustion chamber (7b), the last baffle (2) is pushed out of the pipe (1) to the outside. The energy of the combustion chamber (7c) is a locking mechanism. Grenade (3), moving along the channel of the launch tube (1), accelerates. By the time the grenade (3) leaves the pipe body (1), the propellant charge (5) completely burns out. At the end of the pipe (1), the grenade (3) has a maximum speed of movement.

Claims (3)

1. Grenade launcher on an explosive tube accelerator containing a launching barrel in the form of a metal pipe, propelling charge, electric igniters and missile body, characterized in that the propelling charge is placed in partitioned combustion chambers connected by an electric circuit, while the electric igniters are located in the propelling charge, and the last of the combustion chambers is a locking mechanism. 2. Grenade launcher according to claim 1, characterized in that the number of combustion chambers is from two or more. 3. A grenade launcher according to any one of claims 1 and 2, characterized in that a through hollow pipe is used as a launch barrel, the wall thickness of which is made with an increase to the location of the propellant charge.