Warhead initiation device

Abstract

FIELD: military technology.SUBSTANCE: device for initiating the warhead contains an electrical harness with a contact unit connected to the body, a threaded cover, a main detonator, an initiating mechanism consisting of a striker, a rod, a pyrotechnic press, installed in a sleeve placed in a cylindrical sleeve divided into a cocking chamber and a pyrotechnic block chamber, in which electric igniters are located and in the pyrotechnic block chamber an expelling charge is located, a plate placed in the cylindrical sleeve, an inertial mechanism with an intermediate detonator, a spring-loaded sting, a safety rod and a cocking indicator. The safety rod consists of a limiter, made perpendicular to the spring-loaded sting, and a tip with a cavity, the movement of which is ensured by a pin through a calibrated hole in the insulating gasket. The ratio of the tip cavity diameter to the diameter of the calibrated hole of the insulating gasket is from 0.6 to 0.7.EFFECT: increase in the safety of using warheads intended for unmanned aerial vehicles and low-altitude aircraft.3 cl, 2 dwg

Description

[0001] Technical field

[0002] The invention relates to military equipment devices for initiating (deploying) a warhead. It is preferably used with mini and small-sized aircraft, such as unmanned aerial vehicles (UAVs) and low-altitude aircraft equipped with an electrical power source and a command device.

[0003] Technology Level

[0004] A known detonator (patent RU 2780636, F42C 11 / 00, priority dated September 28, 2022) comprises a housing, an electrical harness with a contact unit, a segmented metal arming block containing an electric arming igniter, a segmented electrical insulating block including a arming filter, an inertial mechanism with a detonator, a composite reaction mechanism consisting of a striker, a pressure nut, a rod and a pin, an arming indicator, and a mechanical safety device moved by a screw cap. The arming process begins with the application of a DC pulse from the UAV command device. The current passes through the contact unit and the electrical harness, then through the inductance of the arming filter, which activates the electric arming igniter and switches the device to the combat position. The device is triggered on the trajectory when the electrical pulse activates the command electric igniter. Its activation initiates the ejection charge, which pushes the piston rod out.The piston moves, displacing the central part of the partition and activating the stunner within the inertial mechanism. A disadvantage of this technical solution is the multi-layered architecture and the presence of various components, which increase the risk of mechanical failure or improper assembly. Furthermore, the L-shaped transport safety catch, secured with a screw cap, can become a weak point if the screw cap becomes loose or damaged, leading to unintentional activation of the device. Other disadvantages include the presence of a mechanical safety catch, whose movement by the screw cap increases the difficulty of manipulation and does not ensure complete sealing of the fuse when attaching a munition equipped with a fuse to unmanned aerial vehicles (UAVs) and low-altitude aircraft.

[0005] Also known is a detonator (patent RU 2592934, F42C 14 / 06, F42C 15 / 24, F42C 15 / 40, F42C 15 / 31, F42C 19 / 08, F42B 3 / 10, F42C 1 / 02 priority from the retarder, united by a common sealed cavity, an electric filter, a composite reaction striker made in the form of a rod, a striker and a pressure nut, an inertial striker with a spring-loaded detonator capsule and a transfer detonator, a spring-loaded striker, a sleeve with a pyrotechnic composition, a side-striker sleeve, a detonator and an electrical harness with a contact unit. When an aerial bomb is dropped, an electrical impulse from the aircraft mechanism activates the electric igniter. This process causes the formation of gases that The delay element is ignited, providing the necessary time for the other components to function properly. Gases from the electric igniter fill the sealed chamber of the cocking block, initiating combustion of the delay element, which in turn ignites the pyrotechnic composition.The spring-loaded pin then moves, preparing the blasting cap for firing. When the pin strikes the blasting cap, detonation occurs, which initiates the firing of the transfer detonator. This leads to the detonation of the main detonator, causing an explosion. A disadvantage of this technical solution is the mechanical safety device; under difficult and unusual conditions (for example, strong impacts or vibrations), there is a risk of unintentional detonation of the fuse. Furthermore, the fuse is not sealed when it is reset to the firing position, which can lead to improper operation of the delay device or the electric igniter, leading to failure of the fuse.

