BG4259U1 - Anti-hail rocket - Google Patents

Abstract

This utility model relates to an anti-hail rocket which will find application in the field of agriculture for the prevention of adverse weather processes, and for the protection of agricultural crops from damage and losses. The designed anti-hail rocket comprises reactant cartridges (3 and 5) mounted in the body (2) of the rocket and four self-destruct units implemented in a fairing (14), a engine bottom end kit (7), a self-destroying fuze (10) and a nozzle unit (13). The new fourth self-destruct unit is implemented by the self-destroying fuze (10), which is composed of a casing (33) and a cap (29) on which an ignitable coating (30) is applied, triggering a pyro timer - delay (31), at the end of which a sealant (32) and a primer cap (17) are mounted, as well as a detonating cord (21) is mounted in the casing (33).

Description

The current utility model relates to an anti-hail missile that will find application in the field of agriculture to prevent adverse atmospheric processes, as well as to protect agricultural crops from damage and damage.

Prior art

From patent application BG 109564, published on 31.11.2007 with the name "Missile for influencing atmospheric processes" is a known anti-hail missile, which consists of an anti-hail head, a body, a starting mechanism, a nozzle block with chrome-nickel steel stabilizers, a block with rocket fuel, engine bottom, two electric lighters and container. A starting mechanism and a rubber transport plug are mounted on the bottom of the container. Stabilization is carried out by means of four pieces of wings, clamped to a ring mounted on the nozzle block, made of phenolic resins with glass fibers AG-4B. The nozzle houses part of the self-extinguishing system and part of the starting system, which consists of two electric lighters, an engine charge igniter, an ejector charge and an electric lighter cable. The electric igniters and the motor charge igniter are mounted in the bottom of the rocket. The self-destruction system consists of three pairs of capsule detonators mounted in the bottom of the engine and in the head of the rocket, respectively. The engine block consists of a propellant block that is monolithically fabricated with a central hole for attachment to the bottom of the engine.

The known missile for impact on atmospheric processes provides only three self-destructions, which affects both the fragmentation of the rocket into pieces and the reliability of self-destruction.

Technical nature of the utility model

The task of the utility model is to create an anti-hail missile, which is a modernized design with a single electric lighter, which design provides four self-destructs, guaranteeing harmless sizes of debris falling to the ground.

The task was solved by creating an anti-hail missile, including an anti-hail head, which is a cone-shaped fairing filled with a balancing mass, to which a capsule carrier is glued, in the openings of which two capsule detonators connected by fuse are placed. The fairing is immovably attached to the rocket body, in which three sequentially located reagent presses are installed, between which rings with holes are established. After the third reagent press and engine bottom assembly, a segment was placed, with the engine bottom mounted by a threaded sleeve to a fuel block. A bushing is located between the fuel block and the nozzle block. The rocket is located in a container closed on both sides with a lid and a bottom. A jack is installed on the bottom, protected by a shipping plug, and the bottom is clamped to the container by a segment. The nozzle block consists of a nozzle on which four wings are mounted, clamped to another ring, on which an ignition putty is applied. A delay and capsule detonator are installed in the nozzle block, and an O-ring and detonating cord are installed in the nozzle grooves.

The engine bottom assembly consists of a bottom with a retarder bracket mounted at one end, another O-ring and a detonating cord inserted into corresponding holes in the bottom. Two holes are made in the bottom, in which capsule detonators are installed.

According to the utility model, a cup set and an electric lighter are mounted on the other end of the bottom. The fuel block is divided into two parts, each of which is a fuel mixture protected by polyvinyl chloride armor. Between the two parts of the fuel block there is a self-liquidator consisting of a housing and a cap. An incendiary putty is applied to the cap, actuating a pyrotimer delayer, at the end of which a seal and capsule detonator are mounted. A detonating cord is also installed in the housing.

The wings of the nozzle block are preferably made of glass-reinforced polyamide - PAS30.

An advantage of the created anti-hail missile is its modernized and modernized design, which provides the possibility of four self-destructions, thus resulting debris falling to the ground has a minimum mass of about 200 g.

Explanation of the attached figures

The present utility model is illustrated in the attached figures, where:

Figure 1 is a half-sectional view of an anti-hail missile according to the utility model;

Figure 2 is a section of a fairing;

Figure 3 is a half sectional view of the bottom of the engine;

Figure 4 is a cross-section of an assembled self-destructor located between the two parts of the fuel block;

Figure 5 is a cross-section of the self-destructor;

Figure 6 is a half-sectional view of the nozzle block; and

Figure 7 is a section of the anti-hail missile container.

Examples of implementation of the utility model

The created anti-hail missile shown in figure 1 includes an anti-hail head 1 immovably attached to a body 2, in which three reagent presses 3 and 5 are successively installed, between which rings with holes 4 and 6 are established, as after the third reagent press 5 and engine bottom assembly 7 is placed segment 8, the engine bottom 7 is mounted by threaded sleeve 26 to fuel block 9 and 11, connected by sleeve 12 to nozzle block 13.

The fairing assembly shown in figure 2 is a fairing 14 of conical shape, filled with a balancing mass 15, to which a capsule carrier 16 is glued, in the openings of which two capsule detonators 17 filled with gunpowder are placed, connected by fuse 18.

