RU2371665C2 - Method of protecting land- and sea-based equipment - Google Patents

Abstract

FIELD: combat equipment.

SUBSTANCE: proposed method exploits the device useful load of which dissipates in atmosphere to form disk-shaped masking curtain developed in frontal plane wherein threat exists in electromagnetic radiation visible and IR spectra.

EFFECT: higher efficiency of protection.

3 cl, 4 dwg

Description

The invention relates to military equipment, mainly to methods and devices for dispersing a payload in the atmosphere, and is intended to protect sea and land based objects from high-precision weapons (WTO) by counterclosing masking curtains (MH) effective in visible, infrared (IR) and radar (RL) wavelength ranges of electromagnetic radiation.

Currently, the urgent task is to create the ability to control the shape and geometric dimensions of the MOH created with the aim of forming disk-shaped MH in the atmosphere, frontally deployed in the direction of the attacking WTO, both at a distance from the protected object and in close proximity to the positions of the attacking WTO, for maximum overlapping the line of sight of visual-optical, thermal imaging and radar aiming and pointing devices. The increase in the size of the MOH created on the oncoming trajectory, and its rotation in the frontal plane in the direction of the threat, makes it possible to block the maximum sector of the WTO attack with the minimum expenditure of protective equipment.

In addition, a reduction to certain thickness limits of the magnetic field along the direction of laser sounding of the target by the VTO systems reduces both the fronts and the duration of the reflected pulses, which makes it difficult to select the magnetic field by the VTO systems according to these criteria.

Setting the device frontally deployed MOH on the opposing guidance path of the attacking WTO allows you to increase the average value of the miss module by two or more times, and when setting the curtain in the immediate vicinity of the positions of the WTO there is a delay or failure to launch it.

A known method of protecting objects of technology by dispersing the payload in the atmosphere and a device for its implementation - US patent No. 5,445,078 from 07/12/1994, CL.6 F42B 12/36 (102/505), publ. 08/29/1995

The specified method consists in sequential radial emission into the atmosphere, in the direction of movement of the device, the payload in the form of dipole reflectors scattered by hot gases on the flight path. Formed by the device MZ is elongated in the form of a tape and has small dimensions in the frontal plane (in diameter of about 20 ... 30 m) and is effective in a narrow range of overlapping wavelengths, which is a significant drawback.

A device implementing the method includes rocket and warheads rigidly interconnected. The head part contains sections with a payload and a gas generator having a pyrotechnic connection with a fuse and a pyro-moderator.

The device operates as follows.

After the device is fired from the launch tube and it reaches a predetermined path section, the fuse, pyro-moderator and gas generator are triggered, the hot gases of which, mixed with the payload, emit and scatter it in the atmosphere, forming a train masking curtain that is effective in the radar wavelength range.

The disadvantages of this analogue (method and device) are the small size of the created MOH in the frontal plane relative to the threat and a narrow (only radar) range of overlapping wavelengths.

As a prototype, the method of dispersing the payload and the device for its implementation were selected - RF patent No. 229784 from 03.03.2003, class. 7 F42B 12/70, publ. 04/10/2005

The specified method consists in sequential radial ejection from the device, in the course of its movement, of the payload packed in modules with axial eccentricity, the disclosure of the modules and the dispersion of the payload in the atmosphere, effective in the radar wavelength range. Given the high speed of the device along the trajectory, the payload ejected by the modules from the head of the device and scattered in the atmosphere is formed in the form of a tape aerosol MZ stretched in the direction of the threat. The small size of the MZ formed by this device in the frontal plane, which does not allow reaching the maximum overlap of the sector of sight of radar guidance and aiming devices, as well as the narrow range of wavelengths it covers, are disadvantages that significantly reduce the efficiency when using this method. At the same time, in order to increase the effectiveness of protection in the radar wavelength range, salvo firing with jamming devices is necessary.

The device implementing the method includes a turbojet engine rigidly connected to the head part, a payload effective in the radar wavelength range, a fuse equipped with an ignition system.

The payload in the form of dipole reflectors located in disk modules having an axial eccentricity and a mechanism for opening and scattering is placed with the formation of an axial channel in the body of the head part, which has a mechanism of its destruction with the release of the payload into the atmosphere.

The device operates as follows.

After its launch, when the specified overload is reached, the inertial mechanism of the fuse is triggered, which initiates the charge of separation of the head part. The pressure of the hot gases of the separation charge destroys the body of the warhead at the installation site of the fuse, which fires off together with the body of the warhead. At the same time, the pyrotechnic mechanism for ejecting modules from the housing of the head of the device starts up.

Due to the eccentricity of the modules, their dispersion in the atmosphere occurs over a larger radius than in the analogue. When the modules are triggered, the payload is ejected and dispersed with the formation of a MZ, elongated along the direction of travel of the device and effective in the radar wavelength range.

The disadvantages of this technical solution are the small size of the MOH in the frontal plane relative to the threat and the narrow (only radar) range of overlapping wavelengths, which does not allow reliable, one device to overlap sectors of sight with WTO systems that have visible, infrared and radar reconnaissance and guidance channels.

