62 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.

The invention discloses a two-stage separation type projectile support for sub-caliber launching of an unstable projectile body. The two-stage separation type projectile support comprises an outer projectile support body, a projectile tail structure, an inner projectile support body and the projectile body. The missile tail structure is driven to decelerate by using the backward opening resistance of the clamping petals, and the missile tail structure is separated from a flying missile body, so that the problem that the missile tail structure with larger mass cannot be separated can be solved; the inner sabot slides backwards along the axis of the projectile body under the action of air resistance in the flying process, so that the flying stability of a combination formed by the inner sabot and the projectile body is improved, target collision at a small attitude angle at a long distance can be achieved, and meanwhile, due to the fact that the flying distance is prolonged, the projectile tail structure and the projectile body are separated more thoroughly; through the arrangement of the resistance table, the inner projectile support can be separated from the projectile body before collision and can also impact the target body together with the projectile body; due to the fact that the inner projectile support can slide in the axial direction of the projectile body and is small in mass, the penetration influence of the inner projectile support on the projectile body can be ignored.

The invention belongs to the technical field of structural mechanics tests, and particularly relates to an engine blade high-temperature impact test device and method. The test device comprises a blade test piece, a test piece supporting unit, a heating unit, a gas gun loading unit, a high-speed camera and a control unit. According to the engine blade high-temperature impact test device, the designed heating unit can uniformly heat the blade test piece, and the highest temperature can reach 1050 DEG C; by means of the designed sabot and sabot separator, the small-diameter projectile can accurately impact a target position at a high speed; and the impact test requirements of fine fragments and particles such as engine blade coating droppings with the diameter within 4mm in a high-temperature environment are met.

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 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 high-speed cross-medium projectile body vertical water entry impact overload / load reduction response characteristic test device and method, belongs to the field of projectile body cross-medium high-speed flight impact tests, and aims to solve the problem of how to give consideration to reduction of impact load borne by a projectile body during cross-medium motion and reduction of self weight. The device comprises an underwater shock wave emitter, a projectile body, a test system and the like. The underwater shock wave generator is composed of a light-gas gun launching tube, a sabot flying plate, a piston, a dynamic pressure sensor and the like. The projectile body is divided into a buffer cap and a non-buffer cap; the test system is composed of a dynamic strain gauge, an axial acceleration sensor, a radial acceleration sensor, a three-dimensional DIC system and the like. According to the invention, different impact wave intensities in water are used for simulating conditions of vertical entry into water at different speeds, impact waves directly act on the front end face of the projectile body to realize impact loading on the projectile body, and the test system is used for realizing research on impact overload / load reduction response characteristics of the projectile body.

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.

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 utility model discloses a projectile launching device based on fuel gas driving, and relates to the technical field of projectile launching devices, the projectile launching device comprises a projectile enhancing cabin, a launching tube, a projectile support separator, a silencer and a laser speed measuring device which are sequentially arranged on a base, energetic materials are filled in a powder chamber of the projectile enhancing cabin, nitrocotton or standard charge is used as launching charge, and the laser speed measuring device is used for measuring the speed of the projectile support separator. The launch charge is ignited through the electronic ignition device, so that high-pressure gas is generated to drive the projectile body / sabot to fly out at a high speed along the launching tube with the caliber of 25 mm, the sabot and the projectile body are pneumatically separated through the sabot separator, the high-pressure gas is further silenced and shunted through the silencer, and the impact influence of the high-pressure gas on a target piece is reduced; and finally, the projectile body impacts the target after being subjected to speed measurement by the laser speed measurement system. The utility model has the advantages that the speed of the projectile body is continuously adjustable, the use and operation are simple, the raw materials are easy to obtain, the safety is controllable and the like; and meanwhile, the influence of high-pressure gas on the target piece can be effectively reduced by the silencer.