The engine bottom assembly 7, shown in figure 3, is composed of a bottom 23, at one end of which is mounted a support 19 of a retarder 20, and in corresponding holes in the bottom 23 another O-ring 22 and a detonating cord 21 are placed. the bottom 23 is also made with two holes in which capsule detonators 17 are mounted. At the other end of the bottom 23, a cup set 24 and an electric lighter 25 are mounted.

The fuel block is divided into two parts 9 and 11, each of which represents a fuel mixture 27 protected by a polyvinyl chloride armor 28. Between the two parts 9 and 11 of the fuel block is located a self-liquidator 10, shown in figure 5, consisting of a housing 33 and a cap 29, on which an ignition putty 30 is applied, triggering a pyrotimer-delay 31, at the end of which a sealant 32 and a detonator capsule 17 are mounted. A detonating cord 21 is also mounted in the housing 33. The assembled two parts 9 and 11 of the fuel block with the positions between these self-liquidators 10 are shown in figure 4.

The nozzle block 13, shown in figure 6, is composed of a nozzle 34, on which are mounted four pieces of wings 39, clamped to another ring 40, on which an ignition putty 30 is applied, and in the nozzle block 13 are established a delay 41 and a capsule detonator 38, and an O-ring 35 and a detonating cord 21 are installed in the channels of the nozzle. The wings 39 are made of glass-reinforced polyamide - PAS30. In the nozzle block 13, the body 36 and the screw 37 of the starter stopper are also established. The nozzle block 13 is attached to the body by means of a segment 8.

The missile is located in a container 43, shown in figure 7, which is closed on both sides by a cover 42 and by a bottom 47, on which a jack is installed, protected by a transport plug 48, the bottom 47 being clamped to the container 43 by a segment 8. Container 43, in addition to storing the rocket during transportation, is also used for the launch itself.

The anti-hail missile is used in the following way.

The missile is placed in a launcher and fired using an ignition device. The ignition device activates the electric igniter 25 by means of an electrical impulse, which ignites the parts 9 and 11 of the fuel block. The flame from the fuel block, passing through the critical section of the nozzle block 13, where the launch stopper is installed, generates thrust and the created pressure pushes the rocket out of the container 43. Upon exiting the container 43, the folded wings 39 of the rocket open, and the rocket continues to fly in the desired direction with rotation providing better accuracy. The burning process lasts about 4.0 ± 1.0 s to accelerate the rocket, the flame in the fuel unit 9 and 11 activates the pyrotimer - delay 31, which after some time activates the reagent composition prepared on the basis of silver iodide, which composition is divided into three reagent presses 3 and 5, between which are located the rings with holes 4 and 6, through which the combustion products of the reagent presses 3 and 5 exit. The reagent presses 3 and 5 burn within 30 - 33 s, after which the flame from their combustion activates the capsule detonators 17, located respectively in the engine bottom assembly 7 and in the fairing 14. With the explosion, the fairing 14 is destroyed, and with the explosion in the engine bottom assembly 7, the central part of the rocket is destroyed and the part with the reagent is separated composition. After a certain time, the nozzle block 13 and the self-destructor 10 activate the capsule detonators 38 and 17 placed in them, during which the rocket disintegrates into harmless debris with a minimum mass of about 200 g.

Claims (1)

An anti-hail missile, including an anti-hail head (1), representing a cone-shaped fairing (14) filled with a balancing mass (15), to which a capsule carrier (16) is glued, in the openings of which two capsule detonators (17) are placed, connected to fuse (18), the fairing (14) being immovably fixed to the body (2) of the rocket, in which three successively located reagent presses (3 and 5) are mounted, between which rings with holes (4 and 6) are established, as after the third reagent press (5) and engine bottom assembly (7) a segment (8) is placed, the engine bottom (7) is mounted by a threaded bushing (26) to a fuel block separated by a bushing (12) from the nozzle block (13), mounted in the body (2), which is located in a container (43), closed on both sides with a cover (42) and with a bottom (47), on which a jack is installed, protected by a transport plug (48), wherein the bottom (47) is attached to the container (43) by a segment (8), wherein the nozzle block (13) is composed of a nozzle (34) , on which four pieces of wings (39) are mounted, clamped to another ring (40), on which ignition putty (30) is applied, and in the nozzle block (13) a delay (41) and a capsule detonator (38) are established, and an O-ring (35) and a detonating cord (21) are mounted in nozzle grooves (34), and the engine bottom assembly (7) consists of a bottom (23) with a carrier (19) mounted at one end of a delay (20), and another O-ring (22) and a detonating cord (21) are placed in corresponding holes on the bottom (23), and two holes are made in the bottom (23) in which capsule detonators are installed ( 17), characterized in that a set cup (24) and an electric lighter (25) are mounted at the other end of the bottom (23), whereby the fuel block is divided into two parts (9 and 11), each of which represents fuel mixture (27), protected by polyvinyl chloride armor (28), and between the two parts (9 and 11) of the fuel block there is a self-liquidator (10), consisting of a body (33) and a cap (29), on which an incendiary putty (30) is applied, triggering a pyrotimer-delay (31), at the end of which a sealant (32) and a capsule detonator (17) are mounted, and a detonating cord (21) is mounted in the housing (33)