851results 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.

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.

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 invention belongs to but not limited to the technical field of interception nets, and particularly relates to a multi-point traction type interception net launching device which comprises a base, a power device, a launcher and an interception net. The base can be adjusted and positioned at multiple angles, the borne impact force is at least not less than 15 KN, the base is designed into a folding structure, the packaging size is reduced, and transportation and storage are facilitated; the power device adopts compressed air as a power source, an air storage chamber is filled with high-pressure air, when a switch is turned on, energy of the high-pressure air is released instantly, and huge aerodynamic force acts on the pressed area of an object, so that the object moves in an accelerated mode from a static state and is thrown out. The power device body is composed of a launching tube, an air chamber, a valve element assembly, a firing device, a trigger, a carbon fiber air cylinder, a shell and the like, the launching tube, the carbon fiber air cylinder and the shell are distributed on the two sides of the air chamber, the firing device is arranged above the air chamber, and the trigger is pressed on the firing device; the launcher is in a horn shape, and four cylindrical storage bins connected with the launching tube are arranged on the edge of the launcher.

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.

An expanding fin aerial rocket in combination with a sleeve for restraining the fins prior to deployment. The rocket has an elongate body with a fore end for a warhead and an opposed aft end for motor and guidance fins. The guidance fins are hingedly attached to the rocket body at a proximal end and extend outwardly to a distal end. Fins may be collapsed during storage to conserve space and prevent damage. The springs are outwardly spring biased for flight upon deployment. The rocket has a durable removable sleeve, which fits over the fins during storage, to retract the sleeves into a collapsed position. The sleeve is removed for deployment, so the fins may radially expend to an extended position. The durable sleeve may then be reused for another rocket.

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.

An explosive fragmentation structure includes a fragment enhancing insensitive munitions (IM) liner. The IM liner includes a patterned metal structure having openings therethrough embedded in a compressible material to define a desired fragmentation pattern of the outer metal casing upon detonation of the explosive. The IM layer is positioned between and in conformal contact with the outer metal casing's inner surface and the explosive's outer surface.

A projectile system is described, the projectile system includes a projectile body, the projectile body including a front end portion that tapers to a point at the front end and the front end portion of the projectile body is dimensionally smaller than a bore of a firearm system, the projectile body including a driving band portion behind the front end portion of the projectile body, the driving band the driving band portion being dimensionally equal to a caliber of the firearm system and dimensionally greater than a bore diameter of the firearm system, such that the driving band portion comes into contact with the bore of the firearm system when the projectile passes through the bore of the firearm system.

A firearm projectile device is provided. The device is comprised of a projectile body with a partially hollow area that allows air to travel through the projectile and reduces the projectile's coefficient of drag. Both ends of the device are preferably pointed to further reduce the coefficient of drag of the device. In addition, the second end attaches to a fitted gas block that seals the projectile from a propellant within the casing of the device.

The invention provides an intelligent simulation training bomb for ground attack of an unmanned aerial vehicle. The training bomb comprises a bomb body, a thrust reverser, a fairing, a mounting frame, a smoke tank and a control module. Wherein a gas cabin is arranged in the bomb body, and the thrust reverser is composed of an electromagnetic valve and a multi-way pipe. The mounting frame integrates a fuming tank, a control module and a motion sensing module, and the control module calculates the falling speed, the grounding time and the position coordinates in real time based on data of all sensors of the motion sensing module so as to control the electromagnetic valve to be opened, so that compressed gas in the gas cabin is ejected from a reverse thrust gas opening in the circumferential direction of the fairing through the multi-way pipe; in combination with deformation buffering of the fairing made of an elastic material, nondestructive recovery of the training bomb is achieved, and repeated use is facilitated. And meanwhile, the fuming tank is controlled to trigger and release tracing smoke, so that an impact point is marked, and parameters such as latitude and longitude during landing are sent to a ground guide training system to serve as an evaluation basis of throwing precision.

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 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.

The invention relates to a PID (Proportion Integration Differentiation) control inertial servo system and a control method. The PID control inertial servo system comprises a controller, a control circuit, a driving circuit, a motor, a potentiometer, a system clock, a timer, an analog-to-digital converter, a plurality of serial ports, a communication bus, main control equipment, a steering engine, a fuzzy PID control module, a sampling module, a current sensor, a linear quadratic regulator, a PWM (Pulse-Width Modulation) duty ratio module and an integration module, the control circuit comprises a control chip; the driving circuit comprises a first driving circuit and a second driving circuit; the first driving circuit comprises a driving chip; and the second driving circuit is electrically connected with the motor and is provided with a plurality of switches. On the basis of position closed-loop feedback, with the fuzzy PID control algorithm as the core, optimal system parameters are obtained through a linear quadratic regulator, and compared with traditional PID control, fuzzy PID control has higher control precision, stability and response speed.

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.

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.

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.

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.

The invention provides a system device for core-level offshore recovery of a carrier rocket and a control method. The system device comprises an offshore recovery platform body, a core-level recovery capture rotary locking device, a dumping thrust reverser, an anti-dumping damping device, an auxiliary holding device and a locking device moving platform. The locking device moving platform can move to any position on the offshore recovery platform body; the core-level recycling, capturing and rotating locking device is used for receiving core-level position signals and supporting vertically descending cores; the dumping thrust reverser is used for holding the core; the anti-toppling damping device is matched with the toppling thrust reverser to enable the core to topple to a horizontal state; the auxiliary clasping device is used for clasping a core in a horizontal state. According to the invention, the carrier rocket core-level can be converted from a vertical fixed state to a horizontal fixed state after being recovered on the offshore recovery platform, the core-level mass center is reduced, the overturning risk of the core-level and the offshore recovery platform body is greatly reduced, and the harbor returning safety after core-level offshore recovery is improved.

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.