RU2211437C1 - Nose percussion fuse - Google Patents

Abstract

FIELD: combination fuse of double action, time and percussion, actuated by inertia movement of mechanisms at an impact with an obstacle and on expiration of the preset time period from the instant of the shot. SUBSTANCE: the nose percussion fuse for small-caliber artillery cartridges has a detonator aligned with the warhead, with a safety device installed between them, percussion inertia mechanism with a ball kinematically linked with the conical fairing of the body, with a retarder, and an inflammation device linked with the pyrotechnical charge of the beam self- destruction primer detonator. The novelty is in the fact that the inertia cocking mechanism is made as a power source and represent a self-actuating electrolytic battery with a RC-network of retardation closed to a photon-coupled pair linked with an igniter, which via a centrifugal contactor is connected to the power source, and the ball of the percussion inertia-reaction mechanism is loaded by the spring-loaded contact of the switch of the electric detonator adjoining the beam self-destruction primer detonator and electrically closed by means of the contacts of the gate throttly of the safety device, that is fixed by the gate of the powder lock communicating with the electric igniter. EFFECT: enhanced functional reliability of the simple construction of the combination double-action nose percussion fuse, contact at various impact angles and contactless in the trajectory of flight, time for self-destruction, enhanced accuracy of operation of the actuating mechanisms. 5 dwg

Description

 The invention relates to remote combined fuses of double action, temporary and shock, triggered by inertial movement of mechanisms when meeting with an obstacle and after a specified period of time from the moment of the shot, determined by the combustion of the powder charge of the self-destruction mechanism.

 The level of this technical field is characterized by a head detonator for small-caliber artillery ammunition according to patent AT 301395, F 42 C 16/01, 1972, which contains an inertial-reaction mechanism of an actuating prick tip, coaxial to a detonator capsule of a combat charge, a centrifugal safety mechanism, a moderator inertial cocking mechanism. The head fairing, kinematically connected with the centrifugal fuse and in which the shock mechanism is mounted, is made with a flat anti-rifle front end to turn the product along the normal when meeting with the target, which creates uniformity in the operation of the fuse.

 The disadvantages of the described analogue are the unsatisfactory reliability of the action of the striking mechanism at the maximum flight range at minimum angles of contact with the obstacle, when the reaction force is not enough to operate the firing device, and the absence of a self-destruction mechanism for cases of missed ammunition past the target, which reduces its functional reliability and combat effectiveness actions.

 The noted drawbacks are eliminated in the MG-25 head fuse for small-caliber unitary loading artillery cartridges containing a detonator coaxial to the warhead, between which a safety device is mounted, a shock reaction mechanism kinematically connected to the conical body fairing, an inertial cocking mechanism with a moderator, and an ignition device the pyrotechnic charge of the self-liquidation detonator beam capsule described in the book "23-mm twin unit ZU-23", Military Publishing , M., 1961, p. 102-103, fig. 14.2.

 This fuse for most of the matching essential features selected as the closest analogue to the proposed.

 The shock mechanism has a contact rod installed with the possibility of autonomous movement in the axial channel of the front end of the housing to the tip of the pruning device mounted on a spiral spring of the cocking mechanism, and the pyrotechnic charges of the initiating device and the self-destruction mechanism communicate with an additional igniter capsule equipped with an inertial pruning device.

 The detonator capsule is closed by a safety pad with a labyrinth flame retardant retardation sleeve.

 This fuse provides contact action at various angles of contact with the obstacle and temporary operation at a distance during the combustion of the powder charge, as well as preventing spontaneous operation in official use and in flight.

 However, the disadvantage of the known fuse is the large time range of the institution (40-100 m distance), determined by the spread in the duration of the pyrotechnic charge burning, and the unsatisfactory functional reliability of the mechanical actuators, which reduces the effectiveness of close combat and failures at maximum range at small meeting angles with the target.

 The task, the solution of which is the basis of the present invention, is to increase the functional reliability of the fuse combined action and the specified accuracy of the long-range cocking.

 The required technical result is achieved by the fact that in the known head fuse for small-caliber artillery cartridges containing a detonator coaxial to the combat charge, a safety device is mounted between them, an inertial-reaction shock mechanism kinematically connected to the conical body fairing, an inertial cocking mechanism with a moderator, and an ignition device, associated with the pyrotechnic charge of the radiation detonator capsule detonator self-destruction, according to the invention, the inertial mechanism the cocking is made as a power source and is an ampoule electrolytic battery with an RC retardation circuit closed to an optocoupler connected to an electric igniter, which is connected through a centrifugal contactor to the power source, and the ball of the inertial-reaction shock mechanism is loaded with a spring-loaded contact of the detonator commutator adjacent to a self-liquidating detonator radiation capsule and an electrically closed safety device by means of the contacts of the slide gate of the safety device, Otori locked gate gunpowder stop communicating with the electric spark.