The present invention discloses a two-stage ultra-high-speed projectile sabot separation device, which includes a separation cylinder, an observation window I, an observation window II, two sets of support seats, and a support platform. The separation cylinder includes a muzzle section and a separation section. The observation window I is arranged on the muzzle section, and the observation window II is arranged on the separation section. The bottom ends of the two sets of support seats are fixedly connected to the support platform, and the top ends are connected to the separation cylinder. A partition plate I is arranged inside the separation cylinder, a central hole is arranged on the partition plate I, and an isolation sleeve I is arranged at the central hole. A clamping groove is arranged inside the separation section, and a partition plate II is arranged inside the clamping groove. In the present invention, by arranging the two-stage ultra-high-speed projectile sabot separation device at the tail of the secondary light gas gun launch tube, the problems that the existing system cannot both ensure the high-vacuum environment of the launch tube and the target chamber, and is convenient for the installation of magnetic velocity measurement and does not cause sabot pollution to the target chamber are effectively solved. The device can realize the stable separation of the projectile and the sabot, without causing damage to the projectile and without polluting the target chamber environment.

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 invention relates to the technical field of ultra-high-speed launching of light-gas guns, in particular to a pneumatic separation sabot which comprises at least two sub-sabot bodies, each sub-sabot body is provided with a sub-cover, all the sub-sabot bodies are circumferentially distributed around a preset axis to form a sabot body, and all the sub-covers define a sealed sabot cavity. The preset axis coincides with the central axis of the sealed elastic cavity; a wind resistance part is formed at the position, away from the central axis, of each sub-support. The inner wall of the sealed bullet cavity can tightly wrap and bear fragile bullets or particle swarms, the effect of fixing the bullets and the particle swarms is achieved, the situation that the bullets are disturbed and move relative to the bullet support to be broken is avoided, and the situation that the particle swarms are scattered in a launching tube is avoided. The wind resistance part is formed at the position, far away from the central axis, of each sub-support, after the projectile support flies out of the launching tube, the wind resistance parts generate radial separation force under the action of air resistance, and radial speed is generated under the action of the radial separation force, so that the projectile support is gradually separated from projectiles or particle swarms in the flying process.

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 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.

An assembly suitable for use in downhole operations including frac'ing. The assembly includes a sabot that includes an ignition stack, and a projectile partially received within the sabot, and the projectile includes an electrical contact in electrical communication with the ignition stack. The assembly may be received in a dispensing device that includes a propellant chamber and a barrel, and the assembly may be positioned in the dispensing device so that the ignition stack extends partway into the propellant chamber.

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.

A sabot separating structure comprises a blocking cylinder, a sealing cylinder and a supporting assembly. The blocking barrel is connected to the end of the gun barrel, two symmetrically-arranged blocking blocks are arranged on the inner wall of the blocking barrel in the circumferential direction, and the blocking blocks are connected with the blocking barrel through shear pins. The sealing cylinder is matched in the gun barrel and is movably arranged in the axis direction of the gun barrel, a projectile body is arranged at the end, away from the bottom of the gun barrel, of the sealing cylinder, during application, the sealing cylinder enters the stopping cylinder, the end of the sealing cylinder abuts against the stopping block, the shear pin is cut off, and the projectile body is separated from the sealing cylinder; the supporting assembly comprises two supporting modules which are symmetrically arranged and connected to the end of the sealing cylinder, the supporting modules are located in the blocking cylinder, the supporting modules and the blocking blocks are arranged in a staggered mode at intervals, the supporting modules comprise a plurality of supporting rings arranged in the axis direction of the blocking cylinder at intervals, the supporting rings are arc-shaped, the angle between the two ends of each supporting ring is smaller than 180 degrees, and the supporting modules are used for limiting the peripheral side of the projectile body. The device not only can realize quick separation of the sabot, but also can reduce the additional mass of the sabot and reduce the influence on a projectile body during separation.

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 utility model discloses a damage prevention structure of a sleeve connecting piece of an electric anastomat, the electric anastomat comprises a cutting anastomosis assembly, a gun body and a first connecting rod connected with the cutting anastomosis assembly and the gun body, and the gun body is provided with an operating mechanism used for opening a jaw of the cutting anastomosis assembly. A disc body which can rotate around the axis of the disc body and is in meshing transmission with the operating mechanism is installed in the gun body, a plurality of gear teeth for meshing are arranged on the circumferential portion of the disc body, a second connecting rod is connected to the disc face of the disc body in a sliding mode, and the first connecting rod is sleeved with a sleeve connecting piece. The first end of the second connecting rod is correspondingly connected with the sleeve connecting piece, the second end of the second connecting rod is rotationally connected with the disc body, when large resistance is encountered, the force can be absorbed through elastic deformation of the elastic arm on the gear, and therefore the situation that the rack is damaged due to stress torsion of the sleeve connecting piece is avoided.

