RU2340862C1 - Missile for active impact on clouds - Google Patents

Abstract

FIELD: weapons.

SUBSTANCE: invention concerns devices for change of atmospheric conditions, in particular, to rockets for impact on clouds. The rocket contains a head part with the draught of the active smoke established in it, two is longitudinal the located channel powder draughts established with radial backlashes concerning the case, nozzle block with the central electrocapsule plug and the jet engine. In addition the rocket is supplied wit a firing charge established coaxially to the electrocapsule plug, and a receiver located between the firing charge and the electrocapsule plug. The channel powder draughts are executed with the equal arches of burning, established in the general case and divided by a diaphragm, and in an adapter between the jet engine and a head part is located delay pellet which end face turned to the device of initiation of a channel draught of an active smoke, is executed in the form of a cumulative funnel adjoining to its nozzle.

EFFECT: increase of efficiency of impact on clouds at the expense of increase of accuracy of hit in them.

2 cl, 1 dwg

Description

The invention relates to a device for changing atmospheric conditions, and more particularly, to rockets for dispersion in the clouds of aerosol generated by the combustion of a pyrotechnic smoke-generating bomb, to prevent hail and cause precipitation.

The level of this technical field is characterized by the design of a rocket for active impact on clouds according to patents RU 2110040, F42В 12/36, 1998 and 2129354, A01G 15/00, 1999, containing a two-mode engine, consisting of two buildings, each of which includes powder and pyrotechnic pieces and interconnected by an adapter, a nozzle block carrying a central electrocapsule sleeve, an aerodynamic stabilizer, a head part with an active smoke bomb, during the combustion of which an aerosol is generated, and a self-liquidation system.

In the fairing of the head part, openings are made for the exit of the generated smoke (aerosol), the solid particles of which serve as nuclei of moisture crystallization or as concentrators of droplet formation in the cloud.

Between the autonomous sections of the jet engine, as well as between the engine and the head part, pyrotechnic amplifiers are installed that form an ignition pulse transmitted to the powder block of the second section and the block of active smoke, respectively.

As the closest analogue of the proposed rocket according to the number of matching features, the rocket according to patent No. 2129354 was selected, in which the checkers of the jet engine are installed with a gap relative to the body, which increases the combustion surface and the dynamics of the rocket entering the mode with increasing flight distance.

A characteristic feature of the described rocket is that the head part is equipped with an actuator mounted on the diaphragm facing the amplifier, including a moderator and a detonator capsule of the self-liquidation system.

The detonator capsule of the actuator communicates with distributed longitudinal and ring belt explosive charges, the operation of which, after a delay after the engine is finished, ensures the destruction of the rocket into safe fragments that do not pose a danger to the population of the area where the rockets are used.

A disadvantage of the known rocket is the unsatisfactory functional reliability of its dual-mode jet engine under the sequential action of autonomous sections, each of which additionally uses pyrotechnic end-combustion checkers associated with amplifiers for transmitting an ignition pulse to stabilize the combustion of channel powder bombs, which significantly reduces the flight range of the rocket.

The structural complication of the fire chain reduces the functional reliability of the rocket.

In addition, the connection of the pyrotechnic checker of the second section of the engine with the checker of active smoke by means of an amplifying charge ensures the ignition of the latter immediately after the end of the jet engine, that is, before the rocket enters the cloud being processed. In this case, the generated working aerosol consumed on approach is not used for its intended purpose, which further reduces the effectiveness of the impact on the cloud.

The problem to which the present invention is directed, is to eliminate the noted drawbacks to increase the functional reliability of the rocket and the effectiveness of the active impact on the clouds.

The required technical result is achieved by the fact that the known rocket for active exposure to clouds, comprising a head part with an active smoke bomb installed therein, equipped with initiation means, a collector and a fairing with outlet openings, a jet engine connected to the head part via an adapter, two longitudinally arranged channel powder checkers installed with radial clearances relative to the body, nozzle block with a central electrocapsule sleeve and aerodynamic blade the tabulator, according to the invention, is equipped with an ignition charge mounted coaxially to the electrocapsule sleeve and a receiver located between the ignition charge and the electrocapsule sleeve, wherein the channel powder bombs are made with equal combustion arches, are installed in a common housing and are separated by a diaphragm, and in the adapter between the jet engine and the head part is a powder moderator, the end of which, facing the device for initiating the channel pieces of active smoke, is made in the form of adjacent the cumulative funnel to its nozzle, while the radial clearance between the engine block and the first checker from the nozzle block side exceeds the similar gap of the second checker, and the ratio of these values is comparable with the ratio of the passage size of the axial channel of the second checker to the passage size of the axial channel first checkers.

Distinctive features ensured a stable operating mode of the jet engine over the entire flight path of a greater distance while simplifying the design and manufacturing technology of the rocket, as well as the rational use of the generated aerosol for the main purpose directly in the cloud being processed due to the new interconnection of the rocket's structural elements.

