31 results about "Sabot" patented technology

A sabot assembly includes a housing defining an interior space and a plurality of projectiles and received in the interior space. The interior space is at least partially defined by a plurality of concavities, each of which is configured to receive a respective projectile. The housing is configured to separate and fall away once the sabot assembly is fired through a gun barrel, thereby releasing the projectiles from the interior space toward a target prior to impact of the sabot assembly with the target.

A sabot assembly 20 includes a housing defining an interior space 30 and a plurality of projectiles 24 and received in the interior space 30. The interior space 30 is at least partially defined by a plurality of concavities 38, each of which is configured to receive a respective projectile 24. The housing 22 is configured to separate and fall away once the sabot assembly 20 is fired through a gun barrel 4, thereby releasing the projectiles 24 from the interior space 30 toward a target prior to impact of the sabot assembly 20 with the target.

A representative reverse-saboted sidearm system includes: a sidearm having a barrel assembly with an inner wall defining a longitudinally extending bore; and a round of reverse-saboted ammunition having a non-necked casing, a reverse sabot, and a projectile, the reverse sabot mounted at a discharge end of the casing with a distal end of the reverse sabot extending outwardly from the casing, the reverse sabot exhibiting a diameter corresponding to a diameter of the casing and defining a receiving passage aligned with a longitudinal centerline of the casing, the projectile being at least partially disposed within the receiving passage of the reverse sabot; the inner wall of the barrel assembly being configured to engage an exterior surface of the projectile to direct the projectile.

The invention belongs to the technical field of electromagnetic emission, and particularly relates to a bird body emission and separation device applied to a multistage electromagnetic coil. According to the technical scheme, the bird body launching and separating device applied to the multi-stage electromagnetic coil comprises an acceleration part gun barrel, a braking part gun barrel, a speed buffering part gun barrel, an impact-buffering structure and a magnetic induction cartridge case, and the acceleration part gun barrel, the braking part gun barrel and the speed buffering part gun barrel are sequentially connected together through flanges to form an integral gun barrel; the impact-buffering structure is installed at the end of the gun barrel of the speed buffering part, and the bird body is installed in the magnetic induction cartridge case and is launched and separated through the whole gun barrel. According to the bird body launching and separating device applied to the multistage electromagnetic coil, high-speed stable launching of the bird body can be achieved, and the bird body is safely separated from the sabot.

This invention relates to a projectile ejection device suitable for high-speed impact experiments with rod-shaped projectiles, comprising a sabot system and an ejection system. The sabot system is used to mount the rod-shaped projectile and allow it to be positioned along the axial direction of the gun barrel. The ejection system includes a collection bucket, a buffer pad, and an interceptor. The end of the collection bucket away from the sabot system has a baffle with a first through hole in its center. The buffer pad is disposed inside the collection bucket and abuts against the baffle, and has a second through hole. The first and second through holes are coaxially aligned and continuous. One end of the interceptor is embedded in the second and first through holes, and the other end has at least two spaced buffer layers along its axial direction. The interceptor has a through-channel for the rod-shaped projectile to pass through. This design allows the sabot system to completely separate from the rod-shaped projectile without affecting its original flight attitude, ensuring the projectile is ideally isolated when passing through the magnetic velocity measurement test area and impacting the target.

The present disclosure provides a fin stabilized projectile which can accommodate subsonic and supersonic flight velocities, wherein flight performance characteristics of the projectile are stabilized. The projectile is configured to be incorporated into a sabot free cartridge, wherein the projectile can be launched from a smooth bore barrel. The projectile includes an elongate body having a diverging ogival nose section extending rearward from a leading end, a converging ogival back section terminating at a trailing end; and a tail segment having a tail fin projecting radially from the back section and extending longitudinally forward of the trailing end of the elongate body and extending longitudinally rearward of the trailing end of the elongate body.

