RU2456537C2 - Firing mechanism for shells of multiple artillery rocket systems - Google Patents

Abstract

FIELD: blasting operations.

SUBSTANCE: firing mechanism includes installation device, reaction percussion mechanism, safety and arming unit and ignition train. The latter is branched and made in the form of independent parts - ignition part which contains detonating cartridge with intensifying charge, sleeve-type igniter capsule with striker, bursting charge and electric spark igniter, and detonation part containing detonator, lead charges, ignition cap, and explosive electric igniter. The first lead charge and bursting charge are arranged in turning disc of safety and arming unit. Detonating cartridge with intensifying charge and detonator made in the form of a ring and arranged around detonating cartridge are installed coaxially in firing mechanism sleeve. Installation device includes receiving circuit on the basis of inductive communication line, electronic temporary device the output of which is connected to electric igniter of firing part of ignition train. Turning disc of safety and arming unit of firing mechanism is retained in uncocked position with a clock mechanism and spring-loaded action bar kinematically connected to the disc.

EFFECT: higher safety and reliability and improved control possibilities.

4 cl, 2 dwg

Description

The invention relates to military equipment, in particular to fuses for shells of multiple launch rocket systems (MLRS).

The creation of fuses for modern and promising MLRS shells with high accuracy and accuracy of fire, high safety, the ability to automate control during prelaunch preparation, and also perform tasks of controlling motion and correcting flight paths at a relatively low cost is an urgent complex scientific and technical problem. One of the technical solutions that provide the requirements for accuracy and efficiency of fragmentation of manpower is the use of rockets with detachable and parachuting the warhead with a multifunction remote contact fuse.

Known electronic remote fuse with a remote installation, having three outputs of the fire chain, described in US patent No. 5.147.975, published September 15, 1992 (IPC F42C 15/40). This device is designed for reactive systems and is used to neutralize mines by detonating an aerosol mixture delivered by a projectile to the minefield area and consists of an electronic device that allows three independent fire chain outputs to be initiated, the first fire chain output being used to open the parachute and remove the protective shell of the fuse probe, while simultaneously starting a mechanical temporary device that slows down the deployment of a 1.8-meter probe. The second output of the fire chain is initiated when the probe contacts the barrier (for the purpose) and leads to the explosive pushing out of the outside two aerosol detonators, including safety cocking devices located on the rear of the warhead housing. The third output of the fire chain is initiated by an electronic temporary device, launched by touching the probe of the obstacle, and leads to the initiation of a explosive charge of the warhead after removing the explosive detonators of the aerosol at a safe distance, excluding their detonation when the warhead is triggered. Under the action of an impulse charge pulse, the fuel in the canister breaks the canister and, mixed with the surrounding air, forms a fuel-air aerosol cloud, which is then blown up by two detonators thrown away.

Closest to the proposed fuse for shells to multiple launch rocket systems is the existing for such systems head fuse MRV-U (Fuse MRV-U. Service manual. Military Ministry of Defense of the USSR, Moscow: 1973, 8 pp.). This is a contact fuse with an initiation system in the form of a reaction strike mechanism, an installation device for three decelerations and with a semi-fuse type fire chain. The safety-cocking device of this fuse is made on the basis of an inertial mechanism with a zigzag movement of the settling sleeve, the retained part of which (the reaction mechanism hammer), in turn, holds the spring-loaded engine with the igniter capsule, the axis of which is offset from the fire channel of the installation device, the channel being blocked by the obturator cup . The installation device is made on the basis of a slewing crane and has three positions - fragmentation effect, low deceleration and high deceleration). The safety-cocking mechanism used in this fuse on the basis of the “zig” does not fundamentally provide the necessary safety of the fuse in case it falls separately or together with the projectile in official use on a rigid base. The height of the safe fall of such mechanisms does not exceed 2 ... 5 meters. In addition, in order to increase safety, it is preferable to use safety-type devices in fuses with insulation of detonator capsules, rather than igniter caps, as is customary in the prototype. It should also be borne in mind that with the current trend of increasing the firing range of MLRS and, consequently, a steady trajectory of a missile’s flight, the effectiveness of fragmentation damage to the target with shells equipped with fuses like MRV-U will be insufficient.

