RU2268457C1 - Contact explosive device - Google Patents

Abstract

FIELD: contact explosive devices for small-sized antiaircraft guided missiles.

SUBSTANCE: the device has a system of contact pick-ups, safety-actuating mechanism with a safety-type firing circuit, one of the contact pick-ups is made in the form of a pulse magnetoelectric oscillator of wave action, and the other - in the form of a wave impact contactor, both pick-ups are combined in a single casing, the safety-actuating mechanism is made in the form of a rotary bush with an electric detonator positioned inside the bush, and a contact group installed in the bush that is held by pyrotechnic and inertial locks.

EFFECT: enhanced reliability of operation of the explosive device and efficiency of combat use and providing of the necessary safety.

3 cl, 4 dwg

Description

The invention relates to military equipment, namely to contact explosive devices for small-sized anti-aircraft guided missiles, which are launched from launch tubes from trenches, from ships, from moving vehicles, etc.

Due to the peculiarity of launching small-sized anti-aircraft guided missiles, when the starting engine is first triggered, which ejects the rocket from the launch tube several meters, and then the main engine fires, there may be cases when the main engine fails and the rocket falls dangerously close to the gunner. The so-called “peck” of the rocket occurs. In this case, a guaranteed failure in the operation of the fuse should occur.

Due to the wide variety of modern air targets and the conditions for a missile to meet them (modern targets can be both low-strength drifting balloons, remotely piloted aircraft, and steel sheets protecting critical aircraft and helicopter assemblies), a contact explosive device must ensure reliable destruction in all collision cases.

Known explosive device for rockets according to patent DE 1089304 (IPC F 42 C 11/00, published September 15, 1960) by setting the required response time using electrical signals.

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 predetermined scheme, the electrical circuit of selective deceleration during penetration uses these signals to undermine the charge.

Known safety-detonating mechanism for rockets, described in US patent No. 4019441, IPC F 42 C 11/00, published 04/26/1977, containing a rotor with a clockwork engine, driven into rotation by a spring, and with a fire chain safety type. However, in the patent in question there is no connection between the cocking elements and the rocket movement, which does not provide the required safety.

Closest to the claimed can be considered a contact explosive device for missiles according to the patent of the Russian Federation No. 2186334 (IPC F 42 C 9/10, 11/00, F 42 B 15/00, published July 27, 2002), which contains a system of contact sensors, some of which are mounted on the shell of the rocket, and the second part is destruction sensors - in the warhead of the rocket, a safety-executive mechanism with a fire chain of a safety type, with a rotor driven in spring by movement. The cocking of the rotor occurs after it is released by an electromagnetic stop, which is electrically connected to the missile launch system. The known device contains only one stage of protection in the form of an electromagnetic stopper, and to bring it into action, an electric signal is required from the fire control system.

The objective of this technical solution is to create a contact explosive device with increased combat effectiveness due to the use of selective sensors depending on the type and characteristics of the target and increased security through the use of a safety-actuating mechanism with stoppers interconnected with the rocket launch system electrically and kinematically.

The reasons that impede the achievement of the technical result indicated below when using a known device adopted as a prototype include the insufficient reliability of the explosive device detonating a missile’s warhead after it reaches an air target and collides with it, because it is impossible to place the target’s contact sensors in the head missiles and that in the safety-executive mechanism there is no connection of cocking elements with the movement of the rocket, which does not provide the required safety.

Common features with the invention in the prototype device is the presence in the contact explosive device of a system of contact sensors and a safety-actuating mechanism with a fire chain of a safety type.

The technical result achieved during the implementation of the invention is expressed in increasing the reliability of the explosive device, increasing the effectiveness of combat use, ensuring the required safety.

The essence of the invention lies in the fact that in a contact explosive device containing a system of contact sensors and a safety-actuating mechanism with a firing circuit of a safety type, the system of contact sensors is made in the form of two types of sensors, the first of which is a pulsed magnetoelectric sensor of wave action, and the second shock wave contactor, both sensors are structurally combined in a single housing, the safety-actuating mechanism is made in the form of a rotary sleeve from the electric counter torus inside it and with a contact group located on it. The rotary sleeve is held by two stoppers, a pyrotechnic stopper and an inertial stopper. The contact group consists of flexible plate lamellas having an arc shape in cross section and with the ability to bend towards the axis of the rotary sleeve. The pyrotechnic stopper is in contact with the pyrotechnic composition, that is, it rests against the press fitting. The burning time of the press-fit TPZ is determined by the formula

TPZ = aTn

where Tn is the duration of the inertial overload at rocket launch;

and - coefficient taking into account the response time of the inertial stopper. This coefficient is equal to a = 0.6-0.8.