A sabot that includes a body configured to be partly received within a propellant chamber of a perf gun, and the body includes an interface configured to engage a projectile, a divider that defines part of the interface, an ignition pass through that extends through the divider, an ignition stack electrically connected to the ignition pass through, a ground terminal electrically connected to the ignition pass through, a deflector defined by the divider and having a cup-shaped configuration, and the deflector is configured to expand diametrically upon ignition of a propellant in the propellant chamber when the sabot is positioned within the propellant chamber, a gas valve configured and arranged to be actuated by expansion of the deflector, and a compensator positioned between the interface and the gas valve.

The invention discloses a universal anti-unmanned aerial vehicle bullet for rifles and machine guns, and relates to the technical field of ammunition, a bullet body is arranged at the front part of a bullet shell, a cavity is formed in the bullet body, a cup-shaped bullet support is placed in the cavity of the bullet body, a plurality of scattered bullet particles are assembled on the cup-shaped bullet support, and the scattered bullet particles are mutually connected through silk threads; a gunpowder chamber is arranged at the rear part of the cup-shaped sabot, front gunpowder and a fire transfer agent are filled in the gunpowder chamber, and the side part of the fire transfer agent is filled with an ignition agent; the cartridge case is filled with rear gunpowder, one side of the rear gunpowder is in contact with the ignition agent, and the other side of the rear gunpowder is in contact with the primer filled at the rear end of the cartridge case. After the rear gunpowder filled in the cartridge case is ignited by the primer at the rear end, the ignition agent is ignited by the rear gunpowder, and the front gunpowder is ignited by the ignition agent, so that pushing force is provided for the cup-shaped sabot, the scattered bullet particles which are connected through the silk threads in the cup-shaped sabot are launched out, a scattered net-shaped attack surface is formed, and the flying wings of the unmanned aerial vehicle are caught and wound. Compared with the prior art, the invention has the following advantages: the range is increased; the hit rate is improved; the adaptability is high.

A reduced energy marking cartridge includes a casing supporting a sabot for relative sliding movement and defining a combustion chamber at the breech end of the cartridge and a vent chamber at the muzzle end of the cartridge. An assembly of seals and radial venting passages in the sabot, which may be in the form of notches, slots or holes, cooperate during the relative movement of the casing and sabot to provide a valving mechanism for controlling the flow of combustion gas from the combustion chamber through the venting chamber and into the acceleration chamber for propelling a projectile from the cartridge.

The invention relates to a device (1) forming a rear guidance interface for ammunition, which ammunition comprises a projectile surrounded by a sabot having at least one rear support bearing (52), the device (1) comprising a linking element (2) and a contact interface element (3, 4), the linking element (2) comprising a fixing part (20) adapted to be fixed to the rear support bearing (52), a clamping part (21) and a guiding part (22), and the contact interface element (3, 4) comprising a pad-forming member (3) movably mounted, with guidance by the guiding part (22), relative to the linking element (2) between a retracted position and a protruding position in which the pad-forming member (3) protrudes at least partially out of the linking element (2) from the clamping part (21) and is adapted to be located at a diameter greater than that of the weapon tube (11),and a actuating element (4) of the sliding element (3) towards its projecting position. The present invention also relates to a munition comprising such devices (1). Figure to be published with the abbreviation: Fig. 6.

The invention relates to the technical field of impact testing, and discloses a launching module, a testing system and a testing method.The launching module comprises a launching device, a sabot and an annular gear piece, the launching device comprises a driver, a supporting base and a gun barrel, the gun barrel is arranged on the supporting base, and the driver is connected to the gun barrel; the projectile support is detachably installed in the gun barrel and comprises a base and a plurality of clamping pieces, all the clamping pieces are connected to the base, and a clamping space used for containing a projectile body is formed among the multiple clamping pieces; at least one clamping piece is movably connected to the base so as to adjust the size of the clamping space; the annular gear piece is arranged at the launching end of the gun barrel, and an inner ring of the annular gear piece is opposite to a launching opening of the gun barrel; wherein the driver is used for driving the projectile support to move towards the annular gear piece, the annular gear piece is used for blocking the projectile support, and an inner ring of the gear piece is used for ejecting projectile bodies, so that the test requirement that the projectile bodies in different shapes impact an object to be tested can be met.

