RU74268U1 - MISSILES FOR CLOUD INFLUENCE - Google Patents

Abstract

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

The rocket for impact on clouds contains a head part with a bomb of active smoke, closed by a fairing equipped with a smoke exhaust manifold and an actuator for self-liquidation, a solid propellant jet engine made of two successive sections, each of which includes a channel powder bomb, pyrotechnic bomb and an amplifying charge, and also a nozzle block with aerodynamic blades and a central electrocapsule sleeve.

New is that the pyrotechnic checkers of each section of the jet engine are made in the form of a moderator, the burning time of which is multiple times the burning time of the powder checkers, in a ratio of 4: 1.

The proposed technical solution ensured the unification of the push-pull operation of a solid-fuel jet engine, each section of which operates sequentially in two modes automatically, namely: with an active traction component and an inertial pause during active gas generation, which reduces the rocket’s bottom drag, which is aimed at the formation of a shallow trajectory of its motion to increase duration of interaction with the cloud being processed.

Automatic duplication of the dual-mode operation of each section of the jet engine ensured the rocket was raised to a predetermined height for direct cloud processing at maximum length.

Description

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

A rocket according to patent FR 2097895, F42B 00, 1972, which contains an active smoke bomb placed in a head part enclosed by a fairing with exit openings for a generated aerosol, a solid propellant rocket engine with a nozzle block equipped with a stabilizer and a central one, characterizes the level of the art. electrocapsule sleeve, as well as a self-destruction device.

Outlet openings radially located in the fairing of the head part are used to disperse the generated aerosol (active smoke) into the treated cloud, the solid particles of which are moisture crystallization nuclei or droplet condensers to form precipitation.

A disadvantage of the described rocket is the possibility of hitting people and animals in the area of its use by fragments formed during self-destruction by undermining a blasting explosive charge.

The noted drawback is eliminated in missiles with a more advanced self-destruction system in the form of distributed tape charges of explosive along the rocket body interacting with ring tape charges located across the nozzle block and the head part where the actuator is located (see patents RU 2110040, F42В 12/36 , 1998, 21229354, A01G 15/00, 1999 and 2251655, F42В 12/36, 2005)

The actuator of the self-liquidation system is located in the fairing collector; its decelerating charge is initiated automatically from the igniter of the active smoke bomb. The deceleration time (burning of a pyrotechnic charge) is guaranteed to exceed the operating time of the active smoke bomb. The self-destruction system is triggered by a detonator capsule.

Longitudinal ribbon charges when the shell is detonated create oncoming streams of fragments directed towards the center of the rocket, which mutually split upon meeting with a loss of kinetic energy, and ring ribbon charges fragment the most massive parts of the rocket into fragments that do not have destructive force.

As the closest analogue, the rocket according to patent RU 2110040, F42B 12/36, 1998, which contains a warhead with a saber, was selected

active smoke covered by a cowl equipped with a smoke exhaust manifold and an self-liquidating actuator, a solid-fuel jet engine made of two successive sections, each of which includes a channel powder bomb and an amplifying charge, as well as a nozzle block with aerodynamic blades (stabilizer) and a central electrocapsule sleeve .

In the known rocket, the jet engine is made dual-mode to adjust and optimize the altitude and range of its flight.

Two operating modes of the jet engine are ensured by the sequential functioning of its two sections as a whole for the high-speed rise of the rocket to a relatively large height. In the sections, structural elements are accordingly selected according to the composition, mass and nature of their combustion, which is laborious and economically unjustified.

The main disadvantage of the known rocket, the flight path of which is a steep parabola, provided by the operating mode of the solid-fuel jet engine, is the unproductive action for the intended purpose, since a significant part of the active smoke is sprayed above the treated cloud, and the generated active smoke is essentially used only on the ascending and the descending parts of its steep flight path intersecting the dimensions of the cloud.

The task to which the present utility model is directed is the constructive improvement of a meteorological rocket to increase the effectiveness of the action for its main purpose.

