1186results 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.

Various countermeasure dispensing systems (or CMDSs) and method of use are described herein. CMDS may include a dispenser assembly operably engaged with a platform where at least one electrical connection provides electrical communication between the dispenser assembly and a sequencer. CMDS may also include a magazine assembly operably engaged with the dispenser assembly, wherein the magazine assembly comprises a magazine configured to hold at least two countermeasure expendables. CMDS may also include a breechplate assembly operably engaged with the magazine assembly and adapted to dispense the at least two countermeasure expendables. CMDS may also include at least one magazine identification switch (MIS) operably engaged with the magazine assembly and the breechplate assembly. CMDS may also include that the at least one MIS is configured to enable the sequencer and the breechplate assembly to selectively dispense at least one countermeasure expendable from the at least two countermeasure expendables.

The method and apparatus for a remote weapon station or incorporated into manually-aimed weapons. The methodology requires use of a muzzle velocity sensor that refines the aiming of the second and subsequent fires or volleys fired from weapon systems. When firing the first volley a weapon uses an estimated velocity and, at firing, the muzzle velocity of a projectile is measured. When firing the second volley a weapon's fire control calculates an aiming point using the measured velocity of the first volley.

An elongate munition with a longitudinal axis and having a nonfragmenation hollow collar. The hollow collar has an inner surface and an opposed outer surface with a first plurality of ports extending through the collar in a substantially radial direction. The ports are spaced from adjacent ports in both circumferential and longitudinal directions. A first plurality of ammunitions is disposed in each port of the first plurality of ports and oriented outwardly from the longitudinal axis. An ignition source for expelling each ammunition outwardly from the collar responsive to an ignition signal is also provided.

To study a system that transmutes atomic nuclei using muons, devise a light source device and a propulsion device including a nuclear transmutation system, and examine a centrifugal force application unit which may be accelerated by the propulsion device, and devise an electric field generator or a magnetic field generator.SOLUTION: A system is devised that decelerates cosmic muons produced from cosmic rays or high-speed muons derived from mesons produced from atomic collisions with electric field and deceleration means and uses the muons for nuclear transmutation. Also, a decelerator using a laser wake field and a decelerator using an element forming an electric field are proposed. A radiation light source having the nuclear transmutation unit is disclosed. An ionization device, a centrifugal gun device, a centrifugal force and pressure applying device, a pressure generation unit, a pressure applying material, a high-pressure induction superconductivity experimenting system, a magnetic device, and a magnetic sail are disclosed.SELECTED DRAWING: Figure 18

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.

A projectile and method for stopping aerial vehicles. The projectile comprises a shell—and a bunch of filaments. The bunch is wound in a coil and placed inside the shell. The projectile according to the solution may be brought to a target by different methods and utilising different means. For example, the projectile may be fired with compressed air or a propulsion charge, by using a compressed air weapon or rocket launcher. In addition, the projectile may be taken to the target by using a rocket or aerial vehicle.

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.

The invention discloses a typical warhead-fuze collaborative weapon system, and belongs to the technical field of ammunition fuze, the typical warhead-fuze collaborative weapon system comprises a shell, a fuze module, a guidance cabin, a warhead, a detonation module and a fuel cabin are arranged in the shell, the fuze module is located at one end of the shell, the fuel cabin is located at the other end of the shell, and the warhead is located in the middle of the shell; the guidance cabin is located between the fuze module and the warhead, and the detonation module is located between the warhead and the fuel cabin. According to the typical warhead-fuze collaborative weapon system, the collaborative performance is optimized, and efficient collaboration among the warhead, the fuze module and the explosion tube is achieved through innovative module arrangement and connection design; the environmental adaptability is improved, structural strengthening and adaptability design are carried out on key modules of the system for high-altitude, high-temperature and other complex combat environments, and reliable operation of the system is ensured; and through the heat insulation design and multi-layer protection, the isolation performance of the warhead and the fuel cabin is improved, and accidental explosion caused by heat transfer is prevented.

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.

Apparatuses and techniques for reducing backlash between components in a transmission system are provided. The apparatuses and techniques provide a controllable torque over a target range of motion of a component in the transmission system. This eliminates the play at the interfaces between components and forces the components to maintain a controlled contact between the interfacing surfaces.