The objective of this technical solution is to create a fuse for modern and promising MLRS shells with high accuracy and accuracy of fire, the necessary safety, the ability to automate control during prelaunch preparation, and also perform tasks of controlling the movement and correcting the flight path at a relatively low cost, in particular, with the possibility of its use in rockets with detachable and parachuting the warhead.

The reasons that impede the achievement of the technical result indicated below when using a well-known fuse adopted for the prototype include the lack of devices in the MRV-U fuse that provide the ability to automate control during prelaunch preparation, that is, automatically set the time for remote action on the trajectory (time of separation of the missile head and disclosure of the parachute) and the type of action of the warhead of the projectile at the target (fragmentation or high-explosive), insufficient prototype security in the service SG circulation due design features slam-cocking mechanism of the fuse, and also the absence of inertial impactor, performing the role of a mechanism, the backup operation reactionary impact mechanism when installing the fuse for fragmentation effect and the major role in installing the fuse to explosive action.

Common features of the invention with a device selected as a prototype is the designation of fuses for shells for multiple launch rocket systems with two settings for high-explosive and high-explosive actions, the presence of an initiation system as part of the reaction strike mechanism, installation device, safety cocking device and fire chain .

The essence of the claimed invention lies in the fact that the fuse circuit of the fuse is made in the form of two independent parts - igniter and detonation, with corresponding output firecrackers with an amplifying charge and a detonator, which are structurally mounted coaxially in one terminal sleeve of the fuse, and the firecracker and amplifying charge are located on the axis bushings (along the axis of the fuse), and the detonator is made in an annular form, ensuring the transmission of the initiating impulse to the warhead; the igniter part contains an electric igniter, a knockout charge, a sleeve igniter capsule, and the detonation part contains an electric igniter, a detonator capsule, a transfer charge and an additional transfer charge; the safety-cocking device is made on the basis of a rotary disk with a transfer charge of the detonation part and an expulsion charge of the ignition part of the fire chain, which are isolated from each other and isolated from the remaining elements of the fire chain, the disk being held in an unbroken position by a clockwork mechanism and a spring-loaded inertial slider, kinematically connected with the disk using a roller entering the groove of the disk, in addition, the disk has an additional groove on the side surface, providing conductive after the active portion of path driving connection with drive roller and the slider and the disk dovorot the cocked position after the end of the active portion of path as a result of lifting of the slide and the roller under the action of the slider spring; installation device, including a receiving circuit based on an inductive communication line, a power source and an electronic temporary device, to the output of which an electric igniter of the igniter part of the fire circuit is connected. In addition, a pyrotechnic contactor equipped with a pyrocontact composition is included in the electric circuit connecting the igniter of the igniter part of the fire circuit and the reaction mechanism, after which the electronic time device and the subsequent combustion of the pyrocontact composition for 2 ... 3 seconds are connected, the target sensor is electrically connected the reaction of the shock mechanism to the military electric igniter of the detonation part of the fuse circuit of the fuse, in the final volt lke taken fuse device comprising hemispherically shaped striker, based on nondestructive surface of the sleeve with the sleeve ignition fuse igniting portion, the firing circuit fuse. The fuse also differs in that the fuse initiation system further includes an inertial percussion mechanism, consisting of a stinger, a spring, a striker with a firing igniter capsule, a pyrotechnic moderator and a knockout charge, the knockout communicating with a fire channel connecting the electric igniter of the reaction knocker with the detonator.

The fuse is a monoblock, in the housing of which all devices and mechanisms are placed in bushings interconnected by threads and screws. The tightness of the product is ensured by gaskets.

The technical result achieved during the implementation of the invention is expressed in the creation of a class of multifunctional fuses for modern and promising MLRS shells with high accuracy and accuracy of fire, high safety, the ability to automate control during prelaunch training, and also perform tasks of controlling movement and correcting flight paths at relatively low cost.

