511results about "Projectiles" patented technology

A stabilizer for an aerial projectile comprises a conical portion with a first longitudinal axis, a first end of a lesser diameter, and a second end of a greater diameter. A tubular portion having a second longitudinal axis is coaxially conjoined at the first end of the conical portion. An external surface of the conical portion is engrailed or invected by a radial succession of flutes alternating with a radial succession of splines. For invected surfaces, at least a portion of any one flute from among the radial succession of flutes may comprise a planar surface. The surfaces of the flutes and splines may be longitudinally straight or may be helical surfaces. The stabilizer may be made of plastic and a portion of the plastic may be a recycled plastic material.

A polymer capsule jacketed projectile includes a preformed core enclosed by a nose capsule and a base capsule. The preformed core has an ogive region tapering into a core nose that is connected to a core base by the bearing surface. The nose capsule engages the base capsule around the bearing surface at a jacket joint to form the polymer capsule jacket. The outer surface of the polymer capsule jacket may be seamless, having no visible edges or protrusions, or a cannelure may be formed in the outer surface at the location of the jacket joint. The nose capsule and the base capsule are dip molded and the preformed core is pressed into engagement with both capsule pieces to form the polymer capsule jacketed projectile.

The invention discloses an unmanned aerial vehicle catching gun grenade, and relates to the technical field of unmanned aerial vehicle defense. The gun grenade comprises an air cap, a heavy hammer part sleeve, a catching net, a net expanding exploder and a cartridge case. The heavy hammer part sleeve is formed by combining a plurality of split heavy hammer blocks, and the rear end of the heavy hammer part sleeve is hooped by a brittle constraint ring. The net expanding exploder comprises a delay ignition unit and an explosion initiation unit. After launching, the delay ignition unit triggers the detonation unit after delaying a preset time to generate impact to crush the brittle constraint ring, so that the heavy hammer block carries the catching net to be scattered and unfolded at a high speed, and interception is realized. The device is compact in structure, low in cost and high in reliability, can be launched through a gun grenade launcher, is particularly suitable for being carried and used by an individual soldier, and can effectively cope with the threat of a small-sized high-speed unmanned aerial vehicle.

In a MEFP warhead detonation of the main charge is controlled to provide elevated pressure at multiple locations on the back surface of the liner to cut the liner and to form and propel forward a plurality of EFPs. An initiation system is configured for multi-point initiation of a plurality of booster charges to detonate the main charge to produce a plurality of detonation waves that constructively interfere at multiple locations on the back surface of the liner to form pressure hot spots that cut the liner and to form and propel forward a plurality of EFPs. In different embodiments, the elevated pressures are between 110% and 200% of the detonation pressure at the front of an individual detonation wave. The liner may, for example, be a flat plate or a include a plurality of dimples in which case the boosters are aligned to the center of the dimples.

In a MSCJ warhead detonation of the main charge is controlled to provide elevated pressure at multiple locations on the back surface of the liner to cut the liner and to form and propel forward a plurality of SCJs. An initiation system is configured for multi-point initiation of a plurality of booster charges to detonate the main charge to produce a plurality of detonation waves that constructively interfere at multiple locations on the back surface of the liner to form pressure hot spots that cut the liner and to form and propel forward a plurality of SCJs. In different embodiments, the elevated pressures are between 110% and 200% of the detonation pressure at the front of an individual detonation wave. The liner may, for example, include a plurality of recesses such as shallow dimples or deeper conical structures in which case the boosters are aligned to the center of the recessed structures.

An assembly for use as a net-launching projectile is disclosed. The assembly comprises a housing storing a net in a packed configuration and configured such that a rotation of the assembly causes the net to be ejected from the housing, thereby unpacking the net into an expanded configuration. The assembly also comprises a plurality of circumferentially disposed protrusions or ridges for engaging with corresponding rifling in a barrel to induce the rotation of the assembly when launched. Also disclosed is a net-launching system and a method of capturing an aerial target.

A guided vehicle that includes a body, a propulsion system operably engaged inside of the body, a housing operably engaged with the body and encasing a guidance device inside of the housing, a viewing window of the guidance device, and a cover moveably engaged with the housing, wherein the cover is moveable between a pre-flight configuration and a flight configuration. In the pre-flight configuration, the cover covers the viewing window. In the flight configuration, the cover is configured to expose the viewing window in the flight configuration in response to an impulse of acceleration generated by a launch of the guided vehicle.