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 projectile incorporates one or more spoiler-tabbed spinning disks to effect flow around the projectile and thus impart steering forces and / or moments. The spoiler tabs may be deployed only during steering phases of travel thus minimizing the drag penalty associated with steering systems. The disks are driven by motors and informed and controlled by sensors and electronic control systems. The spoiler tabs protrude through the surface of the projectile only for certain angles of spin of the spinning disk. For spin-stabilized projectiles, the disks spin at substantially the same rate as the projectile, but the disks may function in fin-stabilized projectiles as well. Any number of such spinning flow effector disks may be incorporated in a projectile, with the manner of functional coordination differing slightly for even and odd numbers of disks.

A lighted projectile may comprise a switch and a light source. The switch may comprise a moveable portion. The projectile may receive a propellant. The projectile may fluidly couple the propellant to the switch. The projectile may comprise a cavity by which the propellant is fluidly coupled to the moveable portion of the switch. Responsive to receiving the propellant, the moveable portion of the switch may move within the projectile. Responsive to movement of the switch, the light source may be activated. Movement of the switch may close a circuit between the light source and a power supply integrated within the projectile. The moveable portion of the switch may comprise the light source. Responsive to receiving the propellant, the projectile may be deployed from a projectile launcher. The projectile may further comprise a user interface by which a reset force may be applied to the switch to deactivate the light source.

An invention for using commonly available weaponry, namely shotguns or larger caliber cannons, for the control of drones and other projectiles by use of an ammunition containing aerodynamically designed series of sub-projectiles linked together by high tensile strength web in such a manner as to expand to the predetermined maximum size immediately upon exiting the barrel of the weapon and continuing along a steady and predictable flight path to the target while maintain the shape of the web to provide the most consistent interception pattern increasing the odds of success.

The invention discloses a multi-stage damage warhead and a design method thereof, and belongs to the technical field of military equipment.The multi-stage damage warhead comprises a fuze system, a multi-stage damage warhead module is arranged on one side of the fuze system, the multi-stage damage warhead module comprises a shell, and a first-stage damage unit, a second-stage damage unit and a third-stage damage unit are arranged in the shell; the second-level damage unit is located between the first-level damage unit and the third-level damage unit, explosion-proof layers are arranged between the first-level damage unit and the second-level damage unit and between the second-level damage unit and the third-level damage unit, and first detonating devices are arranged in the centers of the explosion-proof layers. According to the multi-stage damage warhead, the design method thereof and the fuze system, staged triggering of the multi-stage damage module can be achieved, it is ensured that the multi-stage damage module is started according to a preset plan, the multi-stage damage module can select the corresponding damage unit to attack according to different characteristics of a target, and the multi-stage damage warhead is high in safety. Therefore, the hard target and the soft target can be efficiently damaged.

The present invention relates to a bullet, in particular a deformation bullet, such as a hollow-point bullet, for example for police and / or authority ammunition, in particular with a caliber in the range of 4.6 mm to 20 mm, comprising a bullet body with a nose wall delimiting a central cavity which is open towards the surroundings, wherein the nose wall is notched and / or the cavity is produced by cold forming in such a way that on impact of the bullet on a target the nose wall is deformed so that it is widened by less than 90°, in particular less than 60°, in particular less than 45° or less than 30°, in relation to the longitudinal axis of the bullet.

Projectiles and methods of making and using same are disclosed herein. A projectile comprises a first portion having a first cylindrical portion having a first flat end surface, a first section extending from the first cylindrical portion at a first acute angle, a second section extending from the first section at a second acute angle, and a tip section extending from the second section and terminating in a pointed tip. The projectile includes a second portion having a second cylindrical portion having a second flat end surface and a trailing portion having a generally frustoconical shape. The trailing portion tapers towards a trailing end of the projectile. A post couples the first cylindrical portion and the second cylindrical portion. The post is in contact with each of the first flat end surface and the second flat end surface.

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 body spin detection device for a projectile, the device including a perturbing element and a detection element electrically connected to detection circuitry in the projectile. The detection circuitry configured to receive, via the detection element, a first and second input signals and determine that the first input signal is different from the second input signal based on signal characteristics for the first and second input signals. The detection circuitry is further configured to determine a spin rate for at least one of the despun control portion and the chassis by determining a time period between receiving the first input signal and the second input signal.

A soft reusable grenade round for team-based shooting game having a top shell assembly and a bottom shell assembly. The top shell assembly has a rounded top shell defining a cavity and at least one hole. The bottom shell assembly is removably coupled to the top shell assembly. The bottom shell assembly has a bottom shell defining an upper cavity and a lower cavity separated by an interior wall, and tabs separated by grooves in line around a perimetral surface of the bottom shell. The top shell assembly and the bottom shell assembly are reusable and made of a soft material such as rubber.

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 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.