691results about "Ammunition 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.

Provided is a polymer jacketed projectile with metal core. The projectile includes a metal bullet core and a monolithic polymer bullet jacket surrounding a portion of the bullet core. The jacket includes a series of radial driving bands cut into the jacket in a graduated configuration at increasing thicknesses. The graduation and increasing thickness of the driving bands allows gradual radial acceleration upon engraving of the rifling due to intentional radial deformation of the forward driving bands. Additionally, the bullet core) includes high-friction surfaces formed in a longitudinal direction or at a base of the bullet core. The modified surface increases friction between the bullet core and polymer, further decreasing radial slippage.

The disclosure is directed at a blank fire bullet trap attachment (BFBTA) that provides improved protection for firearm users when live ammunition is accidently loaded into the firearm. The BFBTA includes a barrel portion made of a first metal; and a hardened element portion made of a second metal, the hardened element portion sized to frictionally fit within the pipe portion; wherein the first metal is softer than the second metal, such that when live ammunition contacts the hardened element portion, the hardened element portion slides within the barrel portion.

A ceramic substrate including a porous internal structure including a sealant infiltrator. The sealant infiltrator includes sodium and silicate. The sealant infiltrator infiltrates at least some of the plurality of pores and closes the plurality of pores filled with the sealant infiltrator when exposed to a negative pressure. The sealant infiltrator is distributed across the exterior surface of the ceramic substrate.

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.

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.

Described herein are multi-part projectiles that include a high-friction coating as part of an interface between parts of the projectile body. The high-friction coating reduces the probability that projectile parts coupled at the interface would rotate relative as the projectile is launched, thus enhancing the reliability and accuracy of the projectile. In one example, a multi-part projectile includes a projectile body having first and back sections coupled by an interface. The front section has a front land and the back section has a back land. The threaded interface restrains the rotation of the projectile body first and back sections. A high-friction coating is disposed on at least one of the lands of one or both the front and back sections. The high-friction coating has a co-efficient of friction greater than the parent metals against each other alone, without the high-friction coating disposed therebetween.

A payload module for an aerial vehicle stores and deploys one or more submunition assemblies, which provide a portion of the vehicle's OML when stored, in a manner that preserves the aerodynamics of the aerial vehicle post-deployment. Pre-deployment a skin is aligned to a strongback such that the submunition assemblies are exposed through openings in the skin. Post-deployment, the skin rotates to cover any openings in the strongback exposed by the deployment of the submunition assemblies to restore the OML.

According to some embodiments of the present invention, an ammunition cartridge is provided herein. The ammunition cartridge may include a cartridge enclosure comprising a cartridge case portion and a jacket portion, wherein the jacket portion is configured to accommodate at least one projectile filling; and a base, connectable to the cartridge enclosure, wherein the base comprises an ignition device, wherein the cartridge enclosure comprises a section configured to control the detachment of at least some of the jacket portion from the cartridge case. According to some embodiments of the present invention, another ammunition cartridge is provided herein. The ammunition cartridge may include: a cartridge case portion; and a jacket portion, wherein the jacket portion is configured to accommodate at least one projectile filling, wherein the jacket portion is made of at least one of: polymer material, and composite material.

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.

A projectile that includes an artillery shell having a casing that defines a surface is provided. The projectile has an obturator that includes an obturator first material layer on the casing surface and an obturator second material layer on the obturator first material layer. The obturator also has an obturator third material layer on the obturator second material layer. The projectile also has a driving band that includes a driving band first material layer on the casing surface and a driving band second material layer on the driving band first material layer. Additionally, the projectile includes a driving band lead-in having a driving band lead-in first material layer on the casing surface and a driving band lead-in second material layer on the driving band lead-in first material layer.

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 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.

Disclosed is a projectile comprising: (1) a metal core, such as a copper alloy core, including a base and a tip, where the base and the tip are separated by a core length along a z-axis running longitudinally through a center of the metal core; and (2) a jacket circumferentially attached to the metal core, the jacket surrounding at least fifty percent of the core length of the metal core, where the jacket includes: a polymer and a first jacket radial thickness along at least a section of an interquartile portion of the core length of greater than 0.03 inches.

The dart part may be the body, the tip (3), or the shaft (6). The part includes a base board (20) equipped with an accelerometer (21) and / or a. gyroscope (22), a. power source (23), and a processing unit (24). It further comprises a communication module (25) for wireless communication and / or an electronic signaling means (vibration motor (32), LED (26), sound generator (30)). The processing unit (24) is configured to receive data from the accelerometer (21) and / or gyroscope (22), to evaluate the data, and to signal the evaluated data via the electronic signaling means and / or transmit them via the communication module (25) for wireless communication. The part may include at least one touch sensor (27) for detecting touch on its surface, a magnetometer (28), or a microphone (29). The LED (26) may be arranged to be visible at the interface (5) of the rear end (4). The replaceable shaft (6) at the rear end (4) may be made of translucent material. The flights (8) on the shaft (6) may be provided with photovoltaic panels (9).

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.

Composite projectiles include various material compositions, diameters, and cavities within the projectiles having a variety of cavity diameters, sidewalls, and bottoms selected and formed to induce different levels of penetration and disintegration of the composite projectiles upon impact with targets.

A submunition assembly to be stored and deployed from an aerial vehicle, particularly a supersonic vehicle, includes a container having at least first and second walls that are joined at one end by a hinge that together define a volume along an axis perpendicular to the hinge that contains a submunition. The submunition assembly is suitably axially-shaped with a rigid parachute panel positioned around the hinge to separate and deploy a parachute. The container may have an internal volume that is conformal to the submunition. The container may have an exterior shape that is either optimized for free-fall or has a portion that provides a conformal surface for the aerial vehicle. The submunition assembly may be configured so that all processing, memory and data resides with the submunition, which issues any and all commands to control the container including separation of the rigid parachute panel and opening of the container to release the submunition.

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.

A projectile capable of coupling or otherwise attaching itself to a target. The projectile includes a coupling mechanism that enables the projectile to be coupled to the target. The projectile can include a variety of electronic components including a processor and a data communications component that enables the projectile to transmit data to a remote device.

A receiving device (40) for guided missiles (3) for airborne deployment from aircraft (2) and a deployment device (50) for airborne deployment of guided missiles (3) are proposed, wherein the deployment device (50) has a receiving device (40) and / or is designed to interact with the receiving device (40), and wherein the receiving device (40) comprises a container (41) with a receptacle (43) for at least one guided missile, which is designed to disintegrate in a predetermined manner by an air flow prevailing during airborne deployment.

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 utility model discloses a deep well petroleum perforating bullet, relates to perforating bullet technical field, including perforating bullet body, lengthening spacing subassembly and explosion-proof subassembly, perforating bullet body includes perforating bullet upper casing and perforating bullet lower casing, lengthening spacing subassembly one end is connected with the perforating bullet upper casing, and the other end is connected with the perforating bullet lower casing, and the explosion-proof subassembly is connected with the perforating bullet upper casing and the perforating bullet lower casing. The perforating bullet body is arranged in the anti-explosion assembly, the anti-explosion assembly comprises an anti-explosion barrel and an anti-explosion cover, different perforating requirements are met by adjusting the volume in the perforating bullet, the perforating bullet is wrapped by arranging the anti-explosion barrel and the anti-explosion cover, and the anti-explosion effect is achieved. And the problem that the debris falls to the bottom of the perforation and the perforation is blocked can be solved while the debris is prevented from being sputtered to other parts in the casing pipe in a large area.

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).

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.