The invention relates to the technical field of ballistic trajectory testing, and discloses a light sabot and ballistic trajectory stabilizing device suitable for a light-gas gun system, the light sabot and ballistic trajectory stabilizing device comprises a sabot, the sabot is of a split structure wrapping the bottom of a projectile body, and a plurality of spiral gas guide grooves are formed in the outer circumferential surface of the sabot; the magnetic attraction stabilizing assembly comprises a radial magnetic attraction piece embedded into the inner wall of the projectile support and a magnetic ring arranged at the bottom of the projectile body; the auxiliary falling-off assembly comprises an annular guide plate located on one side of the outlet end of the gun barrel, a cutting edge is arranged between the annular guide plate and the outlet end of the gun barrel, and an inclined face located behind the cutting edge is arranged on the annular guide plate; micro-clearance fit and lightweight design enable the abrasion loss of the gun barrel to be reduced and the service life of equipment to be prolonged; under the dual effects of magnetic attraction fixing and pneumatic stability of the spiral groove, disturbance in the chamber is effectively restrained, and trajectory deviation is reduced; the auxiliary falling-off assembly achieves forced falling off of the sabot, and the sectioning fragments deviate from the target area angle, so that it is ensured that the projectile body flies to the target plate without interference.

The invention relates to a device (1) forming a rear guidance interface for ammunition, which ammunition comprises a projectile surrounded by a sabot having at least one rear support bearing (52), the device (1) comprising a linking element (2) and a contact interface element (3, 4), the linking element (2) comprising a fixing part (20) adapted to be fixed to the rear support bearing (52), a clamping part (21) and a guiding part (22), and the contact interface element (3, 4) comprising a pad-forming member (3) mounted movably, with guidance by the guiding part (22), relative to the linking element (2) between a retracted position and a protruding position in which the pad-forming member (3) protrudes at least partially out of the linking element (2) from the clamping part (21) and is adapted to be located at a diameter greater than that of the weapon tube (11),and a actuating element (4) of the sliding element (3) towards its projecting position. The present invention also relates to a munition comprising such devices (1). Figure to be published with the abbreviation: Fig. 6.

A reduced energy marking cartridge includes a casing supporting a sabot for relative sliding movement and defining a combustion chamber at the breech end of the cartridge and a vent chamber at the muzzle end of the cartridge. An assembly of seals and venting passages in the sabot, which may be in the form of notches, slots or holes, cooperate during the relative movement of the casing and sabot to provide a valving mechanism for controlling the flow of combustion gas from the combustion chamber through the venting chamber and into the acceleration chamber for propelling a projectile from the cartridge.

The present invention discloses an underwater high-speed projectile configuration device based on electromagnetic coil ejection, comprising a sabot, an armature, a base support, a supporting iron sheet, a tail, and a warhead, to address the technical issues of underwater electromagnetic coil launch testing. The present invention utilizes sub-caliber launch technology, with a supercavitating projectile consisting of a tungsten warhead and an aluminum tail threaded together as the sub-caliber core, secured within the electromagnetic projectile by a nylon sabot and a base support. The electromagnetic projectile shell is formed by a nylon sabot and an aluminum armature threaded together, with an outer diameter matching the inner diameter of the launcher. The base support, mounted at the bottom of the armature, also serves to accelerate the sub-caliber core. The underwater high-speed projectile configuration of the present invention not only meets the launch requirements of underwater multi-stage electromagnetic induction coil guns, but also achieves supercavitating drag reduction during the projectile's navigation process in the water, thereby increasing the initial velocity and range of underwater launches.

A reduced energy marking cartridge includes a casing supporting a sabot for relative sliding movement and defining a combustion chamber at the breech end of the cartridge and a vent chamber at the muzzle end of the cartridge. An assembly of seals and radial venting passages in the sabot, which may be in the form of notches, slots or holes, cooperate during the relative movement of the casing and sabot to provide a valving mechanism for controlling the flow of combustion gas from the combustion chamber through the venting chamber and into the acceleration chamber for propelling a projectile from the cartridge.

