Large caliber machine gun standoff airburst projectile for intercepting micro-uavs

Abstract

The application discloses a large-caliber machine gun fixed-distance air burst bomb mainly used for intercepting micro unmanned planes, which comprises a head fire control module, a middle safety control and detonation module, a tail explosive charging module and a bomb body. The head fire control module mainly comprises a bullet head shell, an inductive charging and geomagnetic signal detecting revolution number fixed-distance fire control module. The bomb body contains the middle safety control and detonation module and is connected with the head fire control module and the tail explosive charging module. The middle safety control and detonation module comprises an isolation ball, a detonator, an open ring, a ball seat, a booster tube seat, a booster tube shell, a booster explosive, a shear pin and a gasket. The tail explosive charging module comprises a bomb bottom, a sealing ring, a reinforcing cap and an explosive charge, namely a warhead. The warhead adopts a warhead-integrated structure, a ball rotor explosion-proof and delay explosion-proof mechanism and a magnetic anti-recovery recoil safety mechanism and a booster sequence, and adopts an integrated design of a belt and a bomb body structure, so that the layout is compact, safety is good and the bomb body has high launching strength.

Description

Technical Field

[0001] This invention pertains to ammunition technology, specifically to a large-caliber machine gun fixed-range airburst round primarily used for intercepting micro-sized unmanned aerial vehicles. Background Technology

[0002] Compared to the advantages of drones, such as simple structure, low cost, small target size, and strong concealment, ground-based air defense weapons targeting manned aircraft and missiles are limited by their own conditions, resulting in short effective interception time, low target interception rate, and high interception cost. According to the report "Application Status and Prospect of Firepower Interception Equipment in Anti-UAV Operations (Ren Yaning, Liu Dapeng, Shi Xinxin, Proceedings of the 2022 UAV Systems Summit Forum (USS2022)," the Tor air defense missile system, the Pantsir gun-missile system, and the 9K333 Willow portable air defense missile are currently used for UAV interception. Among them, the Tor-M2 fire unit is equipped with 16 vertically launched 9M338K surface-to-air missiles; the Pantsir-S1 gun-missile system is equipped with a 2A72 30mm anti-aircraft gun, two 6-cell surface-to-air missile launchers, and 12 9M311M missiles; the Willow portable air defense missile has a range of over 6km, is equipped with a 2.5kg warhead, and the entire launch device weighs 17.25kg. The US FIM-92 Stinger surface-to-air missile is 1.52m long, 70mm in diameter, and weighs 10.1kg, with the launch tube and handle weighing approximately 15.2kg. The UK Starlight surface-to-air missile system is 1.397m long, 127mm in diameter, and has a launch tube outer diameter of 274mm. The UK Euroswept lightweight multi-purpose missile is 1.3m long, 76mm in diameter, and weighs 13kg. These systems lack the capability to detect low-flying unmanned aerial vehicles (UAVs) with small radar cross-sections, especially micro-UAVs.

