RU2691801C1 - Active protection element of an aircraft from guided missiles - Google Patents

Abstract

FIELD: active protection devices.SUBSTANCE: invention relates to aircraft ammunition for protection of aircraft from guided missile of "surface-to-air" and "air-to-air" class. Active protection element of an aircraft from controlled missiles comprises a metal sleeve with a striking module of a fragmentation type, an igniter and a closed plug. According to the invention, the striking module of the fragmentation type and the igniter are installed in a cylindrical body, the outer diameter of which is equal to the inner diameter of the sleeve, in the lower part of the housing there is a nozzle unit with a stabilization device, and in the upper part – a fairing, between the striking module and the nozzle block there is a solid fuel engine, a fuse of a remote type is located under the fairing.EFFECT: high efficiency of protecting an aircraft from guided “surface-to-air” and “air-to-air” missiles with a homing head of various types by enabling the active protection element to be blasted at the design point of space on the trajectory of the guided missile.1 cl, 1 dwg

Description

The invention relates to the field of military equipment, namely, to unguided aircraft munitions, designed to protect aircraft from guided enemy missiles, surface-air and air-to-air.

The closest to the technical nature of the claimed invention is an element of the active protection of the aircraft [see for example, patent RU 2633012, C1, IPC F42B 5/15, F42B 4/26, F42B 12/70, publ. 11.10.2017]., Containing a metal sleeve with an electric igniter placed at the bottom, a pyrotechnic composition located in the cavity of the sleeve and closed with a plug, striking a module consisting of an explosive, on the surface of which a fragmentation belt with integrated explosive control channels is placed a substance whose principle of operation is that after receipt, upon a command from the ejection device control unit, an electric current pulse is triggered, This burning pyrotechnic composition. By the pressure of the combustion products of the pyrotechnic composition, the plug rolls out the sleeve sleeve and the burning pyrotechnic composition is ejected from it, creating a source of infrared radiation. When a pyrotechnic composition is burned through, the explosion control channels are ignited and thereby the transfer of energy through them to an explosive. As a result of the explosive detonation, the fragmentation belt forms a cloud of fragments, falling into which the guided missile receives damage to the homing head and other compartments, leading to a breakdown in the guidance of the guided missile on the attacked aircraft [Patent RU 2633012, C1, MPK F42B 5/15, F42B 4 / 26, F42B 12/70, publ. 11.10.2017].

The disadvantage of the known element of active protection is the low efficiency of protection of the aircraft from guided missiles, due to large errors of shooting at the calculated point of space.

The technical result of the invention is to improve the protection of the aircraft from guided missiles "surface-air" and "air-to-air" with a different type of homing head, by ensuring the undermining of the active protection element in the calculated point of space on the trajectory of the guided missile.

The technical result is achieved by the fact that in a known active protection element containing a metal sleeve with a striking fragmentation-type module, an igniter and a closed cap, according to the invention, a housing with a nozzle block and a stabilization device, a fairing fuse, and a remote type fuse and engine are added solid fuel.

The essence of the proposed technical solution lies in the fact that the striking fragmentation module and the igniter are installed in a cylindrical case whose outer diameter is equal to the inner diameter of the sleeve, in the lower part of the case there is a nozzle block with a stabilization device, and in the upper part is a fairing, between the striking module and nozzle the unit is equipped with a solid fuel engine, a remote type fuse is located under the fairing. In the prelaunch preparation of control equipment, a remote action time is entered into the fuse to ensure the detonation of the munition at the design point. Time determines the required range and is based on the nominal values of the movement parameters of the active protection element. After the active protection element leaves the ejection device, the stabilization device opens and goes into operation. Under the action of the thrust force of the products of combustion of a solid fuel engine, the munition rotates around its axis, which is necessary for a stabilized flight to the calculated point of space. When reaching the time of the remote action, the fuse is triggered and initiates the explosion of the explosive of the striking module. As a result of the explosive blasting of the striking module, a cloud of splinters is formed, getting into which the guided missile is damaged, leading to the disruption of its targeting.

The scheme of the proposed active protection element is presented in FIG. one.

FIG. 1 marked:

1 - metal sleeve;

2 - plug;

3 - igniter;

4 - explosive;

5 - fragmentation belt;

6 - case;

7 - fairing;

8 - remote type fuse;

9 - solid fuel engine;

10 - nozzle block;

11 - ammunition stabilization device.