The invention relates to a patrol bomb ejection device based on methane, air and fuel gas and capable of repeatedly utilizing a high-pressure chamber and a low-pressure chamber. Comprising a launch canister outer canister, a spiral guide rod, a launch canister base, a launch canister support, a launch canister end cover and a high-pressure chamber. The launch canister end cover comprises an inner connecting ring and an outer connecting ring which are provided with partial protruding threads, the launch canister end cover is connected with the high-pressure chamber through the inner connecting ring and connected with the launch canister outer barrel through the outer connecting ring, the outer end face of the launch canister end cover is connected with the launch canister base through a spiral guide rod, and the inner side wall of the launch canister outer barrel is provided with a protrusion for limiting a bullet support. The high-pressure chamber is filled with methane-air fuel gas, a throat part is arranged on the side, facing the sabot, of the high-pressure chamber, a replaceable gas film assembly is arranged at the end of the high-pressure chamber, and a low-pressure chamber is formed among the high-pressure chamber, the outer barrel of the launching barrel and the sabot. The device is wide in application range and high in safety coefficient; the high-voltage chamber can be reused; the launching efficiency in the launching process is improved; the patrol bomb can pop out of the launch canister at a higher speed.

A corrugated deforming sabot system for carrying a payload down a tapered barrel is provided. The corrugated deforming sabot includes a body for encasing the payload and at least one flange area including a deformable corrugated section surrounding the body. The deforming sabot may further include structural elements that reinforce the corrugated section and transfer compressive forces of the tapered barrel on the corrugated section into grip of the body on the payload. The deforming sabot may further include compressive areas that deform in a manner that prevents elongation of the corrugated section when compressed by the tapered barrel. According to an embodiment, the corrugated deforming sabot includes a flange area comprising deformable corrugated sabot wings that deform to form an airfoil when compressed by the tapered barrel. Various tapered barrel configurations are also provided.

A cartridge is disclosed with a casing and a projectile, wherein external ballistic stability is provided by a center of pressure of the projectile being rearward of a center of mass of the projectile. The projectile includes flight control surfaces that cooperate with the bore of a barrel without requiring rifling or sabots. The projectile can include fin configurations that cooperate with the bore to form a bearing surface with the bore.

The invention provides an anti-turbulent-flow unshelling and armor-piercing projectile support clamping flap aerodynamic configuration design method which comprises the steps that a helicopter platform composite flow field model is constructed, and the speed of a single clamping flap relative to helicopter composite airflow is obtained; simulating and calculating the in-air motion trail of the clamping flap of the shelling and armor-piercing bullet in the helicopter composite flow field; the lift coefficient, the resistance coefficient and the overturning torque coefficient of the clamping flap at different attack angles and speeds are substituted into the air movement track of the clamping flap of the shelling and armor-piercing bullet in the helicopter composite flow field, simulation calculation of the clamping flap trajectory is carried out, and then Monte Carlo simulation is carried out to generate a plurality of different clamping flap movement tracks; setting an objective function meeting a safe distance and carrying out iteration to obtain an optimal aerodynamic coefficient combination; the purpose of optimizing the aerodynamic characteristics of the clamping valve is achieved by modifying the geometric shape parameters of the clamping valve model and adjusting the aerodynamic coefficients of the clamping valve at different attack angles and speeds. The safety problem that the clamping petals collide with the platform due to the influence of complex turbulent flow can be solved.

The application discloses a low-speed near-blast electronic detonation module sliding projectile rope driving and intercepting device, which comprises a test tower and a steel cable, one end of the steel cable is fixed to the top end of the test tower, and the other end of the steel cable is fixed to a ground fixed point; a trolley for simulating a projectile body is arranged on the steel cable, an adjustable-angle near-blast electronic detonation module is arranged on the trolley, the angle of the near-blast electronic detonation module relative to the trolley is adjusted to simulate different attack angles of the projectile body; an elastic rope is arranged below the steel cable, the elastic rope is connected with the trolley, and the elastic rope is in a stretching state during the whole sliding process of the trolley on the steel cable; a blocking cable mechanism is arranged at the lower end of the steel cable and used for stopping the trolley; ground effect objects required by the test are arranged on the ground below the steel cable, and data acquisition equipment is arranged on the ground. The application can realize lossless recovery of the electronic detonation module, adopts a non-explosive propelling mode, greatly improves operation efficiency and ensures test safety.