[0003] The fixed-range airburst fuze's multi-beam directional pre-fragmented warhead forms dense and effective fragments, enabling efficient interception of aerial targets (see: Lou Wenzhong, He Bo, Feng Hengzhen, et al. Real-time simulation and hatch opening distance study of terminal air defense interception of small-caliber fixed-range airburst projectiles. *Acta Armamentarii*, 2023-01-02:1-10). The Swiss-developed AHEAD projectile is a cluster-type anti-aircraft and anti-missile munition equipped with an electronic time fuze, primarily used in 35mm anti-aircraft gun weapon systems to deal with small, low-altitude, and fast-moving incoming targets, such as various surface-to-air missiles, with high-density firepower. Specifically, the AHEAD projectile uses a programmable electronic time fuze to precisely control the projectile's detonation at the optimal position in front of the target. At the moment of detonation, hundreds of tungsten alloy submunitions inside the magazine are ejected under the action of inertial and centrifugal forces, forming a dense submunition field, significantly improving the AHEAD projectile's hit probability and damage performance (see: Wu Yingfeng. Research on damage probability model of AHEAD ammunition system. Nanjing University of Science and Technology, 2007). The AHEAD round consists of a warhead casing, a projectile body, a cylindrical tungsten alloy submunition within the magazine, directional propellant, and a programmable electronic time fuse at the base. The programmable electronic time fuse at the base comprises a receiving antenna, a programmable integrated circuit, a rapid activation battery, a detonator, a mechanical safety and defusal mechanism, and a timed self-destruct mechanism. (See: Liu Gang. Application of AHEAD ammunition in air defense weapons. Firepower and Command Control, 2010, 35(S1):87-88+92). The AHEAD ammunition is a complete system, including the AHEAD projectile, a muzzle velocity signal processing device, an information processing and setting device, and a fire control computer. These devices work together to complete the firing of the AHEAD ammunition. When AHEAD ammunition is fired, two velocity measuring coils of the muzzle velocity signal processing device generate an induced magnetic field. When the projectile passes through the induced magnetic field, the magnetic field generates an induced pulse signal. This pulse signal is processed and transmitted to the muzzle information processing and setting device. The information processing and setting device digitizes this signal to obtain the projectile's initial velocity value. This value is sent to the fire control computer to calculate the average initial velocity. It is also compared with the average initial velocity returned by the fire control computer to correct the projectile's flight time calculated by the fire control computer. At the same time, the information processing and setting device encodes the corrected projectile flight time. Just before the projectile leaves the muzzle, it is converted into a pulse signal and assigned to the programmable electronic time fuse at the bottom of the projectile. The programmable electronic time fuse is activated and the timing begins. When the projectile reaches the set time, the programmable electronic time fuse generates a ignition signal, detonating the projectile and ejecting the explosive charge. The projectile explodes, and the tungsten alloy submunition inside is thrown forward to form a submunition field, achieving the AHEAD projectile's hit and damage to the target. The forward scattering of the tungsten alloy bullet inside the AHEAD projectile mainly depends on the projectile's ballistic velocity, rather than on the propellant charge. Therefore, the amount of directional propellant in the projectile is not large. The propellant is mainly used to blast open the pre-grooved metal casing. The initial velocity of the tungsten alloy bullet is comparable to the ballistic velocity of the AHEAD projectile.During the development of the AHEAD projectile, Switzerland discovered that tungsten alloy bullets could not directly destroy the small anti-tank missiles used in the tests, but instead damaged the guidance section of the missiles, causing them to deviate (see: Liu Tengyi, Chen Xi, Yang Dong. Development concept and analysis of 35mm anti-aircraft gun ammunition. Journal of Artillery Launch and Control, 2010, 117(01): 84-88).

[0004] The machine guns and ammunition described in "World Handbook of Small Arms" (edited by Xiao Youqiao, Beijing: Ordnance Industry Press, 1st edition, June 1997) do not include ammunition specifically designed to intercept small drones. The relatively mature solid shot or double-headed bullets used in machine guns are unlikely to form an intercepting barrage and provide effective interception. Summary of the Invention

[0005] This invention draws upon the principles of the Swiss 35mm anti-aircraft gun's AHEAD missile interception system and manned aircraft, proposing a large-caliber machine gun-based fixed-range airburst projectile primarily for intercepting micro-sized unmanned aerial vehicles (UAVs), but also for attacking exposed personnel. This invention's large-caliber machine gun-based fixed-range airburst projectile, mainly for intercepting micro-sized UAVs, consists primarily of an electronic range-setting fuse at the head and a warhead with explosive charge at the tail. The electronic module housing of the electronic range-setting fuse, as well as the structural components of the safety and disarming mechanisms, together with the warhead housing, form fragments that, combined with the entrainment velocity of flight, are used for ranged destruction of micro-sized UAVs and personnel.

[0006] The technical solution for achieving this invention is as follows: a large-caliber machine gun fixed-range airburst projectile primarily used for intercepting micro-sized unmanned aerial vehicles (UAVs), comprising a head firing control module, a central safety control and detonation module, a tail explosive loading module, and a projectile body, all integrated in a single design. The brass projectile body is the main structural component of the airburst projectile, containing the central safety control and detonation module and connecting the head firing control module and the tail explosive loading module. The head firing control module includes a titanium alloy projectile casing, an induction charging and geomagnetic signal detection speed-based fixed-range firing control module within the projectile casing, and a nitrocellulose film cover. The central safety control and detonation module, with explosion-proof and redundant safety functions, includes a ball rotor explosion-proof and delayed-release explosion-proof mechanism, a centrifugal safety mechanism, and a magnetic anti-recovery recoil safety mechanism and detonation sequence, arranged from top to bottom within the projectile's internal bore, achieving safety functions for the flame detonator within the isolation ball and spatial explosion-proof functions. The tail explosive loading module, connected by threads, is the warhead of the airburst projectile.

