RU2217618C1 - Rocket for grenade launched by grenade launcher - Google Patents

Abstract

FIELD: war material. SUBSTANCE: invention can be used designed of ammunition for grenade launchers. Proposed rocket contains housing, propelling charge and electric fuses. Propelling charge is arranged in stages divided by partitions, each consisting of combustion chambers divided by partitions and accommodating propelling charges and electric fuses. Combustion chambers are connected by electric circuit, and last combustion chamber serves as locking device. Number of stages is two minimum. Number of combustion chambers is two minimum. Stages are made for sequential connection. EFFECT: increased range and speed of grenades. 4 cl, 2 dwg

Description

 The invention relates to the field of military equipment and can be used in the design of ammunition for 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.

 An analysis of this information (auth. St. RF 2062428, IPC F 41 F 3/045) showed that the well-known, widely used grenade launchers (ammunition) with certain defined overall and weight characteristics allow throwing grenades using a rocket launcher over a range of several tens up to several hundred meters.

 The disadvantages of such grenade launchers include the limited firing range, the projectile speed, on which the direct range and accordingly the firing accuracy depends, and its insignificant weight (grenades) with the installed dimensions of the product. In addition, even with significant changes (increases) in the dimensions of grenade launchers and grenades, 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 to create a new type of grenade launchers (ammunition), which will increase the range, flight speed of the grenade and its weight with the existing dimensions, as well as reduce the dimensions of the products with the existing weight of the grenade and its flight range, depending on the set tasks.

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

The solution to this problem is achieved by the proposed engine for a grenade fired from a grenade launcher (hereinafter referred to as D 3C GR), comprising a housing, a propulsive charge and electric igniters, where the propulsive charge is placed in steps divided by partitions made with the possibility of their sequential inclusion, the number of which is from two or more, each of which consists of combustion chambers separated by partitions, the number of which is from two or more, with propelling charges placed in them and electric ignition substitutes corresponding to the burning rate condition:
n <n (s);
n (s) = V / V (m);
n = n (s) -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,
while the combustion chambers are connected by an electric circuit, and the last of the combustion chambers is a locking mechanism. The characteristics of grenade launchers and ammunition (grenades) for them vary depending on the tasks to be solved by changing all the structural elements tied into a single whole.

 In our proposed D 3C GR, the acceleration of a grenade is carried out by placing steps with a propulsive charge in the grenade body, the steps are divided into combustion chambers with a propellant charge with several igniters, which made it possible to increase the throwing speed when compressing the propellant charge (reducing the ratio of the weight of the charge of the fuel substance to weight throwing body), reduce the overall size of the structure for existing combat characteristics, increase the weight of the throwing body (grenade), increase the length of the flight path after exiting launch tube.

 The essence of the invention is shown in the drawings. Figure 1 shows a General view of D 3C GR, where the body of a grenade 1, consisting of a propulsion charge in the housing 5 and a payload 3, the propulsion charge consists of stages 4a, 4b, 4c with partitions 2. Figure 2 shows the stage D 3C GR, where the casing of the stage 11 is divided into combustion chambers 6a, 6b, 6c with inter-chamber partitions 10, in the combustion chambers there is a propellant charge 8 in the casing 9 with electric igniters 7, connected by an electric circuit.

 A grenade 1 with a payload of 3 is accelerated with a propellant charge in the housing 5, the design of which ensures the sequential actuation of the stages (4a, 4b, 4c) and, accordingly, the gradual acceleration of the grenade 1 and the complete combustion of the combustible substance 8 from electric igniters 7, at which the device is not yet destroyed due to the explosion from pressure overload placed in the combustion chamber 6a, 6b, 6c.

 The proposed device operates as follows.

 After supplying electricity to the “DZS GR” with the help of series-connected electric igniters 7, a simultaneous ignition of the combustible substance 8 of the first stage (extreme to the exit) 4a occurs in the combustion chambers 6a, 6b, 6c. Inside the combustion chambers 6a, 6b, 6c, a pressure is created corresponding to the condition of the burning rate. The combustion products of a combustible substance (gas compressed to a high density), expanding, press on the housing 1 and inter-chamber partitions 10. Under the pressure of the gases in the combustion chambers 6a, 6b, 6c, the inter-chamber partitions 10 are set in motion, while in the combustion chamber 6a, one inter-chamber partition 10 pushes in front of itself the partition 2 before the next stage 4b, the inter-chamber partition 10 presses on the combustion chamber 6b; in the combustion chamber 6b, the interchamber partition 10 presses on the combustion chamber 6a, the interchamber partition 10 presses on the combustion chamber 6b; in the combustion chamber 6c, the inter-chamber baffle 10 presses on the combustion chamber 6b, another inter-chamber baffle 10 pushes the baffle 10 out of the grenade body 1 to the outside. In each stage 4a, 4b, 4c, ... 4n, the combustion chamber 6c, which is the outermost to the outlet, acts as a locking mechanism, thereby ensuring that the gases of the remaining combustion chambers 6a, 6b, ... 6n are triggered by the pressure of the subsequent stages 4b, 4c, .. .4n, driving the entire structure of the grenade 1 and further due to the successive operation of the remaining stages 4b, 4c, ... 4n.

Claims (4)

1. An engine for a grenade fired from a grenade launcher, comprising a housing, a propulsive charge and electric igniters, characterized in that the propulsive charge is placed in steps separated by baffles, each of which consists of combustion chambers separated by baffles with propelling charges and electric igniters, wherein the chambers The combustion is connected by an electric circuit, and the last of the combustion chambers is a locking device. 2. The engine according to claim 1, characterized in that the number of stages is from two or more. 3. An engine according to any one of claims 1 and 2, characterized in that the number of combustion chambers is from two or more. 4. The engine according to any one of claims 1 to 3, characterized in that the steps are made with the possibility of their sequential inclusion.

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