Abstract: A wireless electronic initiation device for a detonator via a shock tube comprises an initiation member for initiation the shock tube and an energy storage for providing initiation energy to said initiation member. The initiation device comprises also a wireless communication device with a receiver for receiving an initiation command in a wireless way from an initiation arrangement. The initiation device comprises also a controller, which is configured to determine said received initiation command and based on said received initiation command configured to activate said initiation member to ignite the detonator initiator (108) by the energy fed from the energy storage.

Abstract: A compact safety ignition device for a dual pulse motor capable of preventing accidental ignition of an ignition device includes a housing which forms an accommodation space and coupled to a front port of a combustion tube. Primary and secondary circuit portions mounted inside the housing for generating ignition signals for a primary and secondary propellant, respectively. A primary ignition device mounted at one end of the housing and electrically connected to the primary circuit portion and accommodated in the combustion tube. A secondary bulkhead initiator mounted inside the housing and electrically connected to the secondary circuit portion. The primary ignition device includes a primary detonation portion electrically connected to the primary ignition device and includes a primary bulkhead initiator electrically connected to the primary detonation portion at a protrusion protruding from an end of the primary detonation portion.

Abstract: A squib assembly for a non-electric initiator of an anti-personnel obstacle breaching system includes a housing configured to connect to the igniter of a rocket motor of the anti-personnel obstacle breaching system, a slider assembly slidably contained within the housing and configured to connect to a shock tube of the non-electric initiator, and a pyrotechnic element disposed within the housing. Upon activation of the non-electric initiator, the squib assembly is configured to mechanically puncture a base of a initiator sleeve of the rocket motor and to thermally initiate ignition of the rocket motor.

Abstract: Trigger devices for igniting an exothermic reaction is provided. The trigger devices may be flint type trigger devices and electronic type trigger devices. The flint type trigger device has a housing with a spark opening on a rear wall of the housing. A mold mounting assembly is secured to an exterior of the rear wall of the housing. A motor assembly is secured to the inside of the rear wall of the housing. The motor assembly has a flint wheel attached to a shaft of a motor, where the flint wheel is located adjacent the spark opening. A flint assembly is positioned within the housing such that a flint of the flint assembly is in contact with the flint wheel. A controller positioned within the housing is configured to selectively activate the motor to cause the flint wheel to rotate against the flint to create one or more sparks that are ejected from the spark opening.

Abstract: Trigger devices for igniting an exothermic reaction is provided. The trigger devices may be flint type trigger devices and electronic type trigger devices. The flint type trigger device has a housing with a spark opening on a rear wall of the housing. A mold mounting assembly is secured to an exterior of the rear wall of the housing. A motor assembly is secured to the inside of the rear wall of the housing. The motor assembly has a flint wheel attached to a shaft of a motor, where the flint wheel is located adjacent the spark opening. A flint assembly is positioned within the housing such that a flint of the flint assembly is in contact with the flint wheel. A controller positioned within the housing is configured to selectively activate the motor to cause the flint wheel to rotate against the flint to create one or more sparks that are ejected from the spark opening.

Abstract: The present invention relates to an igniter assembly, including a blast tube provided with a supporting part formed in a cylindrical shape, and an aft-closure part having front and rear sides through which igniter combustion gas is emitted, an igniter disposed adjacent to the rear side of the aft-closure part and storing ignition pellet therein, and a blast tube stopper formed in a shape surrounding the supporting part, accommodating the igniter, and coupled to the rear side of the aft-closure part, wherein the aft-closure part includes a plurality of holes through which igniter combustion gas is emitted.

Abstract: An initiator apparatus (IA) for blasting, the IA including: a magnetic receiver configured to receive a through the earth (TTE) magnetic communication signal representing a command from a base station; a blasting controller, in electrical communication with the magnetic receiver, configured to generate response data in response to the command; and an electromagnetic (EM) transmitter system (ETS), in electrical communication with the blasting controller, configured to transmit the response data for the base station using a TTE electromagnetic (EM) signal.

Abstract: A device may include an electrically-operated propellant or energetic gas-generating material, additively manufactured together with electrodes for producing a reaction in the material. The device may also include a casing that is additively manufactured with the other components. The additive manufacturing may be accomplished by extruding or otherwise depositing raw materials for the different components where desired. The electrodes may be made of a conductive polymer material, for example using an electrically-conductive fill in a polymer.