[0007] Compared with the prior art, the significant advantages of this invention are:

[0008] (1) Adopting the integrated design concept, the airburst bomb’s head ignition control module, middle safety control and detonation module and tail explosive charge module are integrated into a whole structure by the bomb body. The head ignition control module and middle safety control and detonation module are in front, and the tail explosive charge module is in the back. The fragments generated during the explosion are all forward, resulting in strong damage.

[0009] (2) The belt and the projectile body are integrated, the structure is simple, and the projectile launch strength is effectively improved.

[0010] (3) The ball rotor explosion-proof and delayed explosion-proof mechanism is adopted. The output end of the flame detonator faces outward and has a dual-axial flame input function. It is symmetrically placed in the isolation ball, which has high ignition reliability. Under the explosion-proof state, the flame transmission channel is blocked, and the fire insulation safety is high.

[0011] (4) A magnetic anti-recovery recoil safety mechanism and detonation sequence are adopted. The gasket is made of permanent magnet. After the safety is released, it tightly attracts the detonation tube seat made of ferromagnetic material to prevent the detonation tube seat from returning to the safe position after the recoil overload disappears. It is mainly achieved by materials, does not take up much space, and is reliable. Attached Figure Description

[0012] Figure 1 This is a longitudinal cross-sectional schematic diagram of the large-caliber machine gun fixed-range airburst projectile structure of the present invention in its assembled state, which is mainly used to intercept micro-small drones.

[0013] Figure 2 This is a cross-sectional view (AA) of the ball mount of a large-caliber machine gun, primarily used for intercepting micro-drones, in the assembled state of the present invention.

[0014] In the diagram, 1 is the warhead casing, 2 is the induction charging and geomagnetic signal detection speed distance ignition control module, 3 is the cover plate, 4 is the isolation ball, 5 is the flame detonator, 6 is the open ring, 7 is the detonator casing, 8 is the detonator charge, 9 is the shear pin, 10 is the detonator base, 11 is the ball seat, 12 is the warhead body, 13 is the washer, 14 is the reinforcing cap, 15 is the sealing ring, 16 is the upper explosive charge, 17 is the lower explosive charge, and 18 is the warhead base. Detailed Implementation

[0015] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only a part of the embodiments of the present invention, and not all of them. All other embodiments obtained by those skilled in the art based on the embodiments of the present invention without creative effort are within the protection scope of the present invention.

[0016] In this invention, descriptions involving "first," "second," etc., are for descriptive purposes only and should not be construed as indicating or implying their relative importance or implicitly specifying the number of technical features indicated. Therefore, a feature defined with "first" or "second" may explicitly or implicitly include at least one of that feature.

[0017] In this invention, unless otherwise explicitly specified and limited, the terms "connection," "fixing," etc., should be interpreted broadly. For example, "fixing" can mean a fixed connection, a detachable connection, or an integral part of a structure. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0018] like Figure 1 and Figure 2 As shown, a large-caliber machine gun fixed-range airburst round mainly used for intercepting micro and small drones includes a warhead casing 1, an induction charging and geomagnetic signal detection speed fixed-range firing control module 2, a cover plate 3, an isolation ball 4, a flame detonator 5, an open ring 6, a detonator casing 7, a detonator charge 8, a shear pin 9, a detonator seat 10, a ball seat 11, a warhead 12, a washer 13, a reinforcing cap 14, a sealing ring 15, an upper explosive charge 16, a lower explosive charge 17, and a warhead base 18.

