Device for unpacking aviation munition

Abstract

FIELD: aviation ammunition.SUBSTANCE: device for unpacking an aviation munition comprises a housing with a transverse partition provided with a channel, a pyroautomatic unit, a threaded cover with a contact unit, an electric filter, an electric igniter placed in a sleeve with a calibrated hole, and an arming indicator. In the channel of the transverse partition there is a motor with a vertical opening, having a bevelled edge, moved by a rod coming out through the wall of the housing. The bevelled edge of the engine is directed towards the cocking indicator. The diameter of the vertical hole of the engine is from 1.2 to 1.8 times the diameter of the calibrated hole, and the channel is closed by a sleeve with a calibrated hole.EFFECT: reliable operation of aircraft munitions with remote fuses exclusively under normal operating conditions.1 cl, 1 dwg

Description

[0001] Technical field

[0002] The invention relates to technical devices in the field of military equipment for decommissioning (detonating) aircraft munitions. It is preferably used for disposable cluster bombs (CBM) with submunitions, as well as other munitions requiring the use of remote detonators.

[0003] Technology Level

[0004] The ATK-10EB type remote detonator is known from the prior art. It is a remote detonator with a clock and safety mechanism, an electric pyrotechnic trigger, and an ignition device, designed for arming RBCs. The presence of a clock mechanism complicates and increases the cost of the design, and also increases the required volume of the detonator. The large number of mechanical parts and assemblies in the clock mechanism reduces the likelihood of failure and the accuracy of beam pulse delivery, and significantly increases the cost of the product. This detonator has a built-in mechanical safety device, which is not accessible for visual inspection. When the remote action time is set, this safety device ceases to function. The detonator's clock mechanism is activated by applying an electrical pulse to a ball fork from the carrier.One of the drawbacks is that if an unauthorized electrical impulse is applied to the preset time fuse, it will detonate. In modern electronic warfare environments and exposure to high-frequency electromagnetic waves, this fuse can be triggered by these factors. Therefore, the fuse's safety under electronic warfare conditions is not ensured. Furthermore, exposure to these electromagnetic fields can cause the electric igniter to detonate before the fuse's preset time, with the built-in mechanical safety device preventing the clock mechanism from starting.

[0005] An aircraft fuse is also known (RU No. 2592934, priority dated June 19, 2016). This fuse has a pre-arming indicator that indicates the activation of the electric igniter, ensuring operational safety. Furthermore, this invention includes an electrical filter that ensures the integrity of the electric igniter. Under conditions of electronic warfare and exposure to high-frequency electromagnetic waves, this fuse cannot be triggered by these factors, as the electrical filter blocks the electrical pulses generated by electronic warfare.

[0006] During combat use, the integrity of the membrane is visually checked before installing the fuse in the aerial bomb. If the membrane is damaged, installation of the fuse in the aerial bomb is prohibited. If the membrane is intact, the fuse is installed in the aerial bomb and the contact unit is connected to the electrical impulse supply mechanism of the aircraft carrier. Immediately before takeoff, the cap is unscrewed and removed (if the membrane is intact), the cylindrical part of the fuse is rotated and positioned perpendicular to the axis of the sleeve using a hinge joint. The cap is stored on the ground until the return of the aircraft carrier. If the aircraft carrier returns with undropped bombs, the cap is used to return the fuse to its original position.

[0007] If an aerial bomb is accidentally detonated with an electrical impulse being applied to the fuse and then armed, the fuse is returned to a safe state by moving the mechanical safety catch to its original position.

[0008] This ensures the fuse's safety against electronic warfare. However, this fuse is designed for use with high-explosive and high-explosive fragmentation bombs, which are detonated not during their trajectory but upon impact with an obstacle. Therefore, this fuse is a contact fuse, which precludes its use as a remote or decompression device.

[0009] Also known is an aircraft-based remote-detonation device using pyrotechnic retarders, the "Target Unpacking Device" (RU No. 2402744, priority dated June 5, 2009). It comprises a housing containing a pyroautomatics unit, consisting of a cylinder with pyrotechnic retarders mounted in parallel and terminating in a manifold located within the cylinder. A cup with a calibrated hole in the bottom ensures uniform operation of the electric igniter, as well as a threaded lid housing the electric pyrotechnic device with a contact unit. The manifold is connected in series with the output charge. An elastic sealing gasket and a rupture disc installed on the bottom of the housing ensure the housing's airtightness.

[0010] When the target is released from the carrier, an electrical impulse activates the electric igniter (EPU) through the contact unit. The resulting gases are throttled through a calibrated orifice in the cup and ignite the pyrotechnic delay elements. After the delay elements burn out, the output charge is ignited through the manifold. The gases generated by the charge combustion rupture the membrane and, exiting the URM housing, detonate the target.

[0011] The solutions used in this invention have increased efficiency, reduced the volume required to accommodate the product, and lowered its cost. A drawback of this technical solution is that it is only applicable for unpacking airdropped targets, which in turn limits its versatility. Another significant drawback is that unauthorized exposure to an electrical pulse will trigger the product.

[0012] Disclosure of invention

[0013] The objective of the invention is to increase the reliability of a remote detonator that ensures the unpacking (activation) of aviation ammunition, preferably for RBC and other ammunition that require the use of remote detonators.

