Method of bombing using rotating munition from low-altitude aircraft and its device

Abstract

FIELD: aviation.SUBSTANCE: unmanned aerial vehicles (UAVs) and low-altitude aircraft that carry out bombing from low and extremely low altitudes. The method of bombing using a rotating munition from a copter includes equipping the munition (1) with a centrifugal fuse (5), armed by achieving the required angular velocity, as well as a flexible connection (2), wound on the munition body with the possibility of free unwinding, installing the munition on a suspension and release device of the carrier, its transportation to the bombing area with subsequent release. The end of the flexible connection is secured to the carrier (3) directly or through a release mechanism (4). The unwinding of the flexible connection, which ensures the unwinding of the ammunition and the arming of the fuse, occurs under the action of gravity.EFFECT: increased efficiency of using rotating munitions during bombing from low-altitude aircraft is ensured, including at low speeds, down to zero speed values in hover mode.4 cl, 5 dwg

Description

[0001] Technical field

[0002] The invention relates to military mini and small-sized aviation, in particular to unmanned aerial vehicles (UAVs) and low-altitude aircraft that carry out bombing from low and extremely low altitudes.

[0003] Technology Level

[0004] A prior art discloses a method for deploying rotating munitions with centrifugal fuses located on the munition's axis of rotation. The fuses are armed when high angular velocities are reached during bombing after the munition's release, due to the oncoming airflow. These munitions can be used in disposable cluster bombs, as well as in containers suspended under combat aircraft or helicopters moving at high speeds. These containers may contain tubes housing the rotating munitions. The rotary munitions are delivered to the target by being inserted into a high-speed airflow, either upon deployment of the disposable cluster bombs or upon release from the containers' tubes.

[0005] However, this result is currently unattainable in mini and small aircraft due to the limited energy reserves in the electric batteries that power the flight. The limited speed of delivery of rotary munitions in small aircraft and the achievement of the angular velocity necessary to arm centrifugal fuses are possible only when dropped from high altitudes.

[0006] Furthermore, the limitations on the mass carried by a copter and other small-sized aviation devices do not allow the use of disposable bomb clusters and containers containing rotating munitions to deliver them to the target and introduce them into the airflow at high speeds to ensure the arming of the fuses.

[0007] A technical solution is known (patent US 3611930, priority dated October 12, 1971), consisting of a spherical munition body with aerodynamic extensions (protruding elements) whose diameter is greater than that of the munition. A centrifugal fuse is located in the center of the munition, the axis of rotation of which coincides with the axis of the munition. When high angular velocities are reached, the fuse is armed. The fuse's safety is ensured by the fact that its arming requires a high angular velocity, significantly higher than the possible rotational speed that occurs during operation and transportation. The method of using such munitions consists of transporting them to the target in closed disposable bomb clusters or in a container, ensuring the absence of oncoming airflow.After a single-use cluster bomb is delivered to its target, it is released from the carrier. Once removed from the carrier, the cluster opens, and the munitions are released. Use from containers involves direct release of the rotating munitions from the container tubes upon reaching the bombing area. Exposure to a high-speed incoming airflow causes the rotating munitions to spin at high angular velocities due to the airflow against the aerodynamic surfaces, which arms the centrifugal fuses.A significant drawback of the rotary munition with aerodynamic surfaces made directly on the hull is the increase in the munition's weight and size characteristics and, as a consequence, the reduction in the munition's warhead for a given payload capacity of the carrier. In addition, this leads to uneven fragmentation of the hull and a decrease in the initial velocities of the projectile fragments, which, in combination, reduces the effectiveness of the destructive effect.

[0008] A technical solution (US Patent 3964391, priority dated July 13, 1976) is also known, which involves installing a stabilizer on a munition with a centrifugal fuse. The fuse is armed by achieving high angular velocity, achieved by spinning the munition using blades. A disadvantage of this technical solution is the stabilizer, consisting of individual blades, which is labor-intensive to manufacture and requires increased material consumption. Furthermore, it has large dimensions and weight characteristics, which reduces the weight of the warhead for a given payload, and, consequently, the lethal effect.