 Distinctive features ensured an increase in the functional reliability of a combined dual-action head fuse, contacting at different angles of contact with the goal of being contactless on the flight path, temporary for self-liquidation, and the accuracy of actuators.

 The execution of the inertial cocking mechanism in the form of an ampoule electrolytic battery with a charging RC circuit increases the speed and reliability of operation of functional interconnected mechanisms, and the use of this energy-containing battery as a power source for structural actuators simplifies the design.

 Equipping an energy-containing autonomous power source with a threshold device in the form of an optocoupler, which contactlessly controls, like a relay, the fuse's electrical circuits, providing isolation between them, allows an order of magnitude increase compared to the pyrotechnic mechanism in the prototype, which is 10-15% (40 + 6 m). This improves the effectiveness of close combat and the reliability of the fuse when in contact with an obstacle.

 A centrifugal contactor serves as an additional step in the automatic protection against unauthorized operation of an electric igniter during an abnormal stop of the ammunition in the weapon barrel, which mechanically excludes access to the combat charge and the launch of the self-destruction mechanism.

 The fuse is equipped with a multi-stage (pyrotechnic, sequentially duplicated mechanical) safety device of the warhead detonation channel, which electrically blocks the operation of the electric detonator, increasing safety during official handling and operation.

 The constructive implementation of the inertial-reaction shock mechanism as a switch for the power circuit of the executive electric detonator expands the functions and ensures reliable fuse operation at almost any meeting angle with the obstacle.

 Therefore, each essential feature is necessary, and their combination in a stable relationship is necessary to achieve the novelty of quality that is not inherent in the characteristics of disunity, that is, a new sum effect is obtained.

The invention is illustrated by the drawing, which has purely illustrative purposes and does not limit the scope of the rights of the totality of the features of the formula, which shows:
- figure 1 is a longitudinal section of a fuse,
- figure 2 is a section along aa in figure 1,
- figure 3 is a section along BB in figure 1.

 - figure 4 is a section along BB in figure 3. centrifugal contactor.

 - figure 5 is a schematic diagram of a fuse.

 A specific example of the invention is illustrated on the design of the head fuse grenades for grenade launchers brands AGS-17 and TBK-722K.

 In the housing 1 (Fig. 1), closed by a conical head fairing 2, a power source 3, which is an ampoule electrolytic battery, an inertial-reaction shock mechanism 4, mounted in a carrier sleeve 5, where the pyrotechnic self-destruction charge 6 is placed, is successively mounted from top to bottom with a radiation capsule-detonator 7, which is adjacent to the Central electric detonator 8.

 A warhead 9 is isolated in the tail part of the fuse, above which a slide gate 10 is mounted with the possibility of lateral movement, fixed in the extreme left (according to the drawing) position by the bolt lock 11 of the safety mechanism 12. When the atom channel 13 of the electric detonator 8 is connected with the gate charge 9 damper 10.

 The shutter 11 is loaded with a spring 14, based on a pyrotechnic charge 15.

 The gate valve 10 is loaded with a spring 16 (figure 2). In the gate valve 10, a through hole 17 is made for direct connection of the electric detonator 8 with the combat charge 9 in the working position.

 The power source 3 contains a glass ampoule 18 with an electrolyte 19 mounted on a coil spring 20 above the tip 21, and radial plate electrodes 22. The power source 3 is equipped with a long-cocking device made in the form of an RC chain (Fig. 5) with an optocoupler 23 connected in parallel , the output of which is associated with an electric igniter 24, communicating with the pyrotechnic charges 6 and 15 (figure 3).

 An electric igniter 24 is connected to a power source 3 through a contactor SA1 (Fig. 5). The power source 3 through the switch SA2 is connected to the electric detonator 8 shorted by the switch SA3.

 The centrifugal contactor SA1 (Fig. 4) has a fixed contact 25 fixed in a radially mounted housing 1 of a mounted current-carrying cup 26, where a mass 28 loaded with a spring 27 with a contact 29 is mounted with the possibility of axial movement.

 The switch SA3 is formed by normally closed contacts 30 (FIG. 2) of the slide gate 10.

 The coaxially located movable 31 and fixed 32 contacts of the switch SA2 (Fig. 1) are mounted on a slider 33 and a support 34 of an inertial-reaction shock mechanism 4, respectively, between which a Belleville spring 35 is mounted. On the opposite side of the slide 33 in an inclined groove radially symmetrical to the axis of the fuse 36, a central spacer ball 37 is placed. The support 34 is rigidly connected to the sleeve 5, which is kinematically closed through the ring 38 to the head conical fairing 2.