The utility model discloses a production device for a bullet support of an armor-piercing bullet, which comprises a winding shaft, the winding shaft comprises a core shaft and three shaping blocks, the shaping blocks are arranged around the core shaft, the outer wall of each shaping block is arc-shaped, and the surface of each shaping block is equidistantly provided with shaping grooves penetrating through the two sides of the shaping block; the compaction blocks are arranged on the outer sides of the shaping blocks and used for pressing the wound carbon fiber filaments into the shaping grooves in the surface of the winding shaft; the hot pressing die comprises an upper die and a lower die, and the sides, close to each other, of the upper die and the lower die are provided with semicircular die cavities which are buckled with each other. According to the utility model, the winding shaft, the compaction block and the hot-pressing mold are matched, so that the carbon fiber yarns can be wound on the winding shaft, then the compaction block is adopted to compact the carbon fiber yarns, and finally the hot-pressing mold is adopted to perform hot-pressing molding, so that three sabot clamping petals can be produced at one time each time, and the three sabot clamping petals can form a complete sabot; therefore, one-time production and machining of the sabot are achieved, and the production efficiency is improved.

The invention relates to a projectile (10), comprising a core (12) having a terminal ballistic effect and extending along a projectile axis (11), a sabot base (16), and a sabot casing (18), wherein the sabot base (16) has an opening (20) in which a first portion (22) of the core (12) is accommodated, wherein the sabot casing (18) can be coupled or is coupled to the sabot base (16) and, in the coupled state, surrounds the core (12) and the sabot base (16), wherein the sabot base (16) has a plurality of retaining arms (26) which are distributed along its circumferential direction, are separated from one another by slots (24), as a whole define the opening (20) and overlap the first portion (22) of the core (12), wherein the sabot casing (18) has a passage (28) with an inner wall, wherein, in the coupled state, a wall portion (30) of the inner wall bears against an outer side of the retaining arms (26) in such a way that the retaining arms (26) are pressed inwards against the first portion (22) of the core (12) and retain the core (12) in the opening (20).

The invention provides an experimental device and an experimental method for simulating fragment penetration of a protective structure, and the experimental device comprises a target cabin, the side wall of which is provided with an incidence hole; the target plate is vertically arranged in the target cabin; the air cannon is arranged on one side of the target cabin, and an outlet of the air cannon is opposite to the incidence hole; the sabot assembly comprises a sabot and a projectile, the sabot comprises an upper section and a lower section which are buckled with each other, and the upper section and the lower section are connected through a first connecting piece; the fusing device is arranged in the target cabin; the control device, the fusing device and the air cannon are in electric control connection with the control device, and under the condition that the sabot moves to the preset position, the fusing device fuses the first connecting piece so that the sabot can be switched from the bearing state of bearing the projectile to the separation state of being separated from the projectile. According to the technical scheme, the laboratory safety problem caused by unstable sabot separation and too late separation when the high-temperature and high-speed space debris penetration protection structure is simulated in the prior art can be effectively solved.

The presently disclosed ammunition is designed around a fared, monolithic discarding sabot that does not come apart during or after exiting the barrel and a single subcaliber flechette borne within. Because the monolithic sabot stays intact, it passes through baffles, diaphragms, wipers, and other components within a suppressor or beyond a gun barrel like a muzzle brake without damaging them or disturbing the trajectory of the flechette. The ammunition is also designed to eject the aeromechanically stable flechette following barrel exit with a set of subscale suppressor components within the sabot itself enhancing ejection, reducing tip-off disturbances, tightening circular errors probable and further suppressing acoustic signatures.