The required technical result is achieved in that in a known rocket for impact on clouds containing a head part with an active smoke bomb covered by a fairing equipped with a smoke exhaust manifold and an self-liquidation actuator, a solid propellant jet engine made of two successive sections, each of which includes a channel a powder checker, a pyrotechnic checker and an amplification charge, as well as a nozzle block with aerodynamic blades and a central electrocapsule sleeve, at the suggestion of the authors, the pyrotechnic checkers of each section of the jet engine are made in the form of a moderator, the burning time of which is multiple times the burning time of the powder checkers, in a ratio of 4: 1.

Distinctive features ensured the unification of the two-stroke operation of a jet engine, each section of which operates sequentially in two modes automatically, namely: with an active traction component and an inertial pause during active gas generation, which reduces the rocket’s bottom drag, which is aimed at the formation of a gentle trajectory of its motion to increase the duration of interaction with a processed cloud.

The proposed layout and the constructive ratio of the checkers in each section of the jet engine create successively two modes of operation: energy when burning a powder checker, providing a rocket

traction, and inertial when burning the pyrotechnic checker of the moderator, when the rocket moves ballistically, gravitationally leaning toward the cloud being processed.

Duplication of these modes by the second section of the jet engine provides the necessary increase in thrust for lifting to a given working height and additional angular displacement of the rocket trajectory to the horizon, which in total allows active smoke to be sprayed directly in the treated cloud at its maximum extent.

In this case, the amplification charge, which acts as an igniter, initiates the start of the second section of the jet engine, the amplification charge of which, in turn, ignites the channel piece of active smoke of the head part, which occurs automatically at predetermined intervals.

The ratio of the retardation times of the moderator and the powder checker in each section of the jet engine is experimentally optimized and unified as 4: 1 to achieve the maximum extent of the flat portion of the rocket trajectory inside the treated cloud, which significantly increases the efficiency of atomization and the action of the generated reagent.

Therefore, each essential feature 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 task posed is not solved by the sum of the effects, but by a new effect of the sum of the attributes.

The essence of the utility model is illustrated in the drawing, which shows the proposed rocket for impact on the clouds. The drawing has purely illustrative purposes and does not limit the scope of the claims of the totality of the essential features of the formula.

In a thin-walled housing 1 by means of bearing shells 2, 3, 4 are rigidly mounted in series:

- a collector 5, on which a fairing 6 is fixed, and a head part 7 with a checker 8 of active smoke;

- two sections 9 and 10 of the jet engine, each of which includes a channel powder block 11, a pyrotechnic block 12 end-face combustion and an amplification charge 13;

- nozzle block 14 with a central electrocapsule sleeve 15 and aerodynamic blades 16.

In the collector 5, communication channels 17 are made with radial openings 18 distributed around the circumference of the fairing 6 for emitting active smoke, and an actuator for self-liquidation is placed, which includes a focusing inductor 19, a pyrotechnic moderator 20, and a detonator 21 connected with continuous tensile charges 22 (longitudinal) and 23, 24 (transverse) mounted on the manifold 5 and the nozzle block 14, respectively.

A diaphragm 25 is mounted on the nozzle block 14, on which the channel powder block 11 of the first section 9 of the jet engine rests, bounded above by a shell 2, inside which a pyrotechnic block 12 and an amplification charge 13 are sequentially mounted.

On the shell 2 is placed a diaphragm 26 separating sections 9 and 10 of the jet engine.

On the diaphragm 26, a channel powder checker 11 of the second section 10 is installed, bounded above by a shell 3, inside of which a pyrotechnic checker 12 and an amplification charge 13 are sequentially installed.

The head part 7 rests on the shell 3 with the active smoke placed inside the checker 8, bounded on top by the shell 4.

The focusing inductor 19 of the self-liquidation actuator is located coaxially with the amplification charge 13 of the second section 10 of the jet engine and communicates with it through the central channel of the checker 8.

In the nozzle block 14, a receiver 27 is formed under the diaphragm 25.

The rocket operates as follows. To launch a rocket mounted on a launcher, an electric voltage is supplied to the electrocapsule sleeve 15, the pulse of which simultaneously ignites the channel powder block 11 and the pyrotechnic block 12 of the first section 9 of the jet engine.