The problem solved by the proposed method (and implementing its design) is to increase the efficiency of protection of objects of sea and land based equipment by creating in the atmosphere a counter large-scale wide-band MZ in one atmosphere, which maximally covers the visual sector of visual-optical, thermal imaging and radar guidance and targeting systems of the WTO .

The problem is solved by delivering a device to a given point on the trajectory of its flight of a payload dissipated in the atmosphere in such a way that a disk-like aerosol formation is formed that is frontally deployed in the direction of the attacking WTO and overlaps the sector of sight with visual-optical, thermal imaging and radar guidance and aiming systems of the WTO.

Unlike counterparts that create MZ, elongated devices along the flight and shielding the protected object only in the radar wavelength range and in the narrow sector of sight of the radar guidance and aiming systems of the WTO, in the proposed method, the payload of the device’s cassettes previously fan-shaped deployed counter to the attacking WTO, scattered in the form of a disk-shaped MZ, screening the protected object in a wide sector of sight with visual-optical, thermal imaging and radar systems the introduction and guidance of the WTO, which significantly increases the reliability and effectiveness of the protection of objects and thus gives reason to consider the proposed method as meeting the criterion of "inventive step".

Figure 1 shows a diagram of the use of the proposed method.

In the initial position, the device is in the launch tube of the object "a". The electrical contact device of the missile part "b" is connected to the threat detection tool, which determines the moment and direction of the launch of the device. When a signal is received about the presence of a threat, an electric pulse is sent to the electrical contact device of the missile part and the device is started. When the device starts from the launch tube, the pyrotechnic circuit of the device is initiated, which determines the algorithm for setting the MOH. After a specified time, the following occurs sequentially:

- separation of the head part "c" from the missile part "b" with a violation of its stabilization and braking;

- ejection from the body of the head of the cartridges with the payload "g" and their fan-shaped (due to a change in the position of the head after shooting each cartridge) dispersion in the atmosphere;

- after a predetermined time (determining the expansion of the cassettes in the frontal plane), the payload “g” is initiated and ejected from the cassettes, effective in the visible and infrared wavelength ranges, as well as the payload is ejected that is effective in the radar wavelength range;

- the formation in the atmosphere of a large-scale disk-shaped masking curtain “e” deployed in the opposite direction (threatening direction), which provides reliable overlap of the sighting sector of the guidance and aiming systems of the WTO in the visible, infrared and radar wavelength ranges of electromagnetic radiation.

The aim of the invention is to increase the efficiency of protection of objects of technology of sea and land based by creating in the atmosphere with one device an oncoming large-scale wide-range masking curtains, as much as possible overlapping the sector of the visual-optical, thermal imaging and radar guidance and aiming systems of the WTO.

This goal is achieved by the fact that in the proposed device protection of objects of sea and land-based equipment, including a missile part, rigidly connected to the head part, in the casing of which there are cassettes with a payload effective in the visible, infrared and radar wavelength ranges, while the cassettes have a central tubular channel and are connected to the unit by means of calibrated spring ring locks mounted in flanges of the cassettes, and in the free volume of each flange are installed dividing charges. The pyrotechnic connection of the separation charges with the propellant charges of the cassettes is carried out through pyro-moderators installed in the flanges of the cassettes, and the pyrotechnic connection of the separation charges with the combustion chamber of the rocket part of the device is carried out sequentially through the pyro-moderators installed in the tubular channels of the cassettes, while the pyro-moderator of the first from the cartridge adapter is sequentially pyrotechnically connected with an expelling charge and a deceleration unit installed in the adapter, and through the pre-chambers of the deceleration unit, internal volume of the combustion chamber portion of the rocket. The adapter, at the junction with the body of the warhead, has an internal diametered calibrated groove.

The installation of a moderator unit and an expelling charge in the adapter of the device allows you to separate the warhead from the rocket with a violation of the stabilization of the flight of the warhead and its sharp braking. Subsequent firing of warhead cartridges with payloads ensures their fan-shaped spread in space and the frontal location of the oncoming threat.

The use of ring spring locks for assembly of the cartridge block makes it possible to simplify the assembly technology of the block and to complete and assemble the cartridges in the block, taking into account the required characteristics and tasks for the masking curtain.

The use of an additional payload in the part of the cartridges (block), effective in the visible and infrared wavelength ranges, allows to increase the reliability of covering protected objects from the WTO, equipped, in addition to radar, with reconnaissance and guidance systems, effective in the visible and infrared wavelength ranges.

The use of tubular channels and separation charges between the cassettes in the cassettes, as well as pyro-retarders and propellant charges of the cassettes, makes it possible to shoot the cassettes fan-shaped with a spread of the cassettes at predetermined ranges with the formation of a disk-like aerosol formation that is frontally deployed facing the threat.

