RU2340861C1 - 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 influence on clouds. The rocket contains a head part with the aerodynamic shroud with exhaust outlets, a channel draught of an active smoke and the executive mechanism of the self-liquidation including consistently established nozzle, pyrotechnic decelerator and a cap-detonator. Between the case of the head part and the aerodynamic shroud, the final collector with diffusion cell, connected with exhaust outlets is located. The nozzle of the executive mechanism of self-liquidation it is located in the diffusion cell, and a cap-detonator - it is longitudinal and screened from above by reflecting crossbeam. The invention provides increase of efficiency of action of a rocket and reliability of the executive mechanism of self-liquidation.

EFFECT: increase of efficiency of action of a rocket and reliability of the executive mechanism of self-liquidation.

3 cl, 1 dwg

Description

The invention relates to a device for changing atmospheric conditions, and more particularly to meteorological rockets for dispersion in clouds of aerosol generated by the combustion of a pyrotechnic smoke-generating bomb, with the aim of artificially causing precipitation or preventing hail.

The level of this technical field is characterized by rockets for active impact on the clouds described in patents RU No. 2129354, A01G 15/00, 1999 and No. 2274824, F42B 12/36, 2006, which contain a head fairing with exit openings for the generated aerosol placed in the casing is an active smoke bomb, a solid-propellant jet engine with a nozzle block, in the center of which an electrocapsule sleeve is installed, and a self-liquidation system.

A disadvantage of the described missiles is the possibility of hitting the population and animals in the area of firing with fragments formed during its self-destruction by undermining a blasting explosive charge, which create a danger at a distance of 50 m

More perfect is a rocket in which the noted drawback is eliminated, according to patent RU No. 21110040, F42В 12/36, 1998, selected by the number of matching features as the closest analogue of the proposed rocket.

The known rocket for active action on the clouds contains a two-mode engine, consisting of two buildings, each of which includes powder and pyrotechnic checkers connected by an adapter, a nozzle block carrying a central electrocapsule sleeve, an aerodynamic stabilizer, a head part with an active smoke bomb, when burning which generates an aerosol, and self-destruction system.

Outlets for active smoke (aerosol) are made in the fairing of the head part, the solid particles of which serve as moisture crystallization nuclei or as droplet concentrators in the treated 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.

A characteristic feature of the known rocket is the constructive implementation of the self-liquidation system in the form of distributed tape explosive charges along the rocket body and across the nozzle block and the head part.

Longitudinal tape charges when the shell is detonated create opposing streams of fragments directed towards the center of the rocket, which mutually break up when they encounter a loss of kinetic energy, which reduces the radius of expansion, and ring tape charges crush the most massive parts of the rocket.

The actuator of the self-liquidation system is initiated from the igniter device of the active smoke bomb through a pyrotechnic moderator in communication with the detonator capsule adjacent to the tape charge of the explosive.

The bomb of active smoke communicates by means of its supporting grating with a jet engine, therefore, the generated smoke additionally expires through the nozzle block. At the same time, in the engine chamber free of burnt powder bombs, condensation and coagulation of solid particles occurs, which are emitted into the atmosphere by larger and more active ones, which increases the efficiency of cloud processing.

However, a disadvantage of the known rocket is the ineffective main effect of the rocket on the dispersion of active smoke due to the loss of its volume as a result of the sticking of solid particles of the generated aerosol onto the walls of long and narrow gas ducts to the exit vents of the fairing.

Another disadvantage is the unsatisfactory functional reliability of the self-liquidating actuator due to the loss of part of the energy of the detonation pulse when it is forced to reorient in the radial direction in order to deflect the shock and detonation waves from a thin-walled cowl, which otherwise collapses. As a result of the destruction of the fairing, the rocket is not able to fulfill the destination functions, because as the aircraft degenerates, and the atomization system of active smoke is destroyed and does not work.

The problem to which the present invention is directed is to increase the efficiency of the main action of the rocket for its intended purpose and the functional reliability of the actuator for its self-liquidation.

The required technical result is achieved by the fact that in the known rocket for active influence on the clouds, in the head part of which there is an aerodynamic fairing with outlet openings distributed along its perimeter, a channel bomb of active smoke, an igniter and an actuator for self-liquidation, including serially mounted nozzles, a pyrotechnic moderator and detonator capsule adjacent to the tape charge of the explosive, radially and longitudinally distributed in the rocket, with According to the invention, an exhaust manifold with a diffuser communicating with the outlet openings is located between the body of the head part and the fairing, the nozzle of the self-liquidation actuator is located in the diffuser, and the detonator capsule is longitudinally and shielded from above by a reflecting crossbar, with a conical cone on the lower end of the pyrotechnic moderator. a recess in the form of a confuser communicating with the nozzle, and at the upper end - in the form of a cumulative funnel directed to the side onu detonator capsule, while the actuator self-destruction is equipped with an additional detonator capsule installed parallel to the first, and duplicated with it.

Distinctive features are aimed at increasing the effectiveness of the meteorological rocket for its intended purpose and its functional reliability while simplifying the design of the gas-dynamic device for atomizing active smoke, the self-liquidating actuator and the head of the rocket as a whole.

