RU2186334C1 - Contact fuse for anti-shipping missiles - Google Patents

Abstract

FIELD: military equipment. SUBSTANCE: in the contact fuse for anti-shipping missiles containing a system of contact pickups and a safety-actuator mechanism with a safety- type firing circuit, the system of contact pickups is made in the form of two groups, the first of which, the target contact pickups, is installed on the missile envelope, and the second one, the destruction pickups, - directly in the warhead. The safety-actuator mechanism has two reservoir capacitors, one of which is connected to the circuit of instantaneous action as a result of closing of the destruction pickups, and the second one - to the firing circuit of delayed action as a result of closing of the target contact pickups, two shock-proof contactors, for example blast relays, and a resistor shunting the reservoir capacitor at an emergency untimely closing of pickups. EFFECT: enhanced efficiency of the missile warhead. 3 dwg

Description

 The invention relates to the field of military equipment, in particular to contact explosive devices of anti-ship missiles. For such explosive devices, in addition to high requirements for reliability and safety, the main criterion is to ensure the optimal response time of the explosive device, at which the most efficient use of the warhead of the missile to hit the target is achieved.

 Due to the wide variety of sea targets in terms of size and reservation, as well as meeting conditions for the target (speeds and angles of approach to the target), a contact explosive device must provide selectivity of action. The greatest effectiveness in hitting a target is ensured by undermining the warhead of the rocket inside the target when a ship's hull is pierced with the required deceleration. However, when a missile encounters particularly strong target elements (for example, the joints of a ship’s frames), a case is possible in which the penetration of the ship will not be achieved. Then it is necessary to provide instant detonation of the warhead on the target’s contour in order to inflict at least some destruction.

 The task of providing undermining of the warhead of the rocket inside the target is solved relatively simply for the warhead of the penetrating missile by setting in the fuse the required time to slow down the undermining of the warhead of the rocket after breaking through the target.

 In the patent of Germany 1089304 describes an explosive device for cocking fuses of rockets by setting the desired response time using electrical signals. US Pat. No. 4,019,441 describes a safety-detonating mechanism for rockets containing a rotor with a clock engine, driven by a spring, and with an electric time setting. In the patents in question, fuses provide only one single time of detonation of the warhead, set when the missile is launched remotely from the firing control panel, and it cannot be changed.

 Known contact explosive devices that recognize the type of obstacle and distinguish between collisions with various objects. The device for detonating a guided missile (US Pat. No. 4,799,427) penetrating a target has an electronic deceleration device that is adjustable in accordance with the signals of the acceleration sensors. The threshold electrical circuit generates output signals that propagate depending on the amplitude of the signals of the acceleration sensors. The output signal of the acceleration sensor located in the projectile, which characterizes the change in acceleration in a collision with a target and thus allows you to find the differences between soft and hard targets, gets to the input of a threshold electric circuit. A threshold electrical device may have several threshold values. Further, the signals of the threshold device activate an electric deceleration time device having at least two deceleration intervals. The deceleration time to undermine the guided missile’s charge should be relatively short when it collides with a solid target, which the projectile may not penetrate. If the projectile hits a soft target, the slowdown time is longer. To account for the effect of rocket speed in a collision with a target, the device has an electrical measuring circuit.

 The device described in US Pat. No. 4,480,550 provides selective penetration retardation using two sensor belts to determine relative speed. The electrical signals of the relative velocity sensors are converted according to a given scheme, the electrical circuit of selective deceleration during penetration uses these signals to detonate the projectile.

 Closest to the claimed can be considered a contact device for missiles (US patent 4019440). In this device, contact sensors sensitive to shock waves are located along the longitudinal axis of the rocket closer to the bow of the rocket and are fed from pulse generators. The output circuits of all sensors are connected to a temporary pulse selector, in which the logical processing of signals of the "NAND" type is performed. In the case of a normal collision with a given obstacle when the sensors alternately engage the sensors on the conical shell of the rocket, the selector is activated provided that the duration of each subsequent signal from the sensor does not exceed the signal duration of the first sensor. In this case, the selector generates a signal for the operation of the safety-executive mechanism with a firing chain of the safety type and the detonation of the warhead of the rocket. If the signals from the sensors do not fit the duration of the signal of the first sensor, but exceed them, then the selector does not generate an output signal. A signal to detonate a rocket is formed only in the presence of overlapping impulses characteristic of a direct hit only.