[0019] The warhead casing 1 is a rotating body with a hemispherical top and a cylindrical lower half connected by an arc surface in the middle. A groove is located on the cylindrical surface. The interior of the warhead casing 1 has a downward-facing stepped blind hole. The upper half of the outer contour of the projectile body 12 is also an arc surface, smoothly connecting with the arc surface of the warhead casing 1, resulting in a streamlined frontal contour of the airburst round. The lower half of the projectile body 12 is also a cylindrical surface with two strip-shaped protrusions, forming the integrated projectile bands. The central axis of the projectile body 12 has seven stepped through holes, numbered from top to bottom as the first, second, third, fourth, fifth, sixth, and seventh step holes. The inner diameter of the first step hole is slightly smaller than that of the second step hole, formed during assembly by narrowing the opening at the upper edge of the projectile body 12, which bends slightly inward to fit precisely into the groove on the warhead casing 1. The inductive charging and geomagnetic signal detection speed-distance firing control module 2 is installed in the inner hole of the bullet casing 1 and covered by the cover plate 3. The bullet casing 1 is inserted into the second-stage hole, and the outer cylindrical surface of the bullet casing 1 fits tightly with the inner wall of the second-stage hole. The third-stage hole has the smallest inner diameter and is the ignition hole between the bullet head firing control module and the middle safety control and detonation module. The cover plate 3 is above this ignition hole, which separates the bullet head firing control module from the middle safety control and detonation module.

[0020] The third and fourth level holes on the inner contour of the projectile 12 are transitioned by an arc, forming a hemispherical cavity with a short cylindrical section, which serves as the housing and movement space for the isolating sphere 4. The lower end of the sixth level hole on the projectile 12 has an internal thread. The isolating sphere 4 has two identical transverse holes on the left and right sides, coaxial with their axes passing through the center of the sphere, used to house the flame detonators 5. The two flame detonators 5 are identical, possessing biaxial flame input functionality, with their output ends facing outwards within the transverse holes. A first central hole is positioned at the horizontal axis of the two transverse holes. The diameter of the first central hole is smaller than the two transverse holes and connects them, serving as the ignition channel between the two flame detonators 5. Above the first central hole, a second central hole is located along the vertical axis, perpendicular to and connecting to the first central hole. The outer contour of the isolating sphere 4 is an incomplete sphere. Besides the two transverse holes where the flame detonators 5 are placed and riveted together to form the left and right end faces, a small spherical notch is also removed from the lower part of the isolating sphere 4 to form the lower end face. Between the left and right end faces and the lower end face, there is a cylindrical surface along the vertical axis to fix the open ring 6. This cylindrical surface is not connected to the left and right end faces and the lower end face.

[0021] The ball seat 11 is a rotating body, and the cavity between its upper end face and the hemispherical space of the projectile 12 is a pre-designed explosion-venting cavity. The outer contour of the ball seat 11 is a two-stepped shaft, divided into a first-stepped shaft and a second-stepped shaft from top to bottom. The first-stepped shaft mates with the fifth-stepped hole of the projectile 12, and the second-stepped shaft mates with the sixth-stepped hole of the projectile 12, thereby limiting the movement of the ball seat 11. The ball seat 11 has two-stepped through holes along its central axis, namely an upper-stepped hole and a lower-stepped hole. A groove is carved at the center of the upper end face of the ball seat 11 to form an upper ball socket, which also serves as the accommodating and movement space for the isolation ball 4. The upper ball socket connects to the upper-stepped hole. The second-stepped shaft of the ball seat 11 has a first radial hole that connects to the lower-stepped hole. The detonator seat 10 is also a rotating body with an outer contour consisting of a two-stepped shaft. From top to bottom, it is divided into a third-stepped shaft and a fourth-stepped shaft. The third-stepped shaft mates with the aforementioned upper stepped hole, and the fourth-stepped shaft mates with the aforementioned lower stepped hole, thus limiting the position of the detonator seat 10. A second radial hole is provided on the fourth-stepped shaft at the position of the first radial hole on the second-stepped shaft of the ball seat 11. The first radial hole and the second radial hole are connected. An upward-facing blind hole is opened inside the detonator seat 10. The second radial hole leads directly into the blind hole, and the detonator 8 is installed inside the detonator shell 7 and inverted within this blind hole. Five detonation relief grooves are located on the outer circumference of the ball seat 11. These grooves are evenly distributed along the circumference, bypassing the position of the first radial hole. The grooves penetrate the upper and lower end faces and extend inward near the lower end face, connecting to the internal stepped hole. The cross-sectional shape of the detonation relief grooves is inverted T-shaped.