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 a device for ejecting steel balls and archery. The device comprises a sabot, an excitation device, a gun barrel, a bow head, a rubber band, a sight and a grip. The bow head is installed at the front end of the gun barrel, the sight is installed at the tail end of the gun barrel, one end of the rubber band is installed on the bow head, the other end of the rubber band is installed on the bullet support, the bullet support is hung on the excitation device and locked, the bow head is provided with a circular bow door, the excitation device is provided with a bullet support limiting module, and the position and the moving direction of the bullet support are determined through the bullet support limiting module. The center lines of the pantograph head, the bullet support and the bullet support limiting module coincide and are parallel to the center line of the gun barrel. The equipment for ejecting the steel balls and archery is high in power, long in firing range and high in precision, and is suitable for shooting competitions, outdoor sports and slingshot playing and archery activities during leisure and entertainment.

The invention relates to the technical field of ultra-high-speed launching of light-gas guns, in particular to a sabot structure which comprises a sabot body, a gas generating device and a triggering device, a sabot groove is formed in the sabot body, the sabot body comprises at least two sub-supports, the sub-supports are annularly distributed around a preset axis, and the preset axis is the central axis of the sabot groove; the gas generating device is arranged on the side, close to the preset axis, of the sub-support. The triggering device is connected with the gas generating device and used for triggering the gas generating device to generate gas to push the sub-support to be away from the preset axis. The gas generating device can be triggered through the triggering device to generate gas, so that the sub-support is pushed by air pressure to be transversely away from the central axis, and active separation between the sub-support and the projectile is achieved. And the projectile and sabot separation effect is greatly improved while the influence on the projectile state is avoided, and projectile and sabot separation under the higher speed condition is achieved.

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 present provides a munition comprising a projectile (7) and an at least two-segment sabot (1) having an ogive (2) incorporated on the sabot.

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.

The invention discloses a design and manufacturing scheme of a composite lightweight sabot. The composite lightweight sabot comprises a shell 1, a mandrel 2, a structural adhesive 3 and a core material 4. The shell 1 is made of chopped carbon fiber reinforced engineering plastics, and in order to further reduce the weight, the shell 1 structurally adopts a hollow design and is filled with the core material 4 to supplement the strength. The mandrel is formed by high-modulus carbon fiber mold pressing or multi-axis continuous fiber 3D printing, and the overall deformation is smaller than 0.3 mm under the control emission condition. The shell 1 and the mandrel 2 are connected in a meshed mode, and in order to improve the stability, the shell 1 and the mandrel 2 are connected in a glued mode. The light weight design requirement is met, and the weight is reduced by at least 3.6 Kg compared with the whole set of cast aluminum structure. The high-strength and high-modulus carbon fiber material is adopted as a whole, the structural strength is better than that of aluminum alloy, and under the condition that the chamber pressure is certain, the launching speed, the firing range and the penetrating blasting capacity of the projectile can be remarkably increased.

The utility model discloses an armor-piercing bullet support structure, which comprises a plurality of support petals and a plurality of metal plates, the support petals are made of carbon fiber composite materials and are arranged in an arc shape, the plurality of support petals are combined in an annular shape, and the metal plates are bonded on two sides of each support petals. And ring grooves which are communicated with each other are formed in the inner sides of the supporting petals and the metal plates. The sabot has the advantages that the sabot structure is jointly formed by arranging the sabot petals made of the carbon fiber composite materials and matching the sabot petals with the metal plates, the structural strength and torsional rigidity of the sabot can be guaranteed, the weight of the sabot can be reduced, light weight of the sabot is achieved, and meanwhile good compression strength is kept.