 The objective of this technical solution was to create a contact explosive device with increased effectiveness of the warhead of the missile due to the selectivity of the action of the explosive device, depending on the type and characteristics of the target.

 The reasons that impede the achievement of the technical result indicated below when using the known device adopted for the prototype include the insufficient reliability of the explosive device detonating the warhead of the guided missile after it reaches the sea target and its penetration, due to the fact that it is impossible to place several belts in the head of the rocket contact sensors; at small angles of meeting the missile with the goal of sequential sequential triggering of the sensors will not be provided; to ensure the reliable operation of a temporary selector based on existing microelectronics for anti-ship missiles and a power source for circuits in conditions of enormous overload when penetrating targets in the armor is an almost impossible task.

 Common features with the invention in the prototype device is the presence of a system of contact sensors located in the rocket, and a safety-actuating mechanism with a firing chain of a safety type.

 The technical result achieved by the implementation of the invention is expressed in the creation of a new class of highly effective anti-ship missiles.

 The technical result of the recognition of the action of a contact explosive device is achieved by introducing into the electrical circuit of a contact explosive device a temporary selector constructed on the basis of shock-resistant explosive logic elements in combination with contact sensors of the target. As such elements, an electric detonator, an electric igniter, shockproof explosive relay are used. A temporary selector of the type of a logical element of the type “NOT-I” is created on the basis of a pyrotechnic moderator, the burning time of which does not exceed the time of destruction of the warhead. The purpose of the selector is to generate an output signal for blasting only if the destruction time of the warhead does not exceed the burning time of the pyrotechnic moderator. Only in this case, the selector will generate a signal to undermine the warhead.

 The essence of the claimed invention lies in the fact that in a contact explosive device for anti-ship missiles containing a system of contact sensors and a safety-actuating mechanism with a firing chain of a safety type, the system of contact sensors is made in the form of two groups, the first of which, contact sensors of the target, is mounted on rocket shell, and the second, destruction sensors, directly in the warhead, and the safety-executive mechanism contains two storage capacitors, one of which The second one is connected to the instantaneous circuit from the closure of the destruction sensors, and the second to the delayed-fire circuit from the closure of the contact sensors of the target, two shockproof contactors, for example, explosive relays and a resistor shunting the storage capacitor in the event of emergency premature closure of the sensors.

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

 Figure 1 shows the location of contact sensors on the head of the rocket and on its warhead and their connection with the safety-actuating mechanism.

 In FIG. 2 presents an electrical diagram of the proposed technical solution with elements of the fire chain.

 In FIG. Figure 3 shows a variant of the electrical circuit and the fire circuit using mechanical protection with a rotary sleeve.

 Figure 1 shows the placement of the contact explosive device in the head of the rocket 1, where the first group of contact sensors (target sensors) 2, connected by wire connection 3 with the safety-actuating mechanism 4, is installed on the shell of the rocket in front of the warhead of the rocket 5, and the second group contact sensors (contact sensors of destruction of the warhead) 6 is installed inside the warhead 5 and is also electrically connected to the safety-actuating mechanism 4.

 The electrical circuit of the proposed technical solution depicted in FIG. 2, consists of two circuits, the first of which ensures the engagement of the fire chain from the contact sensors of target 2, the second - the engagement of the fire chain from contact sensors of the destruction of the warhead 6.

 The first circuit includes a storage capacitor C1, in parallel to which resistor R1 is connected through the contacts of the contact sensors of the target 2, through the contact of the switch 7 is an electric igniter 8, through the contact of the explosive relay 9 is a double-action electric detonator 10.