The location of the exhaust manifold with a diffuser between the body of the head and the fairing allows you to compactly integrate a device for dispersing active smoke, while ensuring the bearing strength of the head of the rocket. The generated gaseous products of combustion of the pyrotechnic composition of the channel checker feed directly to the distributed outlet openings, which contributes to a more efficient use of active smoke in the atmosphere, since its solid particles do not undergo agglomeration and do not adhere to the walls of labyrinth gas ducts, which are excluded from the structure by a known design.

The communication of the collector diffuser with the outlet openings serves to inhibit the flow of active smoke before distribution over the outlet openings located around the perimeter of the fairing. In the diffuser there is a drop in speed and an increase in pressure of the active smoke stream, which is jet emitted into the atmosphere, accelerating when passing through the outlet openings of a much smaller diameter, which contributes to a more efficient atomization of the functional aerosol in the treated cloud.

In this case, there is no agglomeration of solid smoke particles, which ensures the presence of condensation centers of different fractionations in the treated cloud, taking into account the additional smoke flow through the free engine casing and the nozzle block of the rocket, which contains a priori larger solid particles.

The nozzle arrangement of the self-liquidating actuator actuator in the diffuser above the channel block of active smoke provides unhindered passage of the initiating heat pulse from the coaxially mounted igniter device of the head part. This provides simultaneous ignition of the pyrotechnic charge of the moderator with the active smoke bomb, which is duplicated by direct contact with hot gaseous products of combustion of the active smoke bomb entering the diffuser to guarantee.

Dyuza performs the functions of a lens focusing the fire force of a remotely mounted igniter device of a channel bomb of active smoke at the same time igniting the pyrotechnic composition of the moderator of the actuator of self-liquidation of a rocket.

Thus, a reliable scheme of parallel initiation of ignition of the channel checker of active smoke and a pyrotechnic moderator from one energy source is implemented.

Placing the detonator capsule longitudinally, directly adjacent to the pyrotechnic moderator, increases the reliability of the self-liquidation actuator.

Shielding the detonator capsule from above with a reflecting bar protects the thin-walled cowl from the destructive action of shock and detonation waves, reflecting them. The compact design of the self-destruction mechanism allows you to place the detonator capsule longitudinally in the fire chain and in the head of the rocket.

The execution at the ends of the pyrotechnic moderator of the actuator for self-liquidation of conical recesses provides the formation of sharply directed torches initiating elements of the fire chain.

Providing the self-liquidation actuator with an additional detonator capsule installed parallel to the first one and duplicated with it allows one to increase the operational safety of the rocket for the population in the firing area, because radiation detonator caps in the fire chain act independently to initiate detonation tapes distributed around the perimeter of the rocket, which fragmented into predetermined mass-dimensional parts.

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

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

The invention is illustrated by the drawing, which has a purely illustrative purpose and does not limit the scope of the claims of a combination of essential features. The drawing shows: in Fig.1 - schematically a General view of the rocket; figure 2 - the head of the rocket.

The proposed meteorological rocket contains a head part 1 closed by an aerodynamic fairing 2, a jet engine 3 with two channel powder checkers 4, 5 coaxially mounted in series in a common housing 6, and an ignition charge 7 located opposite the central electrocapsule sleeve 8 of the nozzle block 9 equipped with a blade stabilizer 10.

The igniter charge 7 is installed in the lattice 11, based on the end protrusion of the nozzle block 9, the forming receiver 12, separating the electrocapsule sleeve 8 and the igniter charge 7.

Channel powder checkers 4 and 5, having an equal burning set, are adjacent from different sides to the separation diaphragm 13 and are installed in the housing 6 with radial annular gaps 14 and 15, respectively, and the size of the gap 14 adjacent to the nozzle block 9 exceeds the upper ( the drawing) of the gap 15, is inversely proportional to the ratio of the diameters of their channels.

The housing 6 through the adapter 16 is connected with the head part 1, carrying channel pieces of active smoke 17, which communicate with the igniter device 18 installed in the adapter 16.

The igniter device 18 is placed on the nozzle 19, adjacent to the top of the pyrotechnic moderator 20, based on the grate 21, separating from the channel powder checkers 5 of the engine 3.

An exhaust manifold 22 is mounted between the body of the head part 1 and the fairing 2, in which a diffuser 23 which is distributed along the perimeter of the outlet openings 24, is arranged in the diffuser 23 in communication with the channel blocks of the active smoke.

In the diffuser 23 is located coaxial to the ignition device 18 nozzle 25 of the actuator 26 of self-destruction of the rocket.

The actuator 26 sequentially includes (FIG. 2): a pyrotechnic moderator 27, two parallel-blocked beam detonator capsules 28, each of which is adjacent to the tape charge 19 of the explosive, radially and longitudinally distributed around the perimeter of the rocket. An explosive charge 29 is shielded from above by a rigid reflective beam 30.

The tape charge 29 communicates with the longitudinal tape charges 31, placed on the surface of the housings of the head part 1 and the engine 3, and the ring charge 32 of the explosive in the nozzle block 9 (figure 1).

