RU2520708C1 - Aircraft gun localiser - Google Patents

Abstract

FIELD: weapons and ammunition.

SUBSTANCE: localiser comprises rotary flap to close gun barrel at no-fire conditions. Deflectors are arranged at said flap furnished with openings to allow projectile to pass there through at flap open position. Flap can turn about its axis misaligned with gun barrel axis.

EFFECT: protection of aircraft skin against barrel shock wave, permanent pressurisation of gun compartment.

4 cl, 2 dwg

Description

The invention relates to the field of military equipment and can be used on an aircraft (military aircraft) for military purposes to reduce the impact on aircraft of powder gases flowing from a muzzle end of a gun barrel.

Gunpowder gases flowing from the barrel of a gun at a speed exceeding the speed of sound, and having high temperature and pressure, form a muzzle shock wave (OWL). OIL acts on the casing and causes vibration of the structure and onboard equipment of the aircraft, which can lead to destruction of the structure and equipment failure. When the muzzle is located near the air intake of the turbojet engine, pulsations of temperature and pressure at the inlet of the air intake caused by the OIL can cause surging of the engine.

To reduce the effect of OIL on the aircraft structure, localizers are used that redirect the flow of outgoing powder gases to the side of the aircraft.

In addition, the ammunition located in the barrel in the initial position for firing, during a break or a delay in firing, can spontaneously work due to its heating by an incoming air stream flowing through the heated barrel. To prevent this, the muzzle of the barrel is blocked by the sash during the break in shooting.

Known placement of weapons on an airplane (US patent No. 3099938), in which the holes of the barrel of the guns brought near the openings of the air intakes. For the removal of powder gases in the side wall of the pipe into which the gun barrel is brought out, holes are made that are oriented away from the air intake and equipped with guide vanes (deflectors).

A well-known aircraft gun localizer (RF patent No. 2100737), comprising a housing with windows and a camera, which is mounted on the barrel of the gun, and vent pipes connected to the windows, mounted on the fixed parts of the gun or on the installation. After the projectile passes the location of the localizer, part of the powder gases rushes from the barrel channel into the chamber of the localizer body and through the body windows into the tubes, and gas flows out of the tubes into the atmosphere.

Closest to the invention is a device for deflecting powder gases of an aircraft gun, described in US patent No. 4619182. Its body is mounted on the barrel of an aircraft gun. The housing has an opening for the projectile, located directly opposite the muzzle of the gun, and a second hole, oriented away from the fuselage of the aircraft. Across this second hole, several guide plates (deflectors) are installed, bent in such a way that the flow of powder gases passes along them and deviates into this hole. The housing is fixed relative to the barrel using a spherical bearing. Despite the fact that such a fastening allows the housing to rotate, its rotation during operation is not provided, it is fixed against rotation by pins, and the purpose of this fastening feature (using a spherical bearing) is to facilitate installation (as described in the description of this patent).

To ensure the explosion safety of the cannon installation compartment, it is necessary to prevent the ingress of powder gases back into the compartment to ensure their explosion-proof concentration. At the same time, blowing the compartment with the use of sashes and gratings on the intake and release of incoming air will increase the “visibility” of the aircraft.

The disadvantages of the described known solutions are that:

- the case preventing the heating of the ammunition is not integrated into the structure,

- not provided a decrease in radar visibility.

The objective of the invention is the creation of a muzzle device that performs the functions of a localizer and a sash, depending on the need at a given time, providing low radar visibility of the corresponding part of the aircraft in the absence of firing.

The problem is solved with the help of a localizer containing a rotary shutter that closes the gun barrel in the absence of firing, deflectors are installed on the shutter, holes are made in the vents to allow the projectile to pass in the open position of the shutter.

The pivoting leaf may be rotatably mounted about an axis that does not coincide with the axis.

The localizer contains a pallet defining the barrel mounting cavity, mounted on the fuselage and hermetically connected to its skin, the pallet has a cylindrical part covering the barrel, the pivoting sash has a mating cylindrical surface at one end, and a hemispherical protrusion at the other end, forming with the mating concave surface part spherical bearing pan.

The pivoting sash is also provided with a liner covering the barrel to ensure sealing of the connection and the possibility of longitudinal movement of the barrel.