[0006] Disclosure of invention

[0007] The task, which the claimed technical solution of the initiation device (ID) is aimed at solving, is to increase the safety of the use of warheads intended for unmanned aerial vehicles (UAVs) and low-altitude aircraft.

[0008] This problem is solved by placing a safety rod in the fuse body, which is a limiter and a tip with a cavity passing through the fuse body, as well as an insulating gasket and an arming indicator containing a bursting membrane.

[0009] This technical solution is characterized by a housing divided by a partition into a cocking chamber and a pyrotechnic block chamber. The cocking chamber also contains an electric igniter, housed within a sleeve with an opening. The pyrotechnic block chamber houses the electric igniter and the propellant (pyrotechnic) charge, connected by channels. The housing contains an opening in which a freely movable safety rod is mounted. This rod consists of a stop and a hollow tip, the movement of which is ensured by a pin through a calibrated hole in an insulating gasket. Furthermore, the stop is perpendicular to the spring-loaded tip, and when the safety rod moves, the stop, which is configured to the diameter of the housing, will rest against the housing.

[0010] In addition, the housing is equipped with a cocking indicator containing a rupture disc. The ratio of the diameter of the safety rod cavity to the diameter of the calibrated hole in the insulating gasket is 0.6 to 0.7, ensuring complete sealing of the initiating device, both during service and when switched to the combat position.

[0011] Premature activation is prevented and operational safety is enhanced by a safety rod consisting of a stopper positioned perpendicular to the spring-loaded tip and a hollow tip. This indicator monitors the presence or absence of the initiator's arming, both before installation in the warhead and during preparation for use. Furthermore, the pyrotechnic seal in the housing, which activates the initiator, activates only after the "activate" command is issued, eliminating the possibility of the initiator being armed by mechanical factors (vibration, fall).

[0012] To prevent abnormal operation of electric igniters when interference and transient processes occur in the electrical harness circuits, electrical filters can be installed between the electrical harness and the electric igniters of the cocking chamber and the pyrotechnic unit.

[0013] To eliminate contact with the device and enhance operational safety, a coaxial threaded hole can be made in the threaded cap, striker, and piston rod, into which a locking screw is installed. When not removed, the screw provides additional operational safety by preventing the device from being triggered by mechanical impacts, even in the event of an abnormal activation of the pyrotechnic press.

[0014] The result achieved by the given set of features is an increase in the safety of using warheads intended for unmanned aerial vehicles (UAVs) and low-altitude aircraft.

[0015] Brief description of drawings

[0016] The essence of the proposed technical solutions is explained by drawings, where:

[0017] Fig. 1 - design of the initiation device in longitudinal section;

[0018] Fig. 2 - cross-sectional view of the initiating device.

[0019] Implementation of the invention

[0020] The warhead initiation device consists of an electrical harness with a contact unit 1 of a housing 2 into which a threaded cover 3 and the main detonator 4 are installed. The housing contains an initiating mechanism consisting of a striker 5, a rod 6 installed in a sleeve 7 and resting on a pyrotechnic pressing 8, the sleeve 7 in turn enters a cylindrical sleeve 9. The cylindrical sleeve 9 is divided by a partition into a cocking chamber 10 and a pyrotechnic block chamber 11, each of which contains an electric igniter 12, in addition, an expelling charge 13 is located in the pyrotechnic block chamber, and a plate 14 is also located in the sleeve 9. In addition to the initiating device, an inertial mechanism with an intermediate detonator 15, a spring-loaded sting 16, a safety rod 17, consisting of limiter 18, tip 19 with a cavity and check 20, a cocking indicator 21 is installed in the housing, consisting of a bursting membrane and an insulating gasket 22.

[0021] The product is transferred to the combat position by mechanically moving the pin 20, connected to the safety rod 17, consisting of a limiter 18 and a tip 19 with a cavity towards the cocking indicator 21 until it stops against the wall of the housing 2.