Pyrotechnic moderator 27 (figure 2) of the actuator 26 self-destruction at the ends made with tapered recesses 33 and 34, the lower and upper according to the drawing, respectively.

The lower recess 33, communicating with the nozzle 25, acts as a confuser to form a center-directed force from the incoming gaseous hot products.

The upper recess 34, directed towards the beam detonator capsules 28, is a cumulative funnel designed to concentrate the combustion products of the pyrotechnic composition of the moderator 27 into a dense heat flux.

The rocket operates as follows.

When the rocket is launched, electrical voltage is supplied to the electrocapsule sleeve 8, the ignition charge of which initiates an ignition charge 7.

The sharply directed torch of the triggered igniter charge 7 ignites the channel powder blocks 4, 5 and the pyrotechnic composition of the moderator 20. Moreover, the blocks 4, 5 burn along the entire developed surface of the central channels and outside in the annular gaps 14 and 15, respectively, and the moderator - at the end.

At the time of starting, the pressure inside the engine 3 increases rapidly and the powder gases rush to the nozzle block 9 to exit, in the receiver 12 there is a deceleration of gas flows and smoothing of the peak pressure with a relatively smooth increase before feeding into the nozzle block 9.

Upon reaching the required thrust, the missile leaves the launcher on the flight path to the cloud being processed.

The means of communication of the solid-fuel engine 3 in the optimal ratio of geometric parameters: the central channels of the checkers 4, 5, radial annular gaps 14, 15 of the grill 11, 21 and the separation diaphragm 13 - provide functional unity of the stable operation of the engine 3 in a stationary mode throughout the entire cycle of combustion of powder bombs 4 and 5.

The burning time of the moderator 20 is a multiple of the times the burning time of the channel powder guns of engine 3 (10s and 3s, respectively), which makes it possible for the rocket to develop the maximum marching speed of the inertial movement to the target.

After that, with the nozzle 19, the flat combustion front of the moderator 20 is transformed into a torch, initiating an igniter device 18, igniting the pyrotechnic composition of the channel checker 17, during the combustion of which an aerosol is generated (active smoke containing solid particles that serve as droplet formation centers in the cloud atmosphere).

The generated aerosol enters the diffuser 23, where the gaseous products of combustion of the checkers 17 expand and with increased pressure are ejected through the distributed outlet openings 24 of the collector 22.

At the same time, the hot combustion products of the checkers 17, formed by the nozzle 25 and the confuser 33 into a concentrated torch, ignite the pyrotechnic composition of the moderator 27, the burning time of which is calculated to be guaranteed longer than the burning time of the checker 17.

The generated aerosol during the burning of the checkers 17 also spreads through the housing 6 of the engine 3, which was free by that time from the burned checkers 4, 5, and is released into the atmospheric cloud through the nozzle block 9.

When the aerosol moves along engine 3, agglomeration of suspended solid particles occurs, therefore, particles of different fractionalities and activities enter the treated cloud, which intensifies the process of precipitation more efficiently.

When the front of combustion of the pyrotechnic composition exits to the upper end of the moderator 27, the cumulative funnel 34 forms a fire torch, from which the detonators 28 detonators, which are blocked in parallel, are triggered.

The detonation wave from the detonator caps 28 is directly transmitted to the adjacent tape charge 29 of the explosive, while being reflected from the shielding bar 30, preventing its destructive effect on the fairing 2.

When the transverse tape charge 29 is detonated, the massive collector 22 and the volume fairing 2 are destroyed.

The detonation impulse from the charge 29 is transmitted to the longitudinal tape charges 31 and the ring charge 32, tearing the housing 6 and crushing the engine 3, destroying the nozzle block 9, respectively, to the parts that are safe for human life in the place where they fall.

Bench and full-scale tests of prototypes of the proposed rocket actually confirmed the feasibility of constructive improvements to the existing full-time meteorological rocket, which is more technologically advanced to manufacture, functionally reliable and characterized by a higher efficiency of active smoke, which allows recommending it for state tests with a view to putting it into service.

Claims (3)

1. A rocket for the active impact on the clouds, in the head of which there is an aerodynamic fairing with outlet openings distributed around its perimeter, a channel bomb of active smoke, an igniter and an actuator for self-liquidation, including a nozzle in series, a pyrotechnic moderator and an detonator capsule adjacent to the tape charge of the explosive, radially and longitudinally distributed in the rocket, characterized in that between the body of the head part and the fairing an exhaust manifold with a diffuser in communication with the outlet openings is located, a nozzle of the self-liquidation actuator is located in the diffuser, and the detonator capsule is longitudinally and shielded from above by a reflecting crossbar. 2. The rocket according to claim 1, characterized in that at the lower end of the pyrotechnic moderator of the actuator of self-liquidation, a conical recess is made in the form of a confuser communicating with the nozzle, and at the upper end - in the form of a cumulative funnel directed towards the detonator capsule. 3. The rocket according to claim 1 or 2, characterized in that the self-liquidation actuator is equipped with an additional detonator capsule mounted parallel to the first and duplicated with it.

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