The proposed device design ensures that a wide-range masking curtain is set up at a given point in the space in a disk-like manner that is counter-deployed in the frontal plane to the threat and effective in the visible, infrared and radar wavelength ranges, which ensures reliable blocking of the sight lines of the WTO systems with visible, infrared and reconnaissance and guidance radar channels.

Unlike the analogues described in the known technical solutions, the combination of essential features in one proposed device for performing this or a similar technical task allows us to consider the proposed device meets the criterion of "inventive step".

Figure 2 shows a schematic representation of the proposed device.

It includes a rocket part 1, an adapter 2, a head part 3, a payload 5 placed in cassettes in the body of the head part 4, effective in the visible, IR and X-ray wavelength ranges. Cassettes through spring ring locks 6 (figure 3) are assembled in a block. In the free volume of the flange 7 of the cassettes, separation charges 8 are mounted pyrotechnically, through pyro-retardants 9 of the flanges connected with the propelling charges 10 installed in the batches of cassettes. Through the tubular channels 11 of the cassettes, the separation charges 8 are pyrotechnic, through the pyro-moderator 12 of the first from the adapter 3, the cassettes are connected to the knockout charge 13 and the deceleration unit 14 installed in the adapter, and through the pre-chamber of the pyro-moderators of the deceleration unit with an internal volume 15 of the combustion chamber of the rocket part 1 (Fig. .four).

The proposed device operates as follows.

When the threat detection tool is triggered, the device starts up, i.e. firing it from the launch tube with the simultaneous initiation of the deceleration unit 14, the operation of which with the initiation of the knockout charge 13 occurs on a given section of the flight path of the device. The operation of the expelling charge 13 leads to the destruction of the calibrated section 16 of the annular groove of the adapter and the shooting of the warhead from the rocket, with subsequent destabilization and braking of the warhead. At the same time, a hot retardant gas initiates a pyro-moderator 12 installed in the tubular channel 11 of the device’s first cartridge adapter 2. Pyro-moderator 12 through the tubular channel 11 of the cassette initiates a separation charge 8 between the first and second cassettes.

From the pressure of the hot gases of the separation charge 8, the spring lock 6 is installed, mounted in the flange 7 of the cartridge, and the cartridge is fired from the pipe of the head part 3.

Simultaneously with the hot gases of the separation charge, the pyro-retardants 9 of the first cartridge are initiated and through the tubular channel 11 of the second separation charge cartridge 8 of the second cartridge, it is separated from the third cartridge of the unit and fired from the pipe of the housing with the simultaneous initiation of the pyro-retardants 9 of the second cartridge. The ejection of subsequent cassettes of the unit into the atmosphere occurs in a similar way, while each cartridge is fired from the main body, it is displaced in space, as a result of which the cassettes are scattered fan-shaped in the frontal plane relative to the flight path of the device.

After a predetermined time, determined by the time of shooting all the cartridge cartridges from the warhead housing and their placement in space at predetermined distances from each other, the propelling charges of 8 cartridges from the pyro-retarders are initiated 9. The propelling charges of the cartridges with a payload effective in the visible and IR ranges, initiate it and by means of a piston ejected from the cassette body.

The ejection of a payload effective in the radar range from cassettes occurs without ignition.

The dispersion in the atmosphere of the payload of all the cassettes of the device block allows you to create a large, several times larger in size in the frontal plane compared to peers, an oncoming masking curtain, deployed in the form of a disk (wall) in the direction of the threat.

Thus, a wide-range masking curtain is installed in the atmosphere, which is effective in the visible, infrared and radar wavelength ranges, allowing the maximum visibility of the WTO reconnaissance and guidance systems with one device. The tests confirmed the claimed characteristics of the device.

Claims (3)

1. A method of protecting objects of marine and land-based equipment, including the launch of a device for protecting objects of sea and land-based equipment with a payload and dispersing the payload in the atmosphere with the formation of a masking curtain operating in the radar range of wavelengths of electromagnetic radiation, characterized in that the dispersion is useful loads in the atmosphere are produced with the formation of a disk-shaped masking curtain, deployed in the frontal plane in the direction of the threat, and additionally about the electromagnetic wave operating in the visible and infrared wavelength ranges. 2. A device for protecting objects of sea and land-based equipment, comprising a missile part, a warhead with a payload operating in the radar range of the radiation, and an initiator, characterized in that the rocket part is connected to the head by means of an adapter in which the expelling charge and the deceleration unit are located , the payload is made additionally operating in the visible and infrared wavelength ranges and is placed in cassettes with a tubular central channel assembled in a block by means of spring to ring locks mounted in the flanges of the cassettes, while in the free volume of the flanges there are separation charges, which are pyrotechnically connected to the propellant charges of the cartridge cassettes through the pyro-retardants located in the flanges, and through the tubular central channels of the cassettes and the pyro-retardant installed in the tubular central channel of the first cartridge adapter - with a knock-out charge installed in the adapter and a deceleration unit, which is pyrotechnically connected to the combustion chamber of the rocket part of the device. 3. The device according to claim 2, characterized in that a calibrated annular groove is made along the inner diameter of the adapter at the location of the knockout charge.

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