RU2629464C1 - Protection method for aerial vehicles against missiles fitted with target-seeking equipment with matrix photodetector - Google Patents

Abstract

FIELD: weapon and ammunition.

SUBSTANCE: invention relates to methods of individual protection of aerial vehicles against missiles fitted with target-seeking equipment with matrix photodetectors. In the space between the aerial vehicle and the most likely direction of a possible missile attack by the enemy, by detonating the active element of protection a fragment group is formed getting into which the missile gets damaged, leading to a disruption of its operability.

EFFECT: efficiency and reliability of aerial vehicles protection.

5 dwg

Description

The invention relates to the military field, and in particular to methods of individual protection of aircraft from missiles equipped with homing heads with matrix photodetector devices.

A known method of protecting aircraft from missiles equipped with homing heads by creating in the space between the aircraft and the most probable direction of a possible missile attack by an adversary a holographic image of a real source emitting electromagnetic waves mainly in the frequency range of the visible and infrared spectra. Sources emitting electromagnetic waves at other frequencies corresponding to the operating frequencies of various missile guidance systems for air targets can also be used as a false target (see RF patent No. 2141094, IPC F41H 11/02, 1999).

The disadvantage of this method is that for the formation of a holographic image of a false target in the form of an aircraft (LA), a large amount of energy is needed to power the onboard holographic system, in addition, the system itself has high mass and size characteristics. For missiles with an induction fuse, this method is ineffective due to the fact that such a fuse is fired in the immediate vicinity of the aircraft under the influence of a changed magnetic field.

Also known is a method of individual protection of an aircraft from missiles with infrared homing heads, based on the fact that, following the course of the aircraft, special pyrotechnic devices (infrared traps) are generated that create intense radiation in the infrared wavelength range (Reference book of an air defense officer. / G.V. Zimin, S.K. Burmistrov, B.M. Bukin and others - 2nd ed., Revised and additional - M .: Military Publishing House, 1987, pp. 474-477 - prototype).

The disadvantage of this method is the lack of efficiency, which is due to the fact that to disrupt guidance of a guided missile with a photodetector array (MFP), it is necessary to constantly close the target image and stretch it, creating a certain distance from the protected aircraft interference with the morphological characteristics of the target.

The use of matrix photodetectors allows you to implement more complex methods of target selection, which include spatial, geometric and trajectory selection based on digital processing of extended images. Therefore, another drawback of existing false thermal targets is their rapid angular divergence with the target and spatial expansion in the form of separate radiation sources that are allowed in the field of view of the optical homing head.

The aim of the present invention is to increase the efficiency and reliability of protection of an aircraft from missiles equipped with optical homing heads with a matrix photodetector (OGS with MFP).

The goal is achieved by the fact that in the space between the aircraft and the most probable direction of a possible missile attack of the enemy by undermining the active defense element (AEZ), a cloud of fragments is formed, falling into which the rocket receives damage, leading to disruption of its performance.

As an AEZ, a pyrotechnic cartridge of infrared radiation with a combat module integrated into the pyrotechnic composition can be used. The striking module is structurally placed in the central cavity of the pyrotechnic cartridge and is made in the form of a cylinder, inside of which there is an explosive charge and a fragmentation belt of ready-made striking elements with control channels for detonating the explosive charge [see, for example, Miropolsky F.P. Methodology for substantiating the caliber and optimal parameters of fragmentation bombs. Tutorial. - M.: VVIA them. prof. NOT. Zhukovsky, 1977. - S. 64-67].

A diagram of a pyrotechnic cartridge with a striking module is illustrated in FIG. one.

In FIG. 1 is indicated:

1 - metal sleeve;

2 - contact electric igniter;

3 - electric igniter;

4 - pyrotechnic composition;

5 - explosive charge;

6 - fragmentation belt of ready-made striking elements (GGE);

7 - control channels for detonating an explosive charge.

The proposed method allows to increase the efficiency and reliability of protecting the aircraft from missiles equipped with OGS with MFP, and unlike the known one, it defeats the compartments of the attacking rocket, namely a fairing, a non-contact fuse with control equipment and an MFP cooling system, a cloud of fragments formed when an active bomb protection element, and brings them out of standing.

A method of protecting an aircraft from missiles equipped with OGSs with MFPs is implemented according to the algorithm shown in FIG. 2 as follows:

1) information about the position of the aircraft in space and its movement parameters is received from on-board sensors and on-board information and navigation system, and information on the initial conditions for launching an enemy attack missile (ARP) is received from the on-board defense complex;

2) using equations describing the movement of the rocket, the coordinates, speed, range, and time of finding the ARP are calculated according to the guidance method used in the missile guidance system and the issuance of data on the path of the ARP. The algorithm for calculating the trajectory of an attacking enemy rocket is presented in FIG. 3;

3) calculation of the motion parameters of the AEZ, which can be used as a pyrotechnic cartridge of infrared radiation with a combat module integrated into the pyrotechnic composition, consisting of an explosive charge and a fragmentation belt of ready-made striking elements with control channels for detonating the explosive charge, according to the algorithm for calculating the movement parameters the active security element shown in FIG. four:

a) information on the aircraft’s position in space and its motion parameters is received from on-board sensors and on-board information system, and information on the missile trajectory is received from the unit for calculating the motion parameters of the ATM;

b) the initial conditions for throwing the AEZ are calculated;

c) the calculation of the resistance function E;

d) the calculation of the parameters of the movement of the AEZ in the area of the trajectory necessary to meet with the ARP

d) the issuance of data on the trajectory and parameters of the throwing of the AEZ.

4) an analysis of compliance with safety conditions for the defended aircraft, calculated in the block calculating the parameters of the AEZ movement, is performed. If the condition that the throwing distance of the AEZ exceeds the minimum allowable throwing distance is met, a transition to the condition on the flight time of the AEZ t is performed;

5) an analysis of compliance with the conditions for the flight time of the AEZ t and the flight time of the ARP τ. In case the conditions are met that the flight time of the AEZ is equal to the time of flight of the ARP, a team is sent to shoot the AEZ.

The scheme of the combat use of the method of protecting aircraft from missiles equipped with OGS with MFPU is illustrated in FIG. 5.

Claims (1)

A method of protecting aircraft from missiles equipped with homing heads with a matrix photodetector, which consists in shooting active defense elements into the environment, characterized in that after the detection of the launch of the attacking missile, its trajectory parameters are determined to calculate the time of shooting and the time of undermining of the active defense elements , the shooting of active defense elements is carried out, ensuring their detonation on the trajectory of the rocket in the immediate vicinity of it, safely distance from the defended aircraft missile fragments falling into the cloud formed by active elements undermining the protection gets damaged, leading to a breach of her performance.

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