Only with this ratio is safety ensured during “pecking,” that is, if a missile is accidentally dropped after it leaves the launch tube in a dangerous proximity to the launch point.

Contact explosive device is powered from a power source located on board the rocket.

Figure 1 presents the functional diagram of the fuse and its placement on the rocket.

Figure 2 presents a variant of the electrical circuit of the fuse.

Figure 3 shows the structural arrangement of two contact sensors: a pulsed magnetoelectric sensor of wave action and a shock wave contactor in one housing.

Figure 4 shows a variant of the placement of the safety-actuating mechanism inside the fuse body and the layout of the electric detonator and the contact group in the rotary sleeve.

The fuse block diagram shown in FIG. 1 shows the fuse case 1, which is the carrier compartment of the rocket, inside which there is a pulsed magnetoelectric wave generator 2, structurally connected together with a shock wave contactor 3. Generator 2 is connected to an electric signal amplification circuit 4, from which the signal is supplied to the safety-actuating mechanism 5. The conclusions from the shock contactor 3 go directly to the actuating mechanism 5, since the signal from the shock mykatelya does not need to be strengthened. Next, the signal enters through the contact group 6 to the electric detonator 7, placed in a rotary sleeve, not shown in figure 1, in which the electric detonator is offset from the transfer charge 8.

The electrical circuit of the proposed technical solution, depicted in figure 2, consists of three circuits, one of which provides the removal of the first stage of protection and is connected with the mechanism for the rocket to exit the launch tube through the starting electric igniter 9. This electric igniter is electrically connected to the steering wheel opening mechanism 10.

The second circuit — the combat circuit — enables the firing circuit from the magnetoelectric sensor 2 through the amplifier 4 or from the shock contactor 3 directly, i.e. directly. The electronic circuit is powered by a storage capacitor "C". Charging the capacitor "C" is carried out by an electric circuit passing through a shunt 11 located in the rotary sleeve (not shown in figure 2). The signals from both sensors are fed to the electric detonator 7 via electrical contacts 6. The third circuit is a control circuit and serves to verify the absence of cocking of the fuse by means of an electric shunt 11a, which, like the shunt 11, is located on the rotary sleeve.

The system of integrated contact sensors shown in FIG. 3 consists of a pulsed magnetoelectric sensor structurally combined with a shock wave contactor and enclosed in a housing in the form of a sleeve 12, in which a magnetoelectric generator is located, consisting of an armature-contactor 13, ring 14, magnet 15, the yoke 16, the pads 17, the winding 18 wound on the frame 19, the adjusting core 20, and the wave shock contactor contains lamellas 21 mounted on the insulating sleeve 22. Anchor-contactor 13 is a common element for pulsed magnetoelectric sensor and shock contactor.

The adjusting core is used to set the static adjustment of the contactor armature to the required threshold, that is, the minimum impact of the elastic mechanical stress wave required to break the armature from the ring and move it by the contact distance.

The main mechanisms of the explosive device are located in the Central sleeve 23 (see figure 4). It contains a rotary sleeve 24, closed by a cover 25. The sleeve is mounted on an axis 26 and rotated by a rotary spring 27. A contact group of at least 6 lamellas 28a, 28b, 28c, 28d, 28e, 28f is installed in the sleeve, with four lamellas installed on one side of the rotary sleeve 24, and two lamellas 28e and 28f (in FIG. 4 they do not fall into the cut) are mounted on the back of the sleeve. The lamellas are made of thin spring tape and have the ability to bend towards the axis of the sleeve, which provides increased impact resistance when a rocket collides with a particularly strong barrier and the necessary contact pressure. The pins 29a, 29b, 29c, 29d abut the lamellas, which serve to connect the leads from the fuse and control circuit of the fuse. In this case, one pair of lamellas is connected to the terminals of the electric detonator, while the others are shorted by electric shunts 11 and 11a.

