Recoil buffer for automatic grenade launcher on tripod

Abstract

FIELD: weapons.SUBSTANCE: recoil buffer for the automatic grenade launcher on the machine consists of disc springs, a guide bushing, a screw, a casing, characterized in that the disc springs, in turn, have an outer diameter of 16 mm, a hole in the centre with a diameter of 10 mm, a thickness of 3.5 mm. Sixteen springs are assembled on a guide bushing made of high-strength alloy steel and having the following dimensions: height 23.4 mm, outer diameter 9.9 mm, inner diameter 8 mm, on one side of which a flange with a thickness of 0.6 mm is made to hold the outer spring, and on the other side a technological hole with a diameter of 6 mm is made. A polyurethane casing is fixed onto the disc springs and bushing.EFFECT: increased probability of hitting a target, a reduction in ammunition consumption, and a reduction in the time required to complete a combat mission.1 cl, 3 dwg

Description

[0001] The invention relates to the field of automatic small arms, namely to the automatic mechanisms of automatic grenade launchers and can be used to reduce dynamic loads that occur when moving parts (bolt, bolt carrier) roll back.

[0002] Modern experience in armed conflicts demonstrates the significant role of grenade launchers, particularly tripod-mounted automatic grenade launchers. Currently, the Russian Armed Forces have adopted and utilized several models of this type, including the 30mm tripod-mounted automatic grenade launcher (AGS-17), the 30mm tripod-mounted automatic grenade launcher (AGS-30), and the 40mm automatic anti-personnel grenade launcher, which is currently undergoing testing. While these models have proven themselves to be effective, they nevertheless have several drawbacks, one of which is the high bounce during automatic fire, which increases grenade dispersion and leads to a high grenade consumption. Let's consider alternatives to the presented invention.

[0003] A known invention consists of a housing attached to the front end of the receiver. Within the housing is a stack of axially movable rings capable of mutual movement along inclined guides provided on each ring. One of the two outer rings is mounted against the front end of the receiver, and the other against the end of the housing. The barrel is equipped with a guide and thrust bushing. The guide bushing is connected to the recoil spring and installed within the receiver cavity. The technical result of the invention consists of improving the weapon's performance characteristics and reducing its overall dimensions.

[0004] The disadvantage of this device is its significant dimensions and the complexity of its construction.

[0005] An invention is known that comprises a cylinder mounted on a barrel, spring-loaded relative to it with a front wall and a piston, and the barrel is made with gas venting channels, the device is provided with a cylindrical casing with a rear wall and a front end, the barrel has the ability to move relative to the casing, which is connected to the cylinder and covers it and the front part of the barrel protruding from it, which is made with a front gas-dynamic blade and at least one additional blade, each of the blades has a C-shaped radial section with a bulge facing the outlet of the barrel, and forms an annular chamber with the casing, each additional blade has a bypass window, the gas venting holes of the barrel are directed at an angle to the axis of the barrel with the apex of the angle facing the inlet of the barrel, and connect the cavity of the barrel with the corresponding annular chambers, the cylinder is made with purge channels in the front wall,and the piston is made stationary relative to the barrel.

[0006] The disadvantage of this device is the relatively low efficiency of recoil energy reduction.

[0007] An invention is known for a method and ejector device for reducing weapon recoil during firing. The invention involves reducing weapon recoil using propellant gases directed in opposite directions to the recoil and rebound of the weapon. According to the method, the propellant gases, before exiting the barrel, are directed for partial cooling, pressure reduction, and deceleration into the converging chambers of Laval nozzles connected to the central body of the barrel. Upon exiting the diffusers of the Laval nozzles, the propellant gases expand and accelerate to supersonic speeds, creating vacuum zones in the diffusers.Using vacuum zones, it ejects outside air through channels connecting these zones to the atmosphere, cooling the propellant gases and increasing the mass of their mixture due to the ejected air. This reduces the propellant gas pressure to an optimal value and increases the total kinetic momentum of the exiting jet from the diffusers in directions opposite to the weapon's recoil and rebound. The ejector device is designed as a muzzle attachment connected to the end of the barrel via threads. The ejector device contains gas bleed holes and an annular gap. The annular gap is located in the expansion chamber that encloses it. The expansion chamber is designed as a geometric detachable connection through a ring of two Laval nozzle confuser inlets with the central body of the barrel. The ring has a calibrated internal bore.The internal bore is calibrated by moving the barrel's end (without rifling) and the rest of the barrel along the threads relative to the corresponding sides of the ring. The outlet of each Laval nozzle diffuser is a critical section, a diffuser equipped with a connecting barrel body. The upper half of the barrel is formed by sectional nozzle openings for the outlet of the gas mixture jet. The Laval end nozzle and the central barrel body form the upper half, while the diffuser's sectional nozzle openings are directed to the sides and upward. This reduces the weapon's recoil during firing.