[0022] The initiation device is armed by supplying a direct current pulse from the UAV command device, which passes through the electrical harness with the contact unit 1 and activates the electric igniter 12, located inside the arming chamber 10. Under the action of the pressure and temperature of the powder gases from the activated electric igniter 12, the pyrotechnical press 8, located in the sleeve 7, which is located in the cylindrical sleeve 9, is ignited. When the pyrotechnical press 8 burns out, the sleeve 7 with the rod 6 placed in it rises under the action of the elastic force of the spring-loaded sting 16, ensuring the transfer of the initiation device to the combat position.

[0023] Triggering on the trajectory is carried out when an electrical impulse is supplied from the command device to the contact unit through the electrical harness 1 and activates the electric igniter 12, located in the chamber of the pyrotechnic unit 11. The activation of the electric igniter 12 initiates the expelling charge 13, located in the plate 14. The plate 14 hits the spring-loaded sting 16, which activates the inertial mechanism with the intermediate detonator 15.

[0024] The contact reaction action is ensured by the movement under the action of the forces of resistance of the obstacle and the impact of the striker 5, which, through the rod 6, located in the sleeve 7, acts on the spring-loaded sting 16, which activates the inertial mechanism with the intermediate detonator 15, and that in turn activates the main detonator 4.

[0025] The contact-inertial action at small approach angles is ensured by the movement of the striker 5 under the action of inertial forces along the conical surface of the threaded cover 3 towards the rod 6, followed by the movement of the spring-loaded sting 16, which activates the inertial mechanism with the intermediate detonator 15, which in turn activates the main detonator 4.

[0026] Safety in service handling is ensured by the presence of a safety rod 17, consisting of a limiter 18 and a tip 19 with a cavity, the movement of which is ensured by a pin 20 through a calibrated hole in an insulating gasket 22, thereby ensuring the sealing of the internal volume of the housing 2 with a ratio of the cavity of the safety rod to the diameter of the calibrated hole of the insulating gasket from 0.6 to 0.7.

[0027] Furthermore, limiter 18 is designed perpendicular to spring-loaded sting 16, and when safety rod 17 is moved, limiter 18, which is configured along the housing diameter, will rest against the housing. Furthermore, arming indicator 21 monitors the absence or presence of the UI arming, both before installation in the warhead and during preparation for use from unmanned aerial vehicles (UAVs) and low-altitude aircraft equipped with an electrical power source and a command device.

[0028] To prevent abnormal operation of electric igniters when interference and transient processes occur in the electrical harness circuits, electrical filters can be installed between the electrical harness and the electric igniters of the cocking chamber and the pyrotechnic unit.

[0029] To eliminate contact with the device and enhance operational safety, a coaxial threaded hole can be made in the threaded cap, striker, and piston rod, into which a locking screw is installed. When not removed, the screw provides additional operational safety by preventing the device from being triggered by mechanical impacts, even in the event of an abnormal activation of the pyrotechnic press.

[0030] Prototypes were manufactured in accordance with the invention formula and experimental tests were carried out, confirming the feasibility of implementing the claimed invention.

Claims

1. A device for initiating a warhead, characterized in that it contains an electrical harness with a contact unit connected to the housing, a threaded cover, a main detonator, an initiating mechanism consisting of a striker, a rod, a pyrotechnic press, installed in a sleeve placed in a cylindrical sleeve divided into a cocking chamber and a pyrotechnic block chamber in which electric igniters are located and in the pyrotechnic block chamber an expelling charge is located, a plate placed in a cylindrical sleeve, an inertial mechanism with an intermediate detonator, a spring-loaded sting, a safety rod and a cocking indicator, characterized in that the safety rod consists of a limiter made perpendicular to the spring-loaded sting, and a tip with a cavity, the movement of which is ensured by a pin through a calibrated hole in an insulating gasket,the ratio of the diameter of the tip cavity to the diameter of the calibrated hole of the insulating gasket is from 0.6 to 0.

7.

2. The device according to paragraph 1, characterized in that the electric igniters of the cocking chamber and the pyrotechnic unit are connected to the electrical harness by means of an electrical filter.

3. The device according to paragraph 1, characterized in that a coaxial threaded hole is made in the threaded cover, striker and rod, into which a fixing screw is installed.

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