RU2846434C1 - Aircraft protection device - Google Patents

Abstract

FIELD: aviation.

SUBSTANCE: aircraft protection device includes a launch container equipped with an ejector charge, a gasket, and a protective bursting membrane. Inside the container there is a housing, on one side of which there are hinged supports with spring-loaded swivel straps fixed on them, capsules with a thermal composition and an initiating charge are installed at the ends of the straps. In the lower part of the capsules, rotary levers are placed, connected at one end to the central disk by metal cables, and strikers are installed at the opposite end of the levers to affect the initiating charge in the capsule. A fuse and striking elements are placed in the head of the case, and the case itself is filled with explosives. The tail unit is located on the opposite side of the hull, and spring-loaded swivel straps with fabric wings attached to them and the hull are mounted in the hinged supports.

EFFECT: increasing the effectiveness of attacking missile damage.

1 cl, 5 dwg

Description

The proposed invention relates to aircraft protection devices and is intended to protect aircraft from surface-to-air and air-to-air guided missiles.

Known is "Element of active protection of aircraft from guided missiles" patent No. 2691801. For active protection of aircraft from guided missiles of the "surface-to-air" and "air-to-air" classes, the element is detonated at a calculated point in space on the trajectory of the missile, the cloud of fragments formed during the explosion hits the missile. The element of active protection has insufficiently high efficiency, it is necessary to act more purposefully on the attacking missile.

In order to increase the effectiveness of the destruction of an attacking missile, it is proposed to fire a device on the trajectory of the attacking missile, which after leaving the launch container is transferred to the combat position, during which the fuse is armed and the thermal composition in the capsules is ignited, while a fire circle of high thermal intensity is formed, which leads to the retargeting of the missile at the protective device, a collision with it, detonation of the device's warhead and destruction of the missile.

The purpose of the invention is to increase the effectiveness of destruction of an attacking missile by retargeting it to a protective device; when the device is triggered, the warhead of the missile is destroyed and its warhead is detonated.

The objective is achieved by the fact that the protection device includes a launch container with an ejection charge, a gasket on one side and a burst protective membrane on the other. Inside the container there is a housing on which hinged supports are placed, spring-loaded rotary bars are installed in the supports, capsules with a thermal composition and an initiating charge are placed at the ends of the bars, a rotary lever is installed in the lower part of the capsule, one end of the lever is connected by a metal cable to the central disk, and at the other end there is a striker for acting on the initiating charge of the capsule in order to ignite the thermal composition. On the opposite side of the housing there is a tail unit and spring-loaded rotary bars with fabric wings attached to the bars and to the housing are hingedly installed, an explosive charge is placed in the housing, and in its head part there is a detonator and striking elements.

Graphic materials

Fig. 1 shows the protection device in the launch container, Fig. 2 shows the protection device in the working position - top view, Fig. 3 - front view of the protection device, Fig. 4 - section B-B, Fig. 5 - the protection device at the moment of the missile attack.

The protection device includes a launch container 1, an expelling charge 2, a gasket 3, a burst protective membrane 4, a housing 5 is placed in the container, which has hinged supports 6, strips 7, strips 8, springs 9, capsules 10, a thermal composition 11, metal cables 12, a central disk 13, a rotary lever 14, a striker 15, an initiating charge 16, a safety spring 17, a tail unit 18, a detonator 19, an explosive charge 20, striking elements 21, fabric wings 22, a safety rod 23, a longitudinal groove in the container 24, and projections on the wings 25.

The protection device operates as follows. When a signal is received about a missile attack, the device is fired towards the attacking missile. In the launch container 1 (Fig. 1), the ejection charge 2 is triggered, which pushes the device out of the container, the gasket 3 prevents the breakthrough of the powder gases, and during the launch, the protective membrane 4 ruptures. After leaving the container (Fig. 2), the bars 8, under the action of the springs 9, rotate in the hinged supports 6, while the metal cables 12 straighten and hold the central disk 13 in the middle of the device (Fig. 3), the disk has a lattice design to reduce the impact of the air flow on the disk when the device is fired. The cable 12 is also secured to the rotary lever 14; when the lever is turned, the striker 15 strikes the initiating charge 16, after ignition of which the thermal composition 11, placed in the capsule 10, ignites; the safety spring 17 prevents accidental activation of the initiating charge. In the rear part of the body 5, the tail unit 18 is made, and spring-loaded strips 7 are mounted on hinged supports; between the strips and the body 5, wings 22, made of heat-resistant fabric, are secured; when leaving the launch container, the wings open and provide a gliding flight of the device. To ensure the oriented position of the device when leaving the container, protrusions 25 are made on the ends of the wings, placed in the grooves of the container 24 (Fig. 4). The head part of the device contains striking elements 21 and a detonator 19, which is switched to the combat position by turning the bar 8, while the rod 23 unlocks the detonator, the body 5 is filled with a charge of explosive substance 20.

When the protective device leaves the launch container, the bars rotate to the working position and the thermal composition ignites, a fiery circle of high thermal intensity is formed in all capsules, which leads to the retargeting of the attacking missile at the device (Fig. 5), the missile strikes the central disk, the fuse is triggered, the explosive charge is detonated, and the striking elements destroy the warhead of the missile and cause the detonation of its warhead.

Claims (1)

A device for protecting aircraft, including a launch container, an ejection charge, a gasket, a protective bursting membrane, characterized in that a housing is placed in the container, on one side of which hinged supports with spring-loaded rotary bars attached to them are installed, capsules with a thermal composition and an initiating charge are installed at the ends of the bars, rotary levers are placed in the lower part of the capsules, connected at one end by metal cables to the central disk, strikers for acting on the initiating charge in the capsule are placed at the opposite end of the levers, a detonator and damaging elements are placed in the head part of the housing, the housing itself is filled with an explosive charge, a tail unit is placed on the opposite side of the housing, and spring-loaded rotary bars with fabric wings attached to them and to the housing are installed in the hinged supports.