Abstract: A downhole tool including a housing, a first portion of a trigger mechanism disposed in the housing, a degradable-on-command component movably disposed within the housing, a second portion of the trigger mechanism disposed in the component, the component being configured to positionally respond to an external input to dispose the first portion and second portion in operational contact with one another resulting in an initiation of degradation of the degradable-on-command component. A method for removing a component of a downhole tool.

Abstract: An igniter for propulsion unit including a receptacle having at least one opening through which passes a conducting line connected to an ignition carrier of a slapper contained within the receptacle, the igniter being characterized in that at least one elastomer material is disposed between the ignition carrier and the opening such that the pressure of the gases generated by the propulsion unit which is ignited pushes the elastomer material at the vicinity of the opening of the receptacle so that this elastomer material blocks the opening and avoids any gas leak through this opening.

Abstract: A downhole tool for performing a wellbore operation includes a perforating gun, a detector module connected to the perforating gun, wherein the detector module transmits a command in response to a signal, a signal generator configured to transmit the signal to the detector module, and a plug dropping mechanism located adjacent to the detector module, the plug dropping mechanism releasing an object upon receiving the command from the detector module. The perforating gun is fired, and the downhole tool is activated. A plug-mate positioned adjacent to the plug dropping mechanism receives the object. The plug-mate has a profile complementary to the object, and the plug-mate and the object cooperating to block flow along the wellbore. In another mode of operation, an actuation member actuates the plug-mate.

Abstract: An energy transfer device (10) is provided that is capable of transferring the energy output from one pyrotechnic device (52) to another device (78) for initiating firing thereof. Device (10) comprises a device housing (12) in which a deformable device insert (14) is received. Device insert (14) comprises a central passageway (34) for transmitting the output from a pyrotechnic device (52), including energy, gasses, and/or solids, to another pyrotechnic device (78). The passageway (34) conducts the pyrotechnic device output to a precise location on the second pyrotechnic device (78) where firing is most effectively initiated. The energy transfer device (10) may be employed as a part of a tool (44) used in well completion operations.

Abstract: A muzzle loaded ammunition round having a bullet and a consumable cartridge case. The cartridge case is hollow and is filled with at least one propellant composition, the cartridge case being constructed from a consumable material, such as foamed celluloid. The bullet is commonly engaged to the propellant composition at least via the cartridge case, the propellant composition having a charge weight.

Abstract: A pyrotechnic slug, intended to be used by bomb squads to neutralize explosive devices, comprising a hollow cylinder, having an internal space, and having a projectile body made of non-metallic material, the projectile body having a closed front end and an open back end receiving a slug plug, the internal space containing a mixture cavity holding a pyrotechnic mixture, which upon ignition and explosion thereof is configured to create a weak pressure wave, and the pyrotechnic slug having an operating system comprising at least one selected from a list including: a) a mechanical impact firing system; and b) a delayed operating system; wherein the pyrotechnic slug is configured to be propelled from a barrel by one of: a) a separate cartridge; b) a unified slug comprising the projectile body inserted into a cartridge; and c) a rocket motor.

Abstract: A method of firing projectiles without the use of cartridge cases by electronically controlling the dynamics of internal ballistics created by combustion of Nitrous Oxide and a fuel injected under high pressure at oxygen rich or stoichiometric ratios. The shape of injector nozzles and the combustion chamber as well as a timed sequence of Nitrous Oxide injection, fuel injection and their ignition are used to create correct ballistics. The Timing of the injection and ignition sequence is automatically altered dynamically by an electronic control unit that obtains information from sensors and from an operator to tune the combustion for each firing so that the internal ballistic pressure versus time curve is favorable.

Abstract: The invention relates to producing a propellant charge igniter tube (2) for a propellant charge igniter (1) by means of hydroforming (high-pressure forming). According to the present invention, a sleeve base (6) is then joined to the propellant charge igniter tube (2) by means of friction welding, for example, and vulcanized without reworking. In this context, the rubber lips of the sleeve base (6) and the propellant charge igniter tube (2) are molded on, or vulcanized, on in one operation. The vacuum-packed benites (8) and the lower part (9) of the propellant charge igniter (1) can then be mounted in the sleeve base (6).

Abstract: Gas generators may be utilized for launching a projectile. Launch tubes may include gas generators. Methods of launching a projectile may include utilizing gas generators to impart an initial velocity to a projectile.

Abstract: Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes.