[0009] A technical solution (patent RU 2239151 C1 dated April 23, 2003) is also known, in which an impeller, designed as a bandage, is installed on the munition. The munition is designed as two half-dumbbells connected by a centrifugal fuse, which is located on the munition's axis of symmetry. In addition, the impeller is mounted on the outer part of the munition. The introduction of the impeller increased the munition's rotation speed, reducing the time it takes for the munition to reach the rotation speed required to arm the fuse, thereby lowering the munition's combat altitude and increasing its rotation speed. A disadvantage of this technical solution is the increased dimensions of the munition due to the impeller, which requires increased storage space for the munition.Furthermore, the use of these munitions from delivery vehicles on mini and small aircraft is only possible when individually slung from a copter. However, the protruding surfaces of these munitions create aerodynamic drag, as, unlike bombs dropped from clusters and containers, the oncoming airflow impacts the munition suspended from the copter, reducing its flight speed. A significant drawback of this technical solution is the reduced payload due to the additional slack and the inclusion of an impeller within the munition. This reduces the warhead's size for a given payload capacity, and, consequently, reduces the effectiveness of the munition.

[0010] Disclosure of invention

[0011] The objective of the invention is to increase the efficiency of using rotary munitions from low-altitude aircraft that carry out bombing from low and extremely low altitudes, as well as to ensure the possibility of using rotary munitions in mountainous conditions, which are characterized by low air density, which does not allow the use of high-speed pressure for spinning the munitions and arming the centrifugal fuse.

[0012] This problem is solved by the invention winding a flexible connection, such as a ribbon, onto the outer surface of the munition. The munition is suspended from the carrier, followed by securing the free end of the flexible connection to the carrier. The munition is then delivered to the bombing area, dropped, unwound, and the munition, with the flexible connection wound onto its side, armed by unwinding the flexible connection. The munition falls onto the target, the armed fuse is triggered, and the target is effectively destroyed.

[0013] This technical solution is characterized by the presence of a flexible connection (tape), which is wound on the side surface, the length of which is selected based on the condition of ensuring the arming of the detonator, and the width of the flexible connection is selected in such a way that a change in the position of the center of mass of the ammunition, including with technological manufacturing errors that are within the limits of the specified width of the flexible connection, ensures the absence of nutation and precession of the ammunition during rotation, which increases the reliability of arming the centrifugal detonator.

[0014] In this case, to remove the flexible link (tape) from the carrier after the munition has unwound, a weakened section is created on the flexible link or the flexible link is connected to the carrier via a release device, and the other end of the flexible link is secured to the munition body. This solution results in the dropped munition being unwound by the flexible link during its fall, eventually unwinding. The kinetic energy of the unwound munition causes the flexible link to be pulled with great force, resulting in its rupture or the mechanism being released.

[0015] To reduce the aerodynamic drag of the suspended ammunition, the said flexible connection can be placed on the cavity of reduced diameter of the ammunition.

[0016] Premature triggering is prevented and safety during operation is increased by a polygonal coil, which has several protruding corners that prevent the ammunition from rotating freely during manufacturing and operation.

[0017] The result achieved by the above combination of features is increased effectiveness of rotary munitions when bombing from low-altitude aircraft, including at low speeds, down to zero hover speeds. This is achieved by reducing the weight and dimensions (by eliminating the passive mass and volume created by aerodynamic surfaces) and, consequently, increasing the warhead size for a given payload capacity. This is also achieved by eliminating uneven fragmentation of the hull and reducing the initial velocities of projectile fragments due to the presence of aerodynamic surfaces.Unlike ammunition equipped with aerodynamic surfaces, the said technical result of the invention is also ensured when using rotating ammunition in mountainous conditions, which are characterized by low air density, which does not allow the use of high-speed pressure for spinning the ammunition and arming the centrifugal fuse due to aerodynamic surfaces.

[0018] Brief description of drawings

[0019] The implementation diagram of the proposed invention is illustrated by figures, where:

[0020] Fig. 1 - shows a munition being transported by a carrier, with the flexible connection being disconnected together with the munition.

[0021] Fig. 2 - shows the ammunition after being dropped from the carrier, the flexible connection remains on the carrier.

[0022] Fig. 3 - shows a spherical-cylindrical munition

[0023] Fig. 4 - ammunition in the form of a half-dumbbell is shown

[0024] Fig. 5 - ammunition in the form of a half-dumbbell with a coil is shown

[0025] The following designations are introduced in figures 1, 2, 3, 4, 5: 1 - ammunition, 2 - flexible connection, 3 - carrier, 4 - tripping device, 5 - centrifugal detonator, 6 - polygonal coil.