[0022] An open ring 6 is disposed in the venting cavity of the aforementioned projectile 12, coaxial with the cylindrical surface of the isolating ball 4, with its upper end face abutting against the isolating ball 4 and its lower end face abutting against the upper end face of the ball seat 11. The isolating ball 4, the flame detonator 5, and the ball seat 11 constitute a ball rotor explosion-proof and delayed-release explosion-proof mechanism. The open ring 6 fixes the isolating ball 4 in place so that it cannot rotate. The isolating ball 4, the open ring 6, and the ball seat 11 constitute the centrifugal safety mechanism of the ball rotor explosion-proof and delayed-release explosion-proof mechanism, which is the first safety for the flame detonator 5 inside the isolating ball 4. A shear pin 9 is disposed in the connecting channel between the first radial hole and the second radial hole, fixing the detonator seat 10 and the internal detonator shell 7 and detonator charge 8, and making the detonator seat 10 a certain distance away from the lower washer 13. At this time, the upper end face of the detonator seat 10 is flush with the detonator shell 7, extends out of the upper stepped hole of the ball seat 11, abuts against the lower end face of the isolating ball 4, and also fixes the isolating ball 4 in place so that it cannot rotate. The detonator casing 7, shear pin 9, detonator seat 10, ball seat 11, washer 13, and projectile base 18 together form a magnetic anti-recovery recoil safety mechanism and detonation sequence, which is the second safety measure for the flame detonator 5 inside the isolation sphere 4. Inside the projectile body 12, the isolation sphere 4, flame detonator 5, opening ring 6, detonator casing 7, explosive charge 8, shear pin 9, detonator seat 10, ball seat 11, and washer 13 together form the central safety control and detonation module.

[0023] The airburst bomb's tail explosive loading module, i.e., the warhead, consists of a base 18 that is a rotating body. The upper half of its outer contour is a four-stepped shaft, and the lower half is a cone. Along the axis, from top to bottom, are the fifth, sixth, seventh, and eighth step shafts, with diameters increasing sequentially. The sixth step shaft has external threads that connect to the internal threads of the sixth step hole in the projectile body 12. The seventh step shaft mates with the seventh step hole in the projectile body 12. The lower end face of the projectile body 12 and the sealing ring 15 abut against the shoulder between the seventh and eighth step shafts of the base 18, achieving positioning and connection between the projectile body 12 and the base 18. Inside the base 18 are upward-opening second-order blind holes. Along the axis, from top to bottom, are the eighth and ninth step holes, with the inner diameter of the eighth step hole slightly larger than that of the ninth step hole. The washer 13 is made of a permanent magnet and is installed in the eighth-order hole. The upper end face of the projectile base 18 and the upper end face of the washer 13 are flush together and abut against the lower end face of the ball seat 11 to limit the ball seat 11. The ball seat 11 is fixed by spot riveting. The explosive charge is divided into two parts. The upper explosive charge 16 is pressed into the reinforcing cap 14 and installed together with the lower explosive charge 17 in the ninth-order hole of the projectile base 18, and fixed by spot sealing.

[0024] In the factory-safe condition, the airburst missile is in its safe position. At this time, the warhead casing 1 is mounted above the missile body 12, with the upper edge of the missile body 12 engaging the annular groove on the warhead casing 1. The missile base 18 is tightened to the bottom of the missile body 12 with a certain torque, pressing upwards against the ball seat 11. The open ring 6 fixes the isolating ball 4 in place, preventing it from rotating. The shear pin 9 is inserted into the connecting channel between the first radial hole of the ball seat 11 and the second radial hole of the detonator seat 10, securing the detonator seat 10 and the detonator casing 7 and detonating charge 8 contained therein. The detonator seat 10 and detonator casing 7 extend from the upper stepped hole of the ball seat 11, abutting against the lower end face of the isolating ball 4, also fixing the isolating ball 4 in place, preventing it from rotating. In this state, the flame detonator 5 installed in the isolating ball 4 is connected to the preset explosion-proof cavity and separated from the detonating charge 8. That is, the open ring 6, shear pin 9, and detonator seat 10 secure the flame detonator 5 in the explosion-proof position. At the same time, although the washer 13 made of permanent magnet generates magnetic force to attract the detonator seat 10 made of ferromagnetic material, the shear pin 9 locks the detonator seat 10 in place. The lower end face of the detonator seat 10 is a certain distance away from the explosive charge below, forming a cavity that is connected to the preset explosion relief cavity through the explosion relief groove on the ball seat 11. That is, the shear pin 9 fixes the explosive charge 8 in the space explosion-proof position, which can reduce the pressure when accidental ignition occurs and the bullet is in a safe state.