 The second circuit includes a storage capacitor C2, in parallel with which a double-action electric detonator 10 is connected through the contacts of the destruction sensors 6 and through the contact of the explosive relay 11. Diodes D1 and D2 are included in the power circuit of the electric circuit.

 A pyrotechnic moderator 12 is installed between the electric igniter 8 and the double-acting electric detonator 10, which ensures the delayed action of the elements of the fire chain of the safety-executive mechanism of the contact explosive device: electric detonator 10, transfer charge 13 and detonator 15.

 An embodiment of the electrical circuit and the firing circuit using mechanical protection with a rotary sleeve shown in FIG. 3, comprises: a rocket launch unit 16, which is electrically connected to the starting electromagnet 17, an on-board power supply of the electrical circuit of the contact fuse device 18, a command firing control panel 19, a rotary sleeve 20 with a groove 21 and a spring 22.

 The circuit elements of FIG. 3 correspond to those shown in FIG. 2.

 At the time of launching rocket 1 from block 16, an electrical command is sent to the starting electromagnet 17. The electromagnetic mechanism releases the rotary sleeve 20, which, under the action of the spring 22, expands to the cocking position, while the contact of the microswitch 7 enters the groove 21 of the sleeve 20 and connects the combat electrical circuit. The safety-executive mechanism is cocked along the fire circuit, that is, the transfer charge 13 is aligned with the electric detonator 10 and detonator 15, and the electric igniter 8 is connected to the storage capacitor C1 along the electric circuit.

 On the flight of the rocket, the corresponding command for the corresponding relay 9 or 11 is received from the firing command control panel 19, depending on the target, and then at a certain distance to the target, a command is received from the on-board power supply of the electric circuit of the contact fuse device 18 to charge the storage capacitors C1 and C2. The safety-executive mechanism is ready for action. When encountering an obstacle, the contact sensors of target 2 are triggered. In this case, capacitor C1 is discharged through the contacts of the target 2 sensor, the contact of the microswitch 7 to the electric igniter 8. The ignition products of the electric igniter 8 cause combustion of the moderator 12, after which the electric detonator 10, the transfer charge 13 and the detonator fire 15. This ensures the delayed action of the fire chain and the detonation of the warhead inside the target.

 Upon receipt of a command from the firing control panel of the shooting 19 command to relay 9, upon impact with an obstacle, a signal is received from the contact sensors of target 2, which causes the detonator of the double action 10 to undermine the capacitor C1, the transfer charge 13, the detonator 15, providing instant undermining of the warhead of the rocket (without any slowdown).

 Upon receipt of a signal from the command panel of the firing control 19 to the relay 11, upon impact with an obstacle, the fire chain is triggered with deceleration, as in the first case. If, after a rocket penetrates the target’s sheathing, the rocket encounters a solid, impenetrable obstacle during its further movement, then the warhead is destroyed and the destruction sensors 6 are triggered, the electric detonator 10, the transfer charge 13, the detonator 15 are triggered and the warhead is instantly undermined. This ensures the selectivity of the action of the contact explosive device according to the type of target (strength and impact conditions).

 The technical result of the claimed invention is confirmed by the results of numerous field tests.

Claims (2)

 1. Contact explosive device for anti-ship missiles, containing a system of contact sensors, a safety-actuating mechanism with a firing chain of a safety type, an on-board power source, characterized in that the system of contact sensors is made in two groups, the first of which is contact target sensors - installed on the shell of the rocket, and the second - destruction sensors - in the warhead of the rocket, and the safety-actuating mechanism contains two storage capacitors that are charged from the onboard a power source, two shock-resistant contactors, the first capacitor connected to the instantaneous circuit via destruction sensors and the contacts of the first shock-resistant contactor, the second storage capacitor connected to the fire circuit through the contact sensors of the target and to the instantaneous circuit through contact sensors of the target and contacts of the second shockproof contactor.  2. The device according to p. 1, characterized in that the shockproof contactor is made in the form of an explosive relay.

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