[0026] Implementation of the invention

[0027] A method for dropping a rotating munition from a drone includes a munition 1 consisting of two parts connected by a centrifugal fuse 5. During ground preparation of munition 1, a flexible connection 2 (tape) is wound on the outer surface of munition 1, the length of which is selected based on the condition of ensuring the arming of the fuse, and the width of the flexible connection is selected in such a way that a change in the position of the center of mass of munition 1, including in the case of technological manufacturing errors that are within the limits of the specified width of flexible connection 2, ensures the absence of nutation and precession of munition 1 during rotation. The free end of flexible connection 2 is rigidly fixed to carrier 3, the second end of the flexible connection is attached to the body of munition 1, after which munition 1 is delivered to the bombing area.Upon command from the carrier, the munition is released (bombing is performed), as a result of the action of flexible link 2 on munition 1, it spins around its axis, ensuring the arming of centrifugal fuse 5, located on the axis of rotation of munition 1, and upon impact with an obstacle, munition 1 is triggered by the impulse of centrifugal fuse 5. Arming of centrifugal fuse 5 occurs due to the achievement of high angular velocities of rotation, achieved during the bombing process after the release of the munition. To ensure the removal of flexible link 2 (tape) from carrier 3 after the spinning of munition 1, a weakened section is made on flexible link 2 (tape) or flexible link 2 (tape) is connected to carrier 3 via a release device 4. This leads to the fact that the released munition 1, upon falling, is unwound by flexible link 2 (tape), until it unwinds.Under the action of the kinetic energy of the spinning ammunition 1, the flexible connection 2 (tape) is stretched with great force, as a result of which it is broken or the mechanism 4 is disengaged.

[0028] 1st embodiment of the device implementing the specified method. Fig. 3 shows a rotating munition 1, which consists of two parts connected by a centrifugal detonator 5, wherein a flexible connection 2 (tape) is wound onto the side surface of the munition, the length of which is selected based on the condition of ensuring the arming of the detonator, and the width of the flexible connection is selected in such a way that a change in the position of the center of mass of the munition, including in the case of technological manufacturing errors that are within the limits of the specified width of the flexible connection, ensures the absence of nutation and precession of the munition during rotation, which increases the reliability of the arming of the centrifugal detonator.

[0029] The 2nd embodiment of the device implementing the specified method, differing from the 1st embodiment of the device. - In the 2nd embodiment, shown in Fig. 4, the rotating munition 1 has the form of two hemispheres connected to each other by a centrifugal fuse 5, the flexible connection 2 (tape) is wound onto a cavity of reduced diameter of the munition 1, which reduces aerodynamic drag, as a result of which the rotation speed of the munition 1 and the unwinding of the flexible connection 2 increases.

[0030] A third embodiment of a device implementing the said method, differing from the first and second embodiments of the device. In the third embodiment, shown in Fig. 5, to improve safety by preventing rotation during manufacturing and operation, flexible coupling 2 is wound on a polygonal coil 6, the corners of which extend beyond the diameter of the ammunition and prevent free rotation of the ammunition.

[0031] 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 method for bombing a rotating munition from a copter, which includes equipping the munition with a centrifugal fuse, armed by achieving the required angular velocity, as well as a flexible connection wound onto the munition body, installing the munition on a carrier suspension and release device, transporting it to the bombing area with subsequent release, characterized in that the flexible connection is wound onto the munition body with the possibility of free unwinding, and its end is rigidly secured to the carrier, wherein the unwinding of the flexible connection, ensuring the unwinding of the munition and the arming of the fuse, occurs under the action of gravity.

2. The method according to paragraph 1, characterized in that the fastening of the flexible connection to the carrier is carried out through a release mechanism that ensures the separation of the flexible connection after it has been completely unscrewed.

3. A rotating munition consisting of two parts connected to each other by a centrifugal fuse, characterized in that a flexible connection is wound onto the munition, the length of which is sufficient to arm the fuse, and the width of which exceeds the possible deviations in the position of the center of mass of the munition.

4. A rotating ammunition according to paragraph 3, characterized in that the flexible connection is wound on a polygonal coil, the corners of which protrude beyond the diameter of the ammunition.

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