[0025] During the handling of airburst rounds, reliable transportation, drops, impacts, and various tactical maneuvers will not cause the bullet casing 1 and the base 18 to detach from the bullet body 12. The flame detonator 5 is always in an explosion-proof state. Under these circumstances, it is believed that there is no possibility of accidental ignition and explosion of the poly-black-14 explosive charge. Even if the detonator accidentally ignites and explodes, it will not ignite or set off the explosive charge and explosive charge, and no dangerous fragments will be generated. Therefore, the bullet is safe.

[0026] The working process of a large-caliber machine gun fixed-range airburst round, mainly used for intercepting micro-sized UAVs, as described in this invention is as follows: The fixed-range airburst round is launched from the barrel. Recoil overload acts on the detonator seat 10, detonator casing 7, detonating charge 8, and shear pin 9, severing the shear pin 9. This causes the detonator seat 10, along with the detonator tube within it, to move backward relative to the ball seat 11 until the bottom surface of the detonator seat 10 contacts and is attracted to the upper surface of the washer 13, releasing the isolation ball 4 secured by the upper surface of the detonator seat 10 and disengaging its recoil safety. Subsequently, as the fixed-range airburst round accelerates within the barrel, its rotational speed gradually increases. At this point, due to the recoil overload and the resulting frictional torque, the opening ring 6 is pressed against the ball seat 11 and cannot open.

[0027] When the fixed-range airburst round is near the muzzle, the frictional torque generated by the recoil overload of the semi-ring of the open ring 6 is insufficient to overcome the centrifugal torque. The open ring will then open along its pre-fabricated weak point in the middle, retracting outwards and adhering to the inner cavity of the projectile body 12, releasing the isolation ball 4. However, due to the presence of recoil overload, the frictional torque generated by the isolation ball 4 and the flame detonator 5 inside pressing against the ball seat 11 will still hinder the rotation of the isolation ball 4 components until the fixed-range airburst round flies out of the muzzle and is close to the end of the aftereffect period. The recoil overload and the frictional torque generated thereby disappear or nearly disappear, and the isolation ball 4 will then turn upright under the action of the centrifugal torque. That is, the axes of the two flame detonators in the isolation ball 4 coincide or nearly coincide with the axis of the projectile. One flame detonator's input-output end faces upwards and is aligned with the central ignition port on the projectile body 12, while the other flame detonator's input-output end faces downwards and is aligned with the fuse detonation tube. At this time, the topmost part is the induction charging and geomagnetic signal detection speed and distance ignition control module 2, the middle part is the flame detonator 5, the bottom part is the explosive charge 8, and the bottom part is the explosive charge. The airburst bomb explosion sequence is activated and it is in the ready-to-ignite state after the safety is released.

[0028] When the pre-set ignition conditions are met, the induction charging and magnetometer rotation speed-based ignition control module 2 generates a flame output, which detonates the flame detonator 5 through the ignition port. The flame detonator 5 then detonates another flame detonator 5, rupturing the detonator casing 7 and detonating the detonating charge 8. The detonating charge 8 ruptures the bottom of the detonator base 10 and the reinforcing cap 14, subsequently detonating the explosive charge. The projectile body 12, the base 18, and other structural components are all shattered into fragments that scatter outwards, completing the predetermined detonation action of the airburst round. Since the ignition signal of the airburst round is generated by the induction charging and magnetometer rotation speed-based ignition control module 2, and the ignition action is completed inside the bullet, ballistic foreign objects will not affect the reliability of the airburst round's ignition.