The present invention relates to a range extension device, particularly to a reversible range extension device, especially reversible base bleed device.There is provided a reversible range extension device, capable in use, of being reversibly engaged to a body of an artillery shell, said range extension device comprising at least one energetic material, and an igniter, wherein the range extension device comprises a first end with an aperture, and second closed end, wherein the range extension device, in use, is selectively arranged to be in an active orientation or inert orientation, wherein in the active orientation the range extension device is arranged such that the aperture faces rearwardly away from the shell to allow the range extension device to function, and in the inert orientation the range extension device is arranged such that the aperture faces inwardly towards the shell.

A payload container includes a nose cone electronics hub assembly, a collar assembly, a canister assembly, and a grid fin system. The nose cone electronics hub assembly has a nose cone housing electronic components in support of flight and detonator systems. The collar assembly includes a collar coupling the nose cone electronics hub and canister together. A canister of the canister assembly houses separate parts when in a shipping configuration that can be attached to an exterior of the payload container in a deployment configuration. A fin assembly facilitates vertical descent of the payload container when dropped from an unmanned aircraft.

The invention discloses a dynamic pressure-based carrier rocket grid rudder control method, which comprises the following steps of: according to a pre-launch binding wind field and the speed of a carrier rocket at the current moment, calculating to obtain the relative airflow speed of the carrier rocket at the current moment; according to the current relative airflow velocity of the carrier rocket, calculating to obtain a current dynamic pressure estimated value; according to the dynamic pressure estimation value at the current moment, solving a control law parameter in the grid rudder online variable gain control law to obtain an optimal control law parameter at the current moment; according to the optimal control law parameters at the current moment, a grid rudder swing angle control instruction at the current moment is obtained through calculation, and real-time control over the grid rudder of the carrier rocket is completed. The method can effectively adapt to the rapid change pneumatic environment of the reentry flight section, remarkably reduces the flight deviation, is suitable for various carrier rocket reentry recovery scenes, and has the advantages of being high in engineering practicability, high in control efficiency and the like.

The anti-unmanned aerial vehicle special bullet comprises a bullet shell and a bullet head inserted into the bullet shell, the bullet head comprises an air cap and a bullet support which are connected with each other, the bullet support is arranged in the bullet shell, a containing cavity is formed in the bullet support, and a plurality of bullet clusters are contained in the containing cavity. Each bullet cluster comprises a plurality of cylindrical bullets, a propelling assembly is further arranged on the bullet shell and used for driving the bullet head to leave the bullet shell, and the structure of the bullet support is arranged to be capable of cracking after leaving the bullet shell so that the cylindrical bullets can be scattered. According to the anti-unmanned aerial vehicle special bullet, the bullet cluster is loaded in the bullet support in the bullet shell, the bullet cluster enables the bullets to be scattered under the action of the propelling assembly and air resistance, so that main killing power is provided, the defect that shotgun guns or other anti-unmanned aerial vehicle equipment is often needed for main killing in anti-unmanned aerial vehicle combat is overcome, and the anti-unmanned aerial vehicle special bullet is suitable for being used in unmanned aerial vehicle combat. The problems of universality and portability of an individual soldier in anti-unmanned aerial vehicle combat in a contemporary combat environment are solved.

A projectile includes a shell defining a cavity and one or more retainers. A bolo is disposed within the cavity and a backplate is engaged with the one or more retainers. The backplate is configured to separate from the shell to release the bolo in response to imbalanced forces resulting from deploying the projectile.

A 25 mm ammunition cartridge centered about a longitudinal axis and extending from a proximal end to a distal end including a case having a base defining the proximal end and a case sidewall extending from the base to a distal mouth and defining a case cavity, a propellant charge disposed in at least a portion of the case cavity, a body having a proximal cup and a body sidewall extending to a distal interface, wherein at least a proximal portion of the body is receivable in the case cavity distal to the propellant charge, a cap extending from a proximal cap portion coupled to the distal interface of the body to a dome defining the distal end of the cartridge, wherein the body and the cap define a projectile cavity, and one or more projectiles positioned within the projectile cavity.

The invention discloses a capture net launching ammunition for intercepting an unmanned aerial vehicle, belongs to the technical field of unmanned aerial vehicle interception, and is suitable for middle and close range interception of a small FPV unmanned aerial vehicle in military and security scenes. The ammunition comprises an outer sleeve, a cartridge case, a primer, propellant powder, a partition plate, a shifting rod, a carbon fiber net and four to six net hammers. When the net hammers are combined, a cylinder structure for accommodating the carbon fiber net is formed; the shifting rod is arranged in a bottom groove of the net hammer, and an outer end protruding part is matched with a straight groove and a spiral groove in the inner wall of the cartridge case. After percussion, gunpowder fuel gas pushes the partition plate to drive the assembly to advance, the shifting rod moves and rotates along the guide groove, the net hammer is driven to scatter centrifugally, the carbon fiber net is unfolded to form a 100-square-meter interception area, and the effective interception distance is about 50 meters. The device can also be transformed into a gun grenade form, is adaptive to standard gun launching, is compact in structure, is reliable to unfold, and can cope with the threat of a small-sized high-speed unmanned aerial vehicle.