 The fuse works as follows.

 When fired under the influence of inertia, the glass ampoule 18 (Fig. 1) moves downward relative to the housing 1, compressing the spring 20, and splits the sting 21, and under the action of centrifugal rotation forces of the grenade, the contactor SA1 is activated (Fig. 4): mass 28 moves to the periphery of the housing 1, compressing the spring 27, and closes the contact 29 with the fixed contact 25, thereby connecting the electric igniter 24 to the power source 3 (figure 5).

 The electrolyte 19 is poured between the radial plate electrodes 22 (Fig. 1), as a result of which an electric current is generated charging the capacitor C (Fig. 5) of the RC circuit.

 Ampoule battery 3 enters the mode at a distance of 1.6-14 m flight, and the capacitor C is charged to an operating voltage of 12 V for 0.3 s flight (approximately 40 m flight), after which the threshold optocoupler 23 is triggered by connecting an electric igniter 24 to the power source 3 - distant guidance is carried out.

 In this case, the electric igniter 24 is activated and ignites the pyrotechnic charges 6 and 15 (Fig. 1). The charge 15 burns out almost instantly, while the rod shutter 11 of the safety mechanism 12 rises by the elastic forces of the spring 14, releasing the slide gate 10, which, under the action of the spring 16, moves to the extreme right position, where the hole 17 is aligned with the center line of the electric detonator 8 and the combat charge 9 , and the contacts 30 of the switch SA3 open, removing the short circuit of the electric detonator 8.

 The fuse is ready for basic operation.

 When the ammunition encounters a flight path with a target, a kinetic blow occurs, as a result of which the support 34 (Fig. 1) of the inertial-reaction mechanism 4 through the sleeve 5, the ring 38 and the head fairing 2 is braked on the obstacle, and its slider 33 inertially continues to move forward and compressing the spring 35, moves the contact 31 to the closure with the contact 32 - the switch SA2 is activated (figure 5), supplying voltage to the electric detonator 8.

 The blast wave of the triggered electric detonator 8 through the influence initiates the detonation of the warhead 9, the impulse of which undermines the ammunition.

 When the ammunition meets the maximum flight range with an obstacle at the ricochet corners, the side part of the fuse case 1, the ball 37 inertially moves towards the impact along the inclined radial channel 36. When the atom ball 37 reactively forcibly moves the slider 33 with the contact 31 in the axial direction of the fuse until it closes with fixed contact 32.

 Further, the action of the functional elements of the fuse occurs as described above.

 In the case of missed ammunition past the target after 40-45 from a flight at a distance of about 2 km, a pyrotechnic charge 6 burns out, a directed fire pulse of which arrives at the beam detonator capsule 7, causing it to fire. Then, detonator 8 and main charge 9 are detonated through the influence in series, the rupture of which ensures self-destruction of the ammunition.

 In the case of stopping the ammunition in the channel of the barrel of the weapon and at the same time lack of rotation, which is possible with a damp propellant charge, the centrifugal contactor SA1 will almost instantly break the power supply circuit of the electric igniter 24 (Fig. 5), de-energizing it, since under the action of the spring forces 27 4) the mass 28 with contact 29 will return to its original position from the stationary contact 25.

 This prevents the initiation of pyrotechnic charges 6 and 15 (Fig. 1), that is, respectively, the self-destruction mechanism does not start and the protection of the slide gate 10 is not removed, which mechanically does not allow access to the combat charge 9. Therefore, the fuse is completely safe in unauthorized use operations in official circulation.

 Thus, the reliable operation of the fuse in all modes of contact and non-contact action, when meeting with the target and after a given flight time.

 A comparative analysis of the proposed technical solution with identified analogues of the prior art, from which the invention does not explicitly follow for an ammunition specialist, revealed that it is unknown, and given the possibility of serial production of the claimed fuse, we can conclude that the patentability criteria are met.

Claims (1)

 A head detonator for small-caliber artillery cartridges containing a detonator coaxial to the warhead, between which a safety device is mounted, an inertial-reaction shock mechanism with a ball kinematically connected to the conical body fairing, a moderator, and an ignition device associated with the pyrotechnic charge of the detonator beam characterized in that the inertial cocking mechanism is made as a power source and is an ampoule electric an tactical battery with an RC retardation circuit closed to an optocoupler connected to an electric igniter, which is connected to a power source through a centrifugal contactor, and the ball of an inertial-reaction shock mechanism is loaded with a spring-loaded contact of the detonator commutator adjacent to the self-liquidation detonator beam capsule and electrically closed the gate valve of the safety device, which is fixed by the shutter of the powder stop, which communicates with the electric ignition it.

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