[0008] The disadvantage of this recoil braking method is its low efficiency in reducing recoil energy, since only a portion of the propellant gases exerts pressure on the piston and spring-loaded cylinder. Furthermore, the transfer of energy from the piston's less-than-perfectly elastic impact to the massive barrel is physically associated with a significant conversion of the impact's kinetic energy into deformation energy of the stop and its heating. Another disadvantage of this method is the complexity and labor-intensive nature of adjusting the resulting axial and lateral forces, which constitute the total momentum vector of the propellant gases acting on the barrel and the weapon, to ensure the desired barrel position before the next shot.

[0009] The purpose of the invention is to reduce the recoil force impulse on the barrel group and the shooter during firing, as a result of which the grenade throwing angle is reduced during automatic firing and the accuracy and precision of firing from an automatic grenade launcher is increased.

[0010] The invention reduces receiver vibration, softens the impact of moving parts, and improves stability and firing accuracy. The developed solution is intended for integration into existing grenade launcher designs without the need for radical redesign. The invention is illustrated by Fig. 1 - a cross-sectional view of the bolt recoil buffer; Fig. 2 - the receiver of an automatic grenade launcher on a tripod without a bolt recoil buffer; Fig. 3 - the receiver of an automatic grenade launcher on a tripod with a bolt recoil buffer mounted on the butt plate.

[0011] The invention consists of disc springs 2, a guide sleeve 3, a screw 4, a casing 1. Distinctive features: disc springs 2, in turn, have an outer diameter D8 = 16 mm, a hole in the center with a diameter D3 = 10 mm, a spring thickness T = 3.5 mm, in the amount of 16 pieces assembled on a guide sleeve 3, made of high-strength alloy steel and having the dimensions height L3 = 23.4 mm, outer diameter D7 = 9.9 mm, inner diameter D2 = 8 mm, on one side of which a flange 5 with a thickness of 0.6 mm is made to hold the outer spring, and on the other side a technological hole with a diameter D6 = 6 mm is made; A polyurethane casing 1 is fixed onto the disc springs and bushing 3 by means of internal projections for the disc springs, made with a height of L1=25 mm, a diameter of D4=24 mm at a distance of L2=6 mm, and the main body is made with a diameter of D5=22 mm, and has an opening on the upper side with a diameter equal to the internal diameter of the guide bushing; the flange has a diameter of D1=14 mm.

[0012] The proposed invention is used as follows. During the grenade launcher's automatic operation, when firing a shot, the bolt group, under the influence of the recoil impulse, performs a translational movement along the axis of the receiver. Upon reaching the extreme rearward position, the moving elements contact the bolt recoil buffer 7 mounted on the butt plate 6, which causes braking dynamics: the linear velocity of the bolt group is reduced, the kinetic energy of the system is converted into thermal energy (up to -65%), the elastic deformation of the damping elements is reduced to (30-35%), and residual vibrations (5-10%). The impact of vibration loads on the receiver is reduced, and the peak value of the impact impulse is reduced to 3000 ns. The angular velocity of the barrel at the moment of grenade firing is reduced and the repeatability of the initial firing conditions is increased.

[0013] Thus, the proposed invention reduces the recoil force on the barrel group and the shooter during firing, resulting in a reduced grenade throwing angle during automatic fire and improved accuracy and grouping of shots from an automatic grenade launcher. The proposed invention increases the probability of hitting a target, reduces ammunition consumption, and shortens the time it takes to complete a combat mission.

[0014] List of references

[0015] 1. Russian Federation Patent RU No. 2258883 C1, IPC F41A 21 / 36, published August 20, 2005.

[0016] 2. Russian Federation Patent RU No. 2191965 C1, IPC F41A 21 / 36, published August 27, 2002.

[0017] 3. Russian Federation Patent RU No. 2413154 C1, IPC F41A 21 / 36, published February 27, 2011.

Claims

A bolt recoil buffer for an automatic grenade launcher on a machine, consisting of disc springs, a guide sleeve, a screw, a casing, characterized in that the disc springs, in turn, have an outer diameter of 16 mm, a hole in the center with a diameter of 10 mm, a thickness of 3.5 mm, springs in the amount of 16 pieces are assembled on a guide sleeve made of high-strength alloy steel and having the following dimensions: height 23.4 mm, outer diameter 9.9 mm, inner diameter 8 mm, on one side of which a flange with a thickness of 0.6 mm is made to hold the outer spring, and on the other side a technological hole with a diameter of 6 mm is made, a polyurethane casing is fixed to the disc springs and the sleeve due to internal projections for the disc springs, made with a height of 25 mm, a diameter of 24 mm, at a distance of 6 mm, and the main body, made with a diameter of 22 mm, and having an opening on the upper side with a diameter equal to the inner diameter of the guide bushing, the flange has a diameter of 14 mm.

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