17 results about "Sabot" patented technology

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 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 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.

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.

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 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.

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.

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.