The installation of the igniter charge coaxially with the electrocapsule sleeve, together with the receiver located between the ignition charge and the electrocapsule sleeve, ensured reliable automatic ignition of the channel powder guns of the jet engine from the electric pulse of the launcher.

The proposed interconnection of the structural elements of the rocket design provided increased dynamics of the descent from the launcher, which improves ballistics and reduces the negative impact of surface wind on the deviation of the flight path from the target, thereby increasing the accuracy of getting into the processed cloud for a more effective impact on it.

The implementation of the channel of the powder guns of the engine with equal arches, despite the fact that they have different geometric dimensions, provides a comparable time of burning and a uniform outflow of gaseous products of combustion during the entire operation of the engine. Thus, the rocket engine, in which ballast pyrotechnic charges for stabilizing the combustion of powder bombs are excluded, operates in a stationary design mode.

This ensures uniform burning of both pieces simultaneously along the entire perimeter due to the back-up of gaseous products of combustion to the nozzle block and their forced flow from the center to the periphery, which improves the traction characteristics of the rocket, its dynamics and the effectiveness of the intended purpose.

As a result of optimization of the gas-dynamic mode of the engine’s operation, the rate of rocket descent from the launcher increases, which improves ballistics and reduces the negative effect of surface wind on the accuracy of the given trajectory of its flight to the target.

The direct connection of the two-channel pyrotechnic checkers by means of calibrated aperture openings simplified the implementation of a single stable gas-dynamic regime throughout the operation of the jet engine. This allowed the use of a common igniter, functionally connected with the receiver, for the simultaneous ignition of both checkers installed with an annular gap relative to the housing, by the heat pulse of the coaxial electrocapsule sleeve.

In the receiver, the generated gaseous combustion products accumulate and mix to equalize the pressure and temperature before expiration through the nozzle block, creating a coaxial draft.

The installation of two-channel powder checkers in a common housing, without intermediate elements between them, simplified the design of the rocket and the serial production technology by reducing the number of assembly units and reducing labor intensity.

The installation between the engine checker and the active smoke checker of a pyrotechnic moderator is intended to create a time delay in the activation of smoke generation directly in the cloud after the rocket dynamically exits at a given flight speed. Productive atomization of the aerosol directly in the cloud provides an increase in the effectiveness of the main action of the rocket for its intended purpose.

The execution of the end face of the powder retarder, facing the device for initiating the channel block of active smoke, in the form of a cumulative funnel, together with an adjacent nozzle, makes it possible to form a force of flame from a relatively slowly layer-by-layer burning composition sufficient to reliably ignite the block of active smoke after a predetermined delay time after the engine has ended .

The placement of gunpowder channel blocks with an annular gap relative to the body has increased the combustion surface and the dynamic characteristics of the rocket in the same dimensions.

Therefore, each essential characteristic is necessary, and their combination is sufficient to achieve a novelty of quality that is not inherent in the signs of disunity, that is, the technical problem posed in the invention is not solved by the sum of the effects, but by a new effect of the sum of the signs.

The invention is illustrated in the drawing, which shows the proposed rocket.

The drawing has a purely illustrative purpose and does not limit the scope of the rights of the aggregate of essential features of the formula.

The proposed rocket for active impact on the clouds includes sequentially installed head 1, a jet engine 2 and a nozzle block 3 with a blade aerodynamic stabilizer 4.

In the head part 1, a channel checker 5 of active smoke is installed, which communicates with the device 6 for its initiation.

A collector 8 closed by a fairing is fixed in the head part 1.

Distributed openings 9 are made in the fairing 7 for the exit of the aerosol generated during the burning of the checkers 5 and a self-liquidation mechanism is mounted in it, including a moderator 10 and a detonator capsule 11 adjacent to the tape charge 12 of the explosive, made in the form of a ring covering the collector 8 associated with longitudinal tape charges 13, distributed around the periphery of the rocket.

The head part 1 by means of an adapter 14 is rigidly connected with the housing 15 of the jet engine 2, in which two channel powder checkers 16 and 17 are longitudinally separated by a diaphragm 18 with calibrated holes 19.

A pyrotechnic moderator 20 is installed in the adapter 14 between the checker 17 of the engine 2 and the device 6 for initiating the checker 5 of active smoke 20. The end of the pyrotechnic moderator 20 is facing the device 6 for initiating the channel checker 5 of active smoke and is made in the form of a cumulative funnel 21 adjacent to the nozzle 22 of the igniter device charge 6.

Channel powder checkers 16 and 17 are made with equal arches of combustion and relative to the housing 15 are mounted with radial gaps 23 and 24, respectively, and the gap 23 is made larger than the gap 24.

The ratio of the bore of the gap 23 to the bore of the gap 24 is comparable with the ratio of the bore of the axial channel of the block 17 to the bore of the axial channel of the block 16.