The technical result is ensured by the use of rockets, which, when installing the fuse for fragmentation, at his command, detaches on the trajectory at a set point in time and parachutes the warhead, which ensures approach to the target of the warhead at angles close to normal and the greatest effect fragmentation field.

The device of the proposed technical solution is illustrated by drawings:

figure 1 - fuse for shells of multiple launch rocket systems;

figure 2 - fuse for shells MLRS (reflected safety cocking device, the second view and section BB).

The fuse is made in a sealed enclosure formed by a threaded connection of several metal and plastic case parts, and it includes an initiation system in the form of a reaction and inertial shock mechanisms, a capacitor power supply, and an installation device in the form of a receiving circuit based on an inductive communication line with an electronic temporary device, safety-cocking device based on a rotary sleeve with "hourly braking" and a branched fire chain made as two independent parts - and igniting detonation.

The installation device 1 (Fig. 1) provides, through the inductive channel of the product, charging the capacitor power source, receiving from the equipment of the remote installation, located on the combat vehicle, the required value of the remote action time of the electronic temporary device 2, designed to form a command to separate the warhead from missile parts. Structurally named elements are made in the form of separate blocks.

The fuse initiation system is composed of reactionary 3 and inertial (not shown) shock mechanisms designed to actuate the fuse when the projectile encounters an obstacle. Moreover, the reaction action of the fuse is provided when the fuse is mounted on a fragmentation effect and is associated with the separation of the head of the rocket from the missile part, in connection with which a capacitor power source, electronic temporary device 2, the igniter part of the fuse circuit of the fuse, and the reaction shock mechanism 3 are used pyrotechnic contactor 4, equipped with a pyrocontact and retarding composition, which, after working out the time, provides an electronic temporary device 2 electrically f connecting the reaction sensor of target 3 to the military electric igniter 11 after a while (2-3 s)

The safety-cocking device of the fuse (figure 1 and figure 2) is designed to exclude the operation of the fuse until the end of cocking. This device includes a rotary disk 6 with a transfer charge 7 of the detonation part located therein and a knockout charge 8 of the ignition part of the fuse of the fuse, and the axis of the transfer charge 7 is parallel to the axis of rotation of the disk, and the axis of the knockout charge 8 is perpendicular to the axis of rotation of the disk and both charges are located on the periphery the disk in such a way that the transfer charge 7 is not triggered when the expelling charge 8 is triggered. In addition, the disk 6 in the initial position is rotated relative to the cocked position, equal to 55 ... 60 °, which provides a shift to a safe distance of these charges (7 and 8) from the previous (electric igniter 5 and detonator capsule 9 and subsequent (sleeve igniter capsule 10 and an additional transfer charge of 20 elements of the igniter and detonation parts of the fuse circuit of the fuse) The rotary disk 6 is held in its original position by a spring-loaded slider 12, which is connected to the disk by means of a roller 13 entering the groove of the disk. The disk also has an additional groove, designed to turn the disk into the cocked position after the end of the active section of the trajectory of a rocket. The rotary disk 6 is also connected by a gear sector with a clock mechanism 14 having a trigger regulator without restoring force. The shape, dimensions and center of mass of the rotary disk are selected in such a way that the axial inertia force acting on the disk in the active section of the flight path of the rocket projectile tends to rotate the disk in the cocked position.

The branched fuse chain of the fuse is made in two parts - igniter and detonation - with the corresponding output firecracker 15 and detonator 16, which are structurally mounted coaxially in one terminal sleeve of the fuse 17, and the firecracker 15 is located along the axis of the sleeve (along the axis of the fuse), and the detonator 16 made of a circular shape and placed in the annular groove of the terminal sleeve 17. In addition to the firecrackers 15, the igniter part of the fuse circuit includes an electric igniter 5 at the output of the electronic temporary device 2, above a charge 8, located in the rotary disk 6, and a sleeve igniter capsule 10. The detonation part of the fuse circuit includes an electric igniter 11, a detonator capsule 9, a transfer charge 7 located in the rotary disk 6, an additional transfer charge 20 and a detonator 16 The safety of the fuse in the fire chain until the moment of cocking is ensured by the fact that the transfer charge 7 and expelling charge 8 are isolated from the remaining elements of the fire chain (their spontaneous operation does not trigger the subsequent lementy firing circuits) due to the fact that they are located in the disk and are shifted with respect to other elements of the firing chain. In addition, the igniter capsule 10 in the bushing with a jumper protects the mechanisms and devices of the fuse from the effects of gases generated by the firecrackers and the charge of the separation device of the head of the rocket and the rocket.