A drone defense ammunition, such as rifle ammunition (e.g., with a caliber of up to 20 mm) or shotgun ammunition (e.g., up to caliber 4), may include projectiles. The ammunition may release the projectiles loosely as a result of an activation occurring with a time delay to firing of the drone defense ammunition.

There is provided a reversible range extension device, capable in use, of being reversibly engaged to a body of an artillery shell, said range extension device comprising at least one energetic material, and an igniter, wherein the range extension device comprises a first end with an aperture, and second closed end, wherein the range extension device, in use, is selectively arranged to be in an active orientation or inert orientation, wherein in the active orientation the range extension device is arranged such that the aperture faces rearwardly away from the shell to allow the range extension device to function, and in the inert orientation the range extension device is arranged such that the aperture faces inwardly towards the shell.

The application provides a hand-throwing riot control device for pneumatically releasing a riot control agent. After the device is thrown, the pressure rod is lifted up under the action of the pressure in the container shell, the handle is rotated around the supporting shaft on the inner cover of the container, the split pin slides in the arc-shaped slide to the terminal position, the rotation of the handle is limited, the lifting distance of the pressure rod is limited, the liquid flow channel is opened after the pressure rod is lifted, the solution of the riot control agent flows through the liquid flow channel under the action of the internal pressure, and is sprayed into the external environment through the atomizing nozzle connected at the end of the liquid flow channel. When the device is sprayed, the device rotates rapidly because the force at one end of the device and the center of mass are not at the same point, so that the device has the function of anti-throwing. The device is applied to the disposal of mass incidents and the like. The application can enrich the devices used for riot control operations and provide diversified choices for disposal operations.

The present invention relates to a missile (10) with a firing device (20) having several barrels (11) extending in the direction of a longitudinal axis (A) of the missile (10) and arranged inclined or skew relative to the longitudinal axis (A), wherein projectiles (12) provided with propellant charges (13) for ejection from the barrels (11) can be loaded into the barrels (20) and a method for operating such a missile (10).

Unmanned systems, and primarily vehicles, and in most embodiments unmanned aerial systems (UAS), as well as novel guided and unguided munitions are presented herein. to the two combine to present unmanned weaponized systems that not only carry weapons functionality, but allow for advanced observation and reconnaissance. These unmanned systems are largely directed toward military applications where the weaponized unmanned system may be forward deployed to allow human warfighters to remain at long range distances from the potential targets, and to provide surveillance, target identification and tracking, general reconnaissance information, and the like, while also providing weaponized attack capabilities. The unmanned systems may, in some embodiments, include advanced command and control capabilities for communication between the system and the remote, rear-positioned warfighter, and between separate elements of the unmanned system. Many embodiments also include weapons systems, munitions, or rounds with guidance and real-time maneuverability capabilities as well.

Methods and apparatus for artificial bird manufacturing in impact testing is described herein. An apparatus to generate an artificial bird for impact testing includes a mold generator to form a mold based on a bird class identification, a mold filler to fill the mold with a first layer of crushed ice and a second layer of crushed ice, a compressor to compress an ice surface of at least one of the first layer or the second layer of the crushed ice to form indentations on the ice surface, and a freezer to re-freeze the crushed ice layers inside the mold to form an artificial bird.

A projectile with a snare for a barreled weapon relates to means for increasing the effective area of a snare, i.e. a structure consisting of weights interconnected by lines which unfolds in flight, fired from a barreled weapon to mechanically immobilize small objects. The projectile is disposed in a shell with a powder propellant and contains weights interconnected by snare lines. The projectile also contains a spring having a central portion and peripheral arms preferably oriented along an imaginary longitudinal axis of the shell. Situated between each arm and the central portion is a bend region. The spring is in a state of elastic flexural deformation. When the projectile is fired and exits the barrel, the spring straightens and throws the weights apart. The lines straighten. The snare flies toward the object to be immobilized and immobilizes same by means of the lines and weights.

A method for thermal processing bullets to reduce adhesive stress, the method includes obtaining one or more bullets configured to be propelled down a gun barrel, disposing the one or more bullets within a chamber having a temperature gradient between ambient temperature and cryogenic temperature, the chamber having a plurality of temperature zones, moving the one or more bullets between the plurality of temperature zones of the chamber, and returning the one or more bullets to the ambient temperature to reduce adhesive stress between the bullets and the gun barrel.