The invention relates to a device (1) forming a rear guide interface for a munition, which munition comprises a projectile surrounded by a sabot comprising at least one rear bearing surface (52), the device (1) comprising a connecting element (2) and a contact interface element (3, 4), the connecting element (2) comprising a fastening part (20) able to be fastened to the rear bearing surface (52), a clamping part (21) and a guide part (22), and the contact interface element (3, 4) comprising a pad-forming member (3) mounted such that it is able to move, guided by the guide part (22), with respect to the connecting element (2) between an effaced position and a protruding position in which the pad-forming member (3) protrudes at least partially out of the connecting element (2) from the clamping part (21) and is able to be situated at a diameter greater than that of the weapon tube (11), and a biasing member (4) urging the pad-forming member (3) towards its protruding position. The present invention also relates to a munition comprising such devices (1).

A representative saboted firearm system includes: a firearm having a barrel assembly with an inner wall defining a longitudinally extending bore; and a round of saboted ammunition having a casing, propellant, a sabot, and a projectile, the casing extending from a striking end to a discharge end, the casing defining an interior, the discharge end having an aperture defining an opening, the opening communicating with the interior, the propellant being disposed within the interior, the sabot mounted at a discharge end of the casing, the sabot defining a receiving passage aligned with a longitudinal centerline of the casing, the projectile being at least partially disposed within the receiving passage of the reverse sabot; the inner wall of the barrel assembly being configured to engage an exterior surface of the projectile to direct the projectile.

This invention relates to a sabot for testing 105mm smoothbore guns, comprising a sabot shell, a projectile inserted inside the shell, a gas-sealing ring threaded to the bottom of the shell, an end cap screwed to the end of the gas-sealing ring away from the shell, a support plate snapped onto the end of the shell near the gas-sealing ring, and a limiting ring snapped onto the end of the projectile near the support plate. This invention uses a tapered nylon limiting ring to ensure complete contact between the projectile base and the bottom of the sabot shell. The thickness of the support plate is adjustable to meet firing intensity requirements, reducing the overall mass of the projectile. The gas-sealing ring has a protrusion in the middle with the same diameter as the support plate, which can press the support plate firmly. The tail of the gas-sealing ring has a variable width at its maximum diameter to adapt to firing sealing requirements under different overloads. The end cap fixed to the tail of the gas-sealing ring increases firing sealing and improves firing reliability. A slit is cut at 20-degree intervals at the connection between the gas-sealing ring and the sabot shell to facilitate better separation of the sabot shell after exiting the muzzle.

This invention belongs to the field of impact dynamics, specifically relating to a two-stage pneumatic sabotage device with an eccentrically arranged parallel axis. It includes a connecting section that connects to the gun barrel, and this connecting section is connected to one end of the sabot recovery chamber body via a sealing device. The sabotage recovery chamber body houses a sabotage mechanism. The sabotage mechanism includes a primary sabotage baffle and a secondary sabotage baffle arranged along the ballistic axis. The circular hole in the center of the primary sabotage baffle is eccentrically positioned, so that after the shock wave is reflected from the inner wall of the primary sabotage baffle, it only exerts force and torque on the sabot, while the projectile is not subjected to force or torque, thus maintaining the projectile's attitude while causing the sabot to deviate. After sabotage removal via the eccentrically arranged secondary baffle sabotage device of this invention, complete sabotage removal is achieved, with no residual sabotage impacting the target. The sabotage device of this invention has minimal impact on the projectile's flight attitude and does not affect the test results.

A sabot that includes a body configured to be partly received within a propellant chamber of a perf gun, and the body includes an interface configured to engage a projectile, a divider that defines part of the interface, an ignition pass through that extends through the divider, an ignition stack electrically connected to the ignition pass through, a ground terminal electrically connected to the ignition pass through, a deflector defined by the divider and having a cup-shaped configuration, and the deflector is configured to expand diametrically upon ignition of a propellant in the propellant chamber when the sabot is positioned within the propellant chamber, a gas valve configured and arranged to be actuated by expansion of the deflector, and a compensator positioned between the interface and the gas valve.