[0029] In addition to its intended normal function, the fuse may function as follows in unforeseen circumstances:

[0030] If the shear pin 9 fails to disengage its safety mechanism, the detonator seat 10 and its internal detonator will not provide space for the isolating ball 4 to rotate, and the isolating ball 4 will not be released. Regardless of whether the open ring 6 is properly disengaged, the isolating ball 4 will remain in the assembled position. If the open ring 6 fails to disengage its safety mechanism, the isolating ball 4 will also remain in the assembled position. When the isolating ball 4 is in the assembled position and does not rotate, the flame detonator 5 remains in the explosion-proof state, and the detonation sequence cannot be aligned. The flame output generated by the normal ignition of the induction charging detection magnetometer rotation distance ignition control module 2 will ignite the flame detonator 5 in the assembled position through the ignition channel perpendicular to the axis of the flame detonator 5 on the isolating ball 4, i.e., the second central hole. At this time, the fuse loses its normal detonation function and enters an insulated state in the explosion-proof position. If the bullet does not disintegrate or break after landing, the induction charging detection magnetometer rotation distance ignition control module 2 will complete the predetermined electric ignition energy dissipation. If the bullet disintegrates or breaks, the explosive disposal hazard is essentially eliminated.

[0031] If both safety measures are disengaged, the isolation ball 4 rotates but does not turn to the correct position, resulting in structural misalignment and functional explosion-proof state. If the detonation sequence cannot be aligned, the flame output generated by the normal ignition of the induction charging detection geomagnetic signal meter rotation distance ignition control module 2 will ignite the flame detonator 5 through the gap between the isolation ball 4 and its chamber. At this time, the fuse loses its normal detonation function and enters an insulated state, ensuring the safety of explosive disposal.

[0032] If the isolation ball 4 rotates normally and the detonation sequence is aligned, but the induction charging detection magnetometer rotation distance ignition control module 2 fails to ignite or fails to detonate the flame detonator 5 after ignition, then upon landing, it may impact and ignite the bullet, or the bullet may disintegrate or shatter due to the impact. In short, the disposal of explosives after a fuse misfire is safe.

[0033] The projectile casing 1 of this invention is made of titanium alloy, which has high strength and low density, contributing to rotational stability and firing intensity design, without affecting the inductive charging and geomagnetic signal detection of the head firing control module. The cover plate 3 is made of nitrocellulose film, ensuring layered sealing of components without affecting the ignition transfer from the head firing control module to the central safety control and detonation module. The projectile body 12 is made of brass, with the cartridge belt integrated into the outer cylindrical surface of the projectile body 12, resulting in a simple structure that effectively improves the overall firing intensity of the bullet.

[0034] The foregoing has shown and described the basic principles, main features, main functions, basic structure, and advantages of the present invention. Various changes and modifications may be made to the present invention without departing from its spirit and scope, and all such changes and modifications fall within the scope of the claimed invention.