The gaseous products of combustion of the checkers 11, 12 enter the receiver 27, where they are mixed, while the temperature and pressure are equalized. From the receiver 27, gaseous products are dynamically ejected through the nozzles of the block 14, developing traction.

Upon reaching the thrust sufficient to depress the launcher stopper, the missile leaves its guides and starts under the action of jet jets from the nozzle block 14.

Within 2 s, the powder bomb 11 burns out, providing a high impulse of specific thrust and rocket propulsion. When burning the pyrotechnic checkers 12, gaseous high-temperature products are formed, which can reduce the back aerodynamic drag and the mass of the rocket, which is accelerated.

During autonomous combustion of the pyrotechnic checker 12 (moderator), the full jet engine impulse decreases over the next 6 s, as a result of which the velocity of the rocket decreases and its angular inclination to the horizon occurs during inertial movement along a ballistic trajectory, more gentle.

When the checkers 12 are burned, the amplification charge 13 ignites with a heat pulse, which then initiates the burning of the checkers 11, 12 of the second section 10 of the jet engine. The operation of the structural elements of section 10 is similar to that described in section 9.

The missile receives an additional thrust impulse during the combustion of the powder checkers 11 of section 10 with its subsequent inertial movement along the ballistic

trajectories during the active generation of gaseous combustion products of the pyrotechnic block 12 (moderator), when the rocket enters the cloud being processed at a minimum angle to the horizon.

The missile of the proposed design develops a maximum speed less than the prototype missile, but the trajectory of movement directly inside the treated cloud is noticeably increased, where the active smoke dispersion time is longer, which inevitably increases the productivity of active precipitation initiation.

The heat plume formed during the combustion of the amplification charge 13 of the second section 10 ignites the channel block 8, during combustion of which an aerosol is generated, which includes an ice-forming reagent in the form of active crystallization nuclei causing precipitation in supercooled clouds.

The generated aerosol enters the collector 5, where through the channels 17 and the radial holes 18 of the fairing 6 is released into the atmosphere, directly into the cloud.

The generated aerosol also enters the atmosphere through the volume of the rocket that is free by that time and the nozzle block 14. During movement along the rocket of the active smoke generated by burning the checker 8, condensation and coagulation of solid particles occurs with the formation of a functional aerosol containing larger particles than those dispersed directly through exit vents 18 fairing. This ensures the distribution in the treated cloud of a balanced number of drop formation centers of different dispersion, as a result of which more prolonged precipitation is more likely to occur, preventing hail formation.

At the same time, the heat pulse from the amplifier 13 of the second section 10 is focused by a coaxial inductor 19 and ignites the pyrotechnic moderator 20 of the rocket self-destruction system, the burning time of which is noticeably longer than the time of active smoke generation by the burst 8.

After a predetermined delay time from the heat pulse of the moderator 20, the beam detonator 21 is triggered, the detonation wave from which triggers the explosive belt charges 22, 23 and 24. When the belt explosive charges distributed on the body are detonated, the rocket is destroyed, respectively, lengthwise and crosswise to the safe parts, without the formation of damaging fragments dangerous to the population and animals of the area affected by the clouds.

The proposed design improvements to the rocket developed technical documentation for the manufacture of prototypes that were tested at the test site. The results of field tests actually confirmed the achievement of higher characteristics of the destination, obtained by calculation using the mathematical model of the design of the experiment.

A comparative analysis of the proposed technical

solutions with identified analogues of the prior art, from which the utility model does not explicitly follow for a rocket specialist, showed that it is not known, and taking into account the possibility of industrial production, it can be concluded that the patentability criteria are met.

Claims (1)

A rocket for influencing clouds, containing a head part with a bomb of active smoke, covered by a cowl equipped with a smoke exhaust manifold and an actuator for self-liquidation, a solid propellant jet engine made of two successive sections, each of which includes a channel powder bomb, pyrotechnic bomb and an amplifying charge, as well as a nozzle block with aerodynamic blades and a central electrocapsule sleeve, characterized in that the pyrotechnic checkers of each reactant section the primary engine is made in the form of a moderator, the burning time of which is several times longer than the burning time of powder bombs in a ratio of 4: 1.