This invention discloses a pre-fragmented loading fixture for irregularly shaped warheads, comprising an outer fragment mold and an inner fragment mold. The inner fragment mold is fitted inside the outer fragment mold. The space formed by the inner surface of the outer fragment mold and the outer surface of the inner fragment mold constitutes a pre-fragmented loading chamber for loading pre-fragments. The outer fragment mold includes a semi-shell, with a first semi-circular end plate and a second semi-circular end plate of identical structure respectively disposed on the two axial end faces of the semi-shell. The distance from the inner wall of the first semi-circular end plate to the inner wall of the top of the semi-shell is 4-5 mm, and the distance from the outer wall of the first semi-circular end plate to the outer wall of the top of the semi-shell is 8-10 mm. This invention uses the inner fragment mold to compress and arrange the pre-fragments, utilizing compression and gravity to achieve the densest arrangement of pre-fragments in batches, greatly reducing the amount of fragment arrangement work and eliminating the irrelevant mass introduced by glue bonding, thus avoiding the loss of the warhead's destructive capability.

[Solution] A hook assembly (18) for use with an entanglement capture projectile (12) is provided. The hook assembly includes at least one hook (19) having an apex portion (22) and a sharpened prong (20) extending distally from the apex portion. A protective cover (26) is carried adjacent the apex portion of the at least one hook. The protective cover includes at least one substantially planar surface (28). The protective cover is positioned relative to the at least one hook such that the sharpened prong of the at least one hook extends distally from the protective cover, thereby leaving the sharpened prong exposed while the protective cover is carried adjacent the apex portion of the at least one hook.

- Launching structure for a pyrotechnic cartridge and pyrotechnic cartridge equipped with such a launching structure. - The launching structure (2) comprises a socket (3) and a pyrotechnic ejection system (4), the pyrotechnic ejection system (4) being activated by the application of an electric current and being mounted in a housing (9) provided at one end (3A) of the socket (3) and being accessible from the outside, the interface (10) between the pyrotechnic ejection system (4) and the socket (3) being provided with an insulator (11) which is configured to completely electrically isolate the pyrotechnic ejection system (4) from the socket (3) so that in the event of electromagnetic interference such as a lightning strike, which could generate an electric current which tends to propagate in the socket (3), the pyrotechnic ejection system (4) is not impacted by this electric current and is not at risk of being activated unintentionally.

The invention relates to the technical field of alloy shaped charge liners for perforating bullets, and particularly discloses an energy-releasing alloy shaped charge liner for a perforating bullet and a preparation method of the energy-releasing alloy shaped charge liner for the perforating bullet to solve the problems that when an alloy shaped charge liner is prepared through an existing Zr-Ti-Nb composite material system, a blank is prone to expanding and cracking, and the dynamic tensile property of a product is insufficient. Comprising the following steps: S1, respectively taking zirconium powder, niobium powder, titanium powder and TiH2 powder, and mixing to obtain a premix; s2, taking the premix, and performing dry bag static pressure to obtain a dry bag static pressure blank; s3, the dry bag static pressure blank is taken and subjected to stepped hydrogen control sintering, and a hydrogen control sintering blank is obtained; s4, the hydrogen-controlled sintered blank is taken and placed in an argon atmosphere, heating and pressure sintering are conducted, and a hot isostatic pressing sintered blank is obtained; and S5, the hot isostatic pressing sintered blank is subjected to oil quenching at the temperature of 1050 + / -50 DEG C, and the energy release alloy shaped charge liner for the perforating bullet is obtained. And meanwhile, multiple processes such as oil quenching heat treatment are combined, the energy-releasing alloy shaped charge liner of the full-beta-phase structure can be stably obtained, and the effects such as the sneaking effect and the chambering effect can be achieved on the premise that the penetrating depth of a perforating bullet is not reduced.

A training munition assembly for use with a weapon includes a case, a first firing element, and a release assembly. The case defines an interior cavity. The first firing element is disposed within the interior cavity. The release assembly is coupled to the case and engages the first firing element. The release assembly is configured to cause movement of the first firing element from a first position within the interior cavity to a second position within the interior cavity responsive to actuation of the release assembly from outside of the case. Movement of the first firing element is configured to generate a firing signature that is indicative of actuation of the release assembly.

A less-lethal projectile 10 include a rear portion and a front portion. The rear portion can be a base member 16 having a head 44, a waist 42, and a skirt 46 configured to obturate a rifled barrel bore 5 of an airgun. The front portion can be a hollow cylindrical cap 14 sealingly engaged with the head 44 such that the cap 14 and the base member 16 define an interior cavity 15 in which a payload 20 is received. The cap 14 can include a plurality of fins 30 and grooves 32 configured to stabilize the projectile 10 during flight toward a target and open without shattering the cap 14 to release the payload 20 from the cavity 15 upon impact of the projectile 10 with the target.