Claims

1. A large-caliber machine gun fixed-range airburst round primarily used for intercepting micro-sized unmanned aerial vehicles, characterized in that: The projectile includes a head ignition control module, a middle safety control and detonation module, a tail explosive loading module, and a projectile body (12). The projectile body (12) is the main structural component of the airburst projectile, with an arc-shaped front and a cylindrical rear profile. The three modules are arranged along the central axis of the projectile body (12) and are integrated with it. The head ignition control module includes a warhead casing (1), an induction charging and geomagnetic signal detection speed-distance ignition control module (2) and a cover plate (3) installed inside the warhead casing (1). The middle safety control and detonation module includes an isolation ball (4) and a flame detonator installed inside the isolation ball (4). (5) and ball seat (11) form a ball rotor explosion-proof and delayed release explosion-proof mechanism, and a magnetic anti-recovery recoil safety mechanism and explosion-proof sequence consisting of a detonation tube shell (7), a detonating explosive (8) installed in the detonation tube shell (7), a shear pin (9), a detonation tube seat (10), a ball seat (11) and a washer (13) made of a permanent magnet, and an isolation ball (4) formed by an open ring (6) as the main component, i.e., a centrifugal safety mechanism for the ball rotor; the tail explosive loading module includes a reinforcing cap (14), a sealing ring (15), an upper explosive loading (16), a lower explosive loading (17) and a projectile base (18), i.e., the warhead; Adopting the integrated design concept, the projectile body (12) is made of brass, and seven stepped holes are opened along the central axis of the projectile body (12) for assembly. The projectile belt is integrated on the outer cylindrical surface of the projectile body (12), that is, the projectile belt and the projectile body are structurally integrated, the structure is simple, and the overall launch strength of the projectile body can be effectively improved. The top of the outer contour of the warhead casing (1) is hemispherical, the lower half is cylindrical, and the middle is connected by an arc surface. There is an annular groove on the cylindrical surface. The inside of the warhead casing (1) is a stepped blind hole with the opening facing downward. The upper edge of the projectile body (12) is closed and inserted into the annular groove on the warhead casing (1). At the same time, the outer cylindrical surface of the warhead casing (1) is tightly fitted with the inner wall of the head of the projectile body (12). The upper half of the outer contour of the projectile body (12) is an arc surface, which is smoothly connected with the arc surface of the warhead casing (1), so that the outer contour of the front end of the airburst projectile is streamlined. The induction charging and detection of the geomagnetic signal clock rotation distance ignition control module (2) is assembled inside the warhead casing (1). The head ignition control module is separated from the middle safety control and detonation module by the cover plate (3). The head of the tail explosive loading module extends into the tail of the projectile body (12), and the two are fixedly connected. The head ignition control module, the ball rotor explosion-proof and delayed release explosion-proof mechanism, the centrifugal safety mechanism, and the magnetic anti-recovery recoil safety mechanism and detonation sequence work together to realize the air-explosive fuse function of the air-explosive projectile. The above mechanisms are arranged from top to bottom along the axis of the projectile body (12). Among them, the induction charging and geomagnetic signal detection speed-fixed distance ignition control module (2) is located above the projectile body (12) and realizes the ignition control function. The ball rotor explosion-proof and delayed release mechanism is mainly composed of the isolation ball (4), the flame detonator (5), the open ring (6), and the ball seat (11). The explosion-proof mechanism is located in the middle of the projectile (12), and the centrifugal safety mechanism of the ball rotor explosion-proof and delayed release explosion-proof mechanism is mainly composed of the open ring (6); the magnetic anti-recovery recoil safety mechanism and explosion-proof sequence composed of the detonation tube shell (7), detonation explosive (8), shear pin (9), detonation tube seat (10), ball seat (11), washer (13) and projectile base (18) made of ferromagnetic material are all located below the isolation ball (4); the space for the isolation ball (4) to accommodate and move is enclosed by the inner cavity of the projectile (12) and the upper ball socket of the ball seat (11); In the safety state, the flame detonator (5) is directly connected to the explosion relief cavity preset between the detonating tube and the reinforcing cap, and is separated from the explosion-propellant (8) below; five explosion relief grooves are evenly distributed on the outer circumference of the ball seat (11), the explosion relief grooves avoid the shear pin, the explosion relief grooves penetrate the upper and lower end faces of the ball seat (11) and are connected to the above-mentioned explosion relief cavity, and the cross-section of the explosion relief grooves is inverted T-shaped; the above-mentioned explosion relief grooves and the predetermined pressure relief cavity help to ensure the explosion-proof safety of the fuse and prevent the formation of a potential ignition channel when the detonator is accidentally ignited in the explosion-proof state, which may accidentally ignite or detonate the main charge.

2. A large-caliber machine gun fixed-range airburst round, mainly used for intercepting micro-sized unmanned aerial vehicles, as described in claim 1, is characterized in that: The warhead casing (1) is made of titanium alloy, which helps with the design of rotational stability and launch strength, and does not affect the inductive charging and detection of geomagnetic signals of the head firing control module; the cover plate (3) is made of energetic non-metallic material, which can ensure the sealing of the component layers and does not affect the transmission of fire from the head firing control module to the central safety control and detonation module.

3. A large-caliber machine gun fixed-range airburst round, mainly used for intercepting micro-sized unmanned aerial vehicles, as described in claim 2, is characterized in that: The material of the cover sheet (3) is nitrocellulose film.

4. A large-caliber machine gun fixed-range airburst round, mainly used for intercepting micro-sized unmanned aerial vehicles, as described in claim 1, characterized in that: The material of the projectile (12) is H62 brass.

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