Between the checker 17 and the adapter 14, a communication lattice 25 with a powder moderator 20 and its axial channel with a radial clearance 24 is installed.

The checker 16 is installed in an annular support 26, bearing an axial igniter charge 27, axially located with the central electrocapsule sleeve 28 of the nozzle block 3.

An annular support 26 is mounted at the end of the nozzle block 3, in which a receiver 29 is formed separating the electrocapsule sleeve 28 and the igniter charge 27.

Along the perimeter of the nozzle block 3, an annular explosive charge 30 is mounted, connected through longitudinal tape charges 13 with a detonator capsule 11 of the self-liquidating actuator.

The rocket operates as follows.

To launch a rocket, an electric voltage is supplied to the electrocapsule sleeve 28, the actuation pulse of which ignites a charge 27 that forms a force of flame propagating along the axial channels of the powder checkers 16 and 17, almost simultaneously igniting them.

The gaseous combustion products of the checkers 16, 17 through the axial channels enter the receiver 29 and through the diaphragm 18 and the grating 25 into the gaps 23 and 24, respectively. In this case, the pyrotechnic charge of the moderator 20 is also ignited, the time of layer-by-layer burning of which is a multiple of the time of burning of the drafts 16 and 17 (10 s versus 3 s, respectively).

Hot combustion products in the gaps 23, 24 ignite, respectively, the powder bombs 16 and 17 additionally from the outer surface and enter the receiver 29.

At the initial moment of starting, the gaseous products of combustion of the drafts 16, 17 in the receiver 29 expand and mix with a relatively smooth increase in pressure, after which they dynamically expire through the nozzles of block 3.

Upon reaching the thrust sufficient for the squeezed stopper of the launcher, the missile leaves its guides and starts under the action of jet jets from the nozzle block 3.

After the combustion of the checkers 16, 17, the rocket develops a marching speed, with which it inertially moves toward the target.

Further, during the combustion of the powder charge of the moderator 20, the cumulative funnel 21 forms a sharply directed torch, which is fed through the nozzle 22 to ignite the composition of the device 6, which initiates the combustion of the channel checker 5, generating an aerosol entering the collector 9 and then through the distributed outlet openings 9 to the atmosphere, directly to the cloud.

Simultaneously with this heat pulse of the device 6, the combustion of the composition of the moderator 10 is initiated, the burning time of which is selected with a guarantee longer than the burning time of the active smoke checkers 5.

The generated aerosol to the atmosphere also expires through the nozzle 22, the grill 25 and the diaphragm 19 of the housing 15 of the jet engine 2, free of burnt drafts 16, 17, the receiver 29 and the nozzle of the block 3.

In the process of movement of the generated smoke through the housing 15, condensation and coagulation of solid particles occurs with the formation of an aerosol.

With this duplicated scheme for the delivery of products of combustion of the checkers 5, a balanced amount of large and small particles (the latter flow directly from the checkers 5 through the outlet openings 9 of the collector 8) is distributed in the cloud being processed, which act as droplet formation centers, as a result of which precipitation actively falls.

After the composition of the moderator 10 is burned, the detonator capsule 11 is triggered, initiating the explosive of the tape charges 12, 13, from which the rocket is destroyed along and across, respectively, to safe parts, without the formation of damaging fragments that are dangerous for the population of the area affected by the clouds.

Tests of the prototypes of the proposed missiles have confirmed the higher, compared with the standard rocket "Alazan-2M", the impact on the clouds, which is characterized by the following destination indicators.

A comparative analysis of the proposed technical solution with identified analogues of the prior art, from which the invention does not explicitly follow for a specialist in meteorological rockets, showed that it is not known, and given the possibility of industrial serial production of rockets for active impact on the clouds, we can conclude that patentability criteria.

Claims (2)

1. A rocket for active exposure to clouds, comprising a head part with an active smoke bomb installed in it, equipped with initiation means, a collector and a fairing with outlet openings, a jet engine connected to the head part via an adapter, two longitudinally located channel powder bombs installed with radial clearances relative to the housing, the nozzle block with a central electrocapsule sleeve and a blade aerodynamic stabilizer, characterized in that it is equipped with ignite a charge installed coaxially to the electrocapsule sleeve and a receiver located between the ignition charge and the electrocapsule sleeve, the channel powder checkers having equal combustion arches, installed in a common housing and separated by a diaphragm, and a powder moderator is located in the adapter between the jet engine and the head part , the end of which, facing the device for initiating a channel checker of active smoke, is made in the form of a cumulative funnel adjacent to its nozzle. 2. The rocket according to claim 1, characterized in that the radial clearance between the engine housing and the first checker from the nozzle block side exceeds the similar clearance of the installation of the second checker, the ratio of these values being comparable with the ratio of the passage size of the axial channel of the second checker to the value passage section of the channel of the first checker.