[0014] This problem is solved by introducing into the fuse housing an electric filter installed in the electric igniter circuit, a fuse, which is a slider moved by a rod (preferably threaded), passing through the wall of the housing, as well as an arming indicator containing a bursting membrane installed in the housing.

[0015] The case is divided by a transverse partition into the cocking chamber and the pyrotechnic block chamber. The cocking chamber, closed by a threaded cover, contains an electric filter and an electric igniter, housed within a sleeve with a calibrated hole. The pyrotechnic block chamber contains boosters, retarders, and a powder (pyrotechnic) charge, connected by channels. A channel is formed in the transverse partition of the case, into which a slide is mounted and movable. Its movement is provided by a rod, preferably threaded. In addition, a cocking indicator containing a rupture disc is installed in the channel. The wedge-shaped slide has a transverse channel that ensures the connection of the chambers when setting them to the firing position. The slide is installed with its tapered section toward the cocking indicator membrane.The slider is pressed against the bottom of the channel by a sleeve with an electric igniter. As the slider moves toward the indicator, the calibrated hole aligns with the slider channel and the hole in the transverse partition. The ratio of the diameter of the hole in the wedge-shaped slider to the diameter of the calibrated hole ranges from 1.2 to 1.8.

[0016] The minimum ratio of the diameters of the hole in the engine and the calibrated hole in the sleeve is determined by the condition of stable activation of the pyroautomatic unit when the electric igniter is triggered in normal mode.

[0017] The maximum ratio of hole diameters ensures that the pyroautomatic unit does not trigger in the event of unauthorized activation of the electric igniter.

[0018] Thus, the introduction of an electric filter into this technical solution provides protection from external electromagnetic influences, and the introduction of calibrated holes in the wedge-shaped engine and sleeve with a diameter ratio of 1.2 to 1.8 leads to an increase in the reliability of the fuse operation (the probability of operation under normal conditions).

[0019] Premature activation is prevented and safety during operation is increased by a wedge-shaped engine moved by a rod and a cocking indicator that monitors the absence or presence of cocking.

[0020] The result achieved by this combination of features is the reliable operation of air-launched munitions with remote fuses exclusively under normal operating conditions. This is achieved by simultaneously ensuring reliable operation upon approach to the target and preventing premature activation both during operation (and, consequently, ensuring operational safety) and during the munition's flight to the target through protection from external electromagnetic influences.

[0021] Brief description of drawings

[0022] The implementation diagram of the proposed invention is illustrated by figures, where:

[0023] Fig. 1 shows a device for unpacking aviation ammunition in longitudinal section.

[0024] Implementation of the invention

[0025] The device for unpacking an aircraft munition contains a housing 1, divided by a transverse partition into two cavities, in one of which a pyroautomatic unit 2 is located. A cocking indicator 3 is installed in the wall of the housing. An electric filter 4 is installed in the second cavity. The filter is connected to a threaded cover 5, a contact unit 6 and an electric igniter 7 pressed by a sleeve with a calibrated hole. A channel with a wedge-shaped engine 9 installed, the movement of which is provided by a rod 10, is made in the transverse partition of the housing.

[0026] The operation of the aircraft ammunition unpacking device is implemented as follows.

[0027] The product is transferred to the combat position by mechanically moving the wedge-shaped engine 9 with the help of the rod 10 towards the cocking indicator 3 until it stops against the wall of the housing 1.

[0028] When an electrical impulse is supplied from the carrier impulse supply mechanism to the contact unit 6, the current passes through the electrical filter 4, which provides protection from external electromagnetic influences, located inside the cocking chamber, and activates the electric igniter 7. The activation of the electric igniter activates the pyroautomatic unit 2 when combustion products pass through the calibrated holes of the wedge-shaped engine 9 and the sleeve 8 with a diameter ratio of 1.2 to 1.8.

[0029] Safety during operation is ensured by the presence of a safety device consisting of a wedge-shaped slider 9, moved by a rod 10, and a cocking indicator 3, which monitors the absence or presence of the cocking of the aircraft munition unpacking device, both before installation and during preparation for use, including when connecting the contact unit 6 to the impulse delivery mechanism. The wedge-shaped shape of the slider 9, using a bevel, helps direct the combustion products formed during the operation of the electric igniter 7 towards the cocking indicator 3, which facilitates their removal from the closed volume of the first cavity and ensures the safety of the pyroautomatic unit 2 in the event of an unauthorized application of an electrical impulse to the contact unit 6.

[0030] For the claimed invention in the form as it is characterized in the claims, the possibility of its implementation with the help of the above-described design solutions and the ability to ensure the achievement of the specified technical result are confirmed.

Claims

A device for unpacking an aviation munition, characterized in that it contains a housing with a transverse partition provided with a channel, a pyroautomatic unit, a threaded cover with a contact unit, an electric filter, an electric igniter placed in a sleeve with a calibrated hole, and a cocking indicator, distinguished in that a slider with a vertical hole is placed in the channel of the transverse partition, having a beveled edge, moved by a rod extending through the wall of the housing, the beveled edge of the slider is directed towards the cocking indicator, the diameter of the vertical hole of the slider is from 1.2 to 1.8 times the diameter of the calibrated hole, and the channel is closed by a sleeve with a calibrated hole.

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