The action of the fuse is as follows.

Before firing a rocket during fragmentation, electric commands are transmitted via an inductive communication line to the fuse receiver coil located in the fuse installation device 1. The output coil output voltage is converted into the stabilized voltage of the capacitor power source in the installation device and prepares the electronic temporary device 2.

When starting a missile at the beginning of the active section of the trajectory, the supply voltage is supplied to the input of the electronic temporary device 2 and the countdown of the set time of the remote action begins.

At the same time, under the action of axial acceleration in the safety-cocking device, the slider 12 settles, compressing the spring (not shown). The rotary disk 6, connected with the slider 12 by the roller 13, is also connected by the gear sector to the clock mechanism 14. At the end of the settling of the slider 12, the roller 13 disengages from the rotary disk 6.

At the end of the active section of the trajectory, the slider 12 rises under the action of the spring, and the roller 13, moving in another groove of the disk 6, turns the rotary disk into the combat position.

Cocking the fuse ends and he is ready for action.

After the set remote control time has elapsed, an electric igniter 5 is activated, which ignites the knockout charge 8 in the rotary disk 6 and the composition of the pyrotechnic closure 4. The knockout charge 8 in the disk triggers the igniter 10 - in the firing pin 18, it hits the sleeve capsule through the metal jumper igniter 10, firecrackers 15 with an amplifying charge 19 and generates an ignition pulse to the separation device of the head of the rocket.

After the pyrotechnic composition of the contactor 4 burns out, the electric circuit of the capacitor power source and the military electric igniter 11 are closed. When the head part meets the obstacle, the contacts in the reaction sensor 3 are closed under the action of the reaction forces of the obstacle, and the military electric igniter 11 is activated from the capacitor power source, which ignites the radiation detonator capsule 9, which drives the transfer charges 7 and 20, which initiate the detonator 16, which actuates the the explosive substance of the MLRS shell is exactly above the target.

High reliability and safety of this technical solution is confirmed by numerous laboratory and field tests.

Claims (4)

1. The fuse for shells of multiple launch rocket systems containing a mounting device, a reaction strike mechanism, a safety cocking device and a fire chain, characterized in that the fire chain is branched in the form of independent parts - igniter, containing a firecracker with an amplifying charge, a sleeve capsule - an ignitor with a striker, a knockout charge and an electric igniter, and a detonation one containing a detonator, transfer charges, a detonator capsule, a military electric igniter, the transfer charge and expelling charge are placed in the rotary disk of the safety cocking device, and the firecracker with an amplifying charge and made in the form of a ring and a detonator placed around the firecracker are installed coaxially in the fuse hub, the installation device includes a receiving circuit based on an inductive communication line, an electronic temporary device the output of which is connected to an electric igniter of the igniter of the fire circuit. 2. The fuse according to claim 1, characterized in that the rotary disk of the safety-cocking device is held in an unbroken position by a clockwork mechanism and a spring-loaded inertial slide kinematically connected to the disk having a groove by means of a roller, the disk also has an additional groove providing kinematic connection with a roller and a slider and turning the disk to the cocked position. 3. The fuse according to claim 1, characterized in that the firing pin of the plug igniter has a hemispherical shape and rests on a flat jumper separating the plug igniter from the hammer. 4. The fuse according to claim 1, characterized in that the pyrotechnic contactor, equipped with a pyrocontact and retardant composition, which delays the connection of the electric circuit of the reactionary strike mechanism to the military electric igniter after the operation of the electronic temporary device, is included in the electric circuit connecting the combat electric igniter and the reaction strike mechanism. .

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