Elements 1-5 characterize the prototype. In addition to them, introduced new elements and devices.

Case 6 is designed to accommodate the components of the active protection element and is made in one piece with the nozzle block - 10 and can be made of a thin-walled tube based on an aluminum alloy, for example D16T, by isothermal punching [see for example, Patent RU 2174455, C2, IPC B21D 41/04 publ. 10.10.2001,], and the inner surface of the housing and the nozzle block, which is in contact with the combustion products of a solid fuel engine, is protected by an erosion-resistant heat-shielding coating based on an anode aluminum oxide film with a thickness of up to 60 μm. The film is applied by electrochemical method. Use as the source material of the entire body of the tubular billet of an alloy based on aluminum significantly reduces the total weight, simplifying the manufacturing process.

To reduce the aerodynamic resistance in the design of the active protection element introduced fairing 7, which can be made of a polymeric material [see for example, Bulatov IM, Vorobey V.V. Technology of rocket and aerospace structures made of composite materials. - M. MSTU. N.E. Bauman, 1998. - p. 442-476].

The remote type 8 fuse is designed to ensure the undermining of the active protection element in the design point of space [see for example, weapons and ammunition / ed. V.V. Selivanova. - M. MSTU. N.E. Bauman, 2008. - p. 930-936]. It is controlled automatically before shooting by the inductive line of communication between the ejection device and the fuse for the required time of remote action entered by the control equipment during the prelaunch preparation. Time determines the required range and is based on the nominal values of the parameters of movement of the munition.

The solid fuel engine 9 is designed to provide the necessary flight speed of the active protection element. It creates a thrust generated by the outflow of gas [see for example, Aviation armament: Textbook / Ed. DI. Gladkov - M .: VVIA them. prof. NOT. Zhukovsky, 1971. - C 62-68.

The nozzle unit 10 serves as a means of increasing the reactive power of the engine. It has an optimal profile nozzle (input part, critical section and an expanding supersonic part) with attachment points for the ammunition stabilization device 11 [see for example, Patent RU 2418186, C2, IPC F02K 9/34, publ. 10.05.2011,], which is made of plates of aluminum alloy and is intended to stabilize the ammunition in flight by imparting a rotational motion around the building axis. The use of a nozzle of this design in combination with the attachment points of the ammunition stabilization device increases reliability and reduces weight.

The element of active protection of the aircraft from guided missiles works as follows. In the process of pre-launch preparation from the control equipment (immediately before launching), the fuse 8 receives signals through an inductive communication channel that carry information about the required time of remote detonation. At the same time, a pulse of electric current from the control device is supplied to the electrical contacts of the liner, initiating the combustion of the powder composition of the igniter 3. The gases produced during the combustion of the igniter powder fill the free volume of the combustion chamber and ignite the fuel charge of the engine 9. The cap 2 rolls off the combustion products of the engine fuel. The cartridge case 1 and the active protection element are ejected into the airspace. When exiting the barrel, the stabilization device of the ammunition 11 is opened. The countdown of the set distance of the remote explosion begins. After the termination of the linear acceleration, i.e. after the end of the active part of the trajectory, the fuse 8 is cocked, thereby removing the degree of protection. After the set time has been counted by the electronic temporary device, the fuse is triggered and the explosive 4 is exploded. As a result of the explosive detonation, the fragmentation belt 5 forms a cloud of fragments at the calculated point of space, falling into which the guided missile receives damage to the homing head and other compartments, leading to its disruption guidance

Thus, based on the analysis of the structure and operation of the proposed technical solution, it can be concluded that the active protection element in which this solution is implemented has advantages that are in line with the task, namely, increasing the effectiveness of protecting the aircraft from guided surface-to-air missiles and “air-to-air” with a different type of homing head, by ensuring the undermining of an active protection element at a calculated point in space on a controlled movement path Aketi.

Claims (1)

An element of active protection of an aircraft from guided missiles, containing a metal sleeve with a striking fragmentation module, an igniter placed in it, and a closed plug, characterized in that the striking fragmentation module and igniter are installed in a cylindrical case, the outer diameter of which is equal to the inner diameter of the sleeve, A nozzle block with a stabilization device is located in the lower part of the body, and a fairing is located in the upper part. An engine is mounted between the striking module and the nozzle block. solid fuel, located under the fairing fuse remote type.

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