The rotary sleeve shown in figure 4, is presented in the idle position, that is, the electric detonator 7 is not in line with the transfer charge 8 located in the bottom of the fuse from the side adjacent to the warhead.

The sleeve is kept from turning - from the action of the spring 27 - two stoppers - pyrotechnic and inertial.

Pyrotechnic stopper 30 at one end enters the groove of the rotary sleeve, and the other end abuts under the action of the spring 31 into the sleeve with the pyrotechnic composition 32. Next to the sleeve 32 is the starting electric igniter 9.

The inertial stopper consists of an inertial body 33 entering a hole in the rotary sleeve. The inertial body is spring-loaded 34.

The lamellas of the battle circuit are connected to the electric detonator, and the control circuit to the electric shunt 11a. Between the terminals of the electric detonator, a resistor 35 is soldered, which serves to bypass from static charges that can accumulate on the electric detonator if it is accidentally destroyed with the formation of cracks.

The work of the proposed contact explosive device is as follows.

Before launching the rocket, the fuse is in the idle position, that is, the combat and fire chains are open. At the time of the launch of the rocket from the pipe, the fuse has an inertial overload, which sinks the inertial stopper 33, and the latter leaves the rotary sleeve, freeing it for further movement. But the sleeve continues to be held by the pyrotechnic stopper 30. With the further movement of the rocket in the launch tube, the rudder of the rocket is opened at the moment of exit from it and an electrical signal is supplied from the rudder opening system to trigger the starting electric igniter 9. A beam of fire from the electric igniter ignites the pyrotechnic composition 32, in the sleeve and after burning the pyrotechnic composition 32, the pyrotechnic stopper 30, under the action of the spring 27, disengages from the rotary sleeve 24, which rotates under the action of the spring 27 etsya so that EB 7 becomes a transfer charge 8. Contact sipe 28c and 28d are connected to the combat chain and lamella 28a and 28b opposite the control circuit opens. An explosive device cocked along the battle and electric circuit.

If after launching a rocket from the launch tube for some reason a pecking of the rocket occurs, for example, after a marching engine failure, the rocket fell dangerously close to the launch point, despite the fact that the inertial stop 33 worked, but the pyrotechnic element in the sleeve 32 did not burn out yet and thus the pyrotechnic stopper will not work and the final fuse cocking will not occur. In this way, the safety of the warhead of the rocket is ensured.

After cocking the fuse, the capacitor "C" is charged to the operating voltage from the on-board power source.

A wave of mechanical stress occurs when a rocket collides with an obstacle and propagates along the rocket shell to the zone where the sensor is located in the fuse.

In this case, depending on the intensity of the input mechanical signal, either the movement of the armature until the contact lamellas closes with its end or the movement of the armature by an amount less than the contact gap. However, in any case, the sensor will generate an EMF pulse, which, after amplification, enters the electric detonator, causing the fuse to fire and detonate the warhead.

This type of functioning occurs when a rocket collides with barriers of exceptionally low strength - the shell of a drifting balloon, the skin of a remotely piloted aircraft.

If the rocket meets an air target of normal strength, then in this case the anchor reliably closes the contacts 21 and the operation of the electric detonator 7 occurs without any signal amplification.

This can also happen in the event of an accidental failure of the amplification circuit 4, for example, a transistor failure.

Thus, extremely high reliability of the explosive device and safety are ensured.

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

Claims (3)

1. Contact explosive device comprising a system of contact sensors and a safety-actuating mechanism with a firing circuit of a safety type, characterized in that the system of contact sensors is made in the form of a sensor of a pulsed magnetoelectric wave generator and a sensor of a wave shock contact, combined in a single housing, and -executive mechanism is made in the form of a rotary sleeve with an electric detonator located inside it and a contact group installed on hub to hold the pyrotechnic inertia and stops. 2. Contact explosive device according to claim 1, characterized in that the contact group consists of flexible plate lamellas having an arc shape in cross section and made with the possibility of deflection towards the axis of the rotary sleeve. 3. Contact explosive device according to claim 1, characterized in that the pyrotechnic stopper is in contact with the pyrotechnic composition of the sleeve.

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