The invention allows to protect the skin of the aircraft from the effects of OIL during firing, and the rest of the time to protect the gun barrel from incoming air and reduce the radar visibility of the aircraft. At the same time, the cannon compartment is constantly sealed.

The invention is illustrated by drawings, where Fig. 1 shows a device in the closed position (no firing), Fig. 2 shows a device open for firing.

The proposed device is as follows.

On the aircraft in the fuselage 1 there is a cavity at the installation site of the gun barrel 2. The localizer contains a rotary leaf 3, which, in the absence of firing, closes this cavity from the outside, including barrel 2, and protects the barrel 2 from heating by an incoming air stream. The outer surface of the sash 3 corresponds to the contours of the fuselage 1 in this place, which minimizes the contribution of the cavity to the radar visibility of the aircraft.

From the side of the aircraft’s internal compartments, this cavity is bounded by a pallet 4, which is rigidly fixed to the fuselage 1 and is hermetically connected to its skin.

The leaf 3 is mounted for rotation about an axis that does not coincide with the axis of the barrel 2.

This can be implemented as follows. The pallet 4 in the area of the barrel 2 has a cylindrical part covering the barrel 2. At one end, the sash 3 has a mating cylindrical surface. This connection of the cylindrical surfaces of the pallet 4 and the sash 3 forms a cylindrical bearing. The cylindrical surfaces of the pallet 4 and the sash 3 can be separated by a sleeve 5 fixed in the cylindrical surface of the pallet 4. At the other end, the sash 3 has a hemispherical protrusion 6, which is the front support of the sash 3 and forms a spherical bearing with the corresponding concave part of the surface (hemispherical recess) of the pallet 4 slip. This allows to partially compensate for technological deviations.

Due to the mismatch of the axis of the barrel 2 and the axis of rotation of the sash 3, the front support of the sash 3 (protrusion 6) is not an obstacle during the passage of the projectile. In addition, the mismatch of the axes allows you to place the device on the sections of the contours of the fuselage 1, non-parallel to the barrel 2, and reduce the dimensions of the device.

The leaf 3 is provided with a liner 7, covering the barrel 2, providing a sealing connection and the possibility of longitudinal movement of the trunk during the rollback. Sealing the compound helps prevent powder gases from entering the aircraft compartments.

On the casement 3, deflectors (guide plates) 8 are mounted, oriented so that in the open position of the casement 3 (see FIG. 2) they deflect the flow of powder gases to the side of the aircraft. In the deflectors 8, holes 9 are made, which are located so that in the open position of the sash 3 they are on the axis of the barrel 2, ensuring the passage of the projectile. For this, the holes 9 have a diameter sufficient for the passage of shells.

The shutter 3 can be driven into rotation by an electric actuator through gear cylindrical gearing (gear). In this case, the gear wheel is rigidly attached to the rotary leaf 3. The leaf 3 is fixed in the extreme open and closed position by stops.

The device operates as follows.

In the absence of firing, the sash 3 is closed, so that it is part of the contour of the fuselage 1. It closes the cannon compartment and hides it from the radars.

Immediately before firing, the sash 3 is rotated using the drive, opening the barrel 2.

When firing, the projectile passes through the holes 9, and the deflectors 8 deflect the flow of powder gases away from the aircraft.

At the end of firing, the sash 3 returns to the closed position.

Claims (4)

1. The localizer contains a rotary shutter that closes the barrel of the gun in the absence of firing, deflectors are installed on the shutter, holes are made in the vents to allow projectile passage in the open position of the shutter. 2. The localizer according to claim 1, characterized in that the pivoting sash is mounted for rotation about an axis that does not coincide with the axis of the gun barrel. 3. The localizer according to claim 2, characterized in that the localizer contains a tray defining the barrel installation cavity, mounted on the fuselage and hermetically connected to its skin, the tray has a cylindrical part covering the barrel, the pivoting sash at one end has a mating cylindrical surface, and on the other, a hemispherical protrusion, forming a spherical bearing with a mating concave part of the surface of the pallet. 4. The localizer according to claim 3, characterized in that the pivoting sash is also provided with an insert covering the barrel to ensure sealing of the connection and the possibility of longitudinal movement of the barrel.

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