Abstract: An electrically operated propellant is configured to ignite and extinguish over a range of pressures. In examples, the electrically operated propellant is included in a gas generation system having a combustion chamber and at least two electrodes coupled with the propellant. The electrically operated propellant is configured to ignite at an ignition condition and extinguish under an extinguishing condition. In the ignition condition an electrical input is applied across the electrodes to ignite the electrically operated propellant. In the extinguishing condition the electrical input is interrupted while the pressure within the combustion chamber is greater than 200 psi, and the ignited electrically operated propellant extinguishes.

Abstract: A energy transfer device (10) is provided that is capable of transferring the energy output from one pyrotechnic device (52) to another device (78) for initiating firing thereof. Device (10) comprises a device housing (12) in which a deformable device insert (14) is received. Device insert (14) comprises a central passageway (34) for transmitting the output from a pyrotechnic device (52), including energy, gasses, and/or solids, to another pyrotechnic device (78). The passageway (34) conducts the pyrotechnic device output to a precise location on the second pyrotechnic device (78) where firing is most effectively initiated. The energy transfer device (10) may be employed as a part of a tool (44) used in well completion operations.

Abstract: Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes.

Abstract: Delay tools, systems and methods for achieving a selection of alternative delay times, a tool of which including a body, a drill bit operable relative to the body and a knob operably connected to the drill bit, and operably disposed relative to the body for engagement of the body with a rocket motor bulkhead and the drill both relative to a delay to provide for achieving a selection of alternative delay times.

Abstract: A device and method which combine electromagnetic acceleration with acceleration by high-pressure gases derived from chemical energy to achieve high slug speeds.

Abstract: A scalable, inert munition data recorder cartridge. This inert cartridge allows users to record data from within a weapon system feed chute, breach, and extractor port. This cartridge is adaptable to any weapon system, packaging unit, environmental chamber, or other ammunition holding and storage device. Although the cartridge is designed to interface with a weapon and ammunition packaging based on its shape, it still functions as designed regardless of its location and application. This would allow the cartridge to be placed anywhere an actual live cartridge of ammunition could be placed.

Abstract: The invention concerns a method for repeatable ignition of propellant charges in a weapon system, e.g. for firing shells from a barrel weapon, through electrical discharge in a combustion chamber duct (3) containing a combustion chamber substance (30), wherein the filling gas in the combustion chamber duct (3) is ionized by the high-voltage potential applied to the ionizing electrode (7), which is connected to a first high-voltage generator (2), thus increasing the electrical conduction capacity in the combustion chamber duct (3) such that an electrical sparkover through electrical discharge via a second high-voltage generator (5) between a rear electrode (22) and a front electrode (21) is generated and produces an effect, with subsequent ionization of the surface of the combustion chamber substance (30), which causes hot gas in a plasma-like state to be expelled from the combustion chamber duct (3).

Abstract: A distributed ordnance system comprises a plurality of ordnance controllers and a plurality of firing units. Each ordnance controller of the plurality of ordnance controllers may be operably coupled with at least one firing unit of the plurality of firing units. Each ordnance controller may be configured to provide power signals to the at least one firing unit coupled therewith, and communicate with the at least one firing unit for initiation of an ordnance event. A multiple-stage ordnance system may comprise a first stage and a second stage that each include an ordnance controller configured to control operation of an ordnance event, and at least one firing unit to initiate the ordnance event. Related methods for constructing a multiple-stage ordnance control system and controlling initiation of an energetic material are also disclosed.

Abstract: The invention relates to a method of, in the electrical ignition of a propellent charge (1) provided with an electrically conductive surface coating (5) and comprising one or more propellant components (3), ensuring that ignition and progressive combustion of the propellent charge take place. The method is characterized in that said electrically conductive surface coating, when ignition of the propellent charge is desired, is connected to an electrical high-voltage source (6), in that said high-voltage source is made to generate at least one high electrical pulse to said connected electrically conductive surface coating, and in that said at least one high electrical pulse produces an instantaneous flashover ignition of the electrically conductive surface coating of the propellent charge and of all its propellant components, simultaneously. The invention also relates to a propellent charge and to an ammunition shot comprising the propellent charge.

Abstract: A primary ignition system for large caliber ammunition which ignition system is less sensitive to unwanted ignition by conventional temperatures or conventional electrical signals or by stray electrostatic voltage electrical signals, or stray RF frequency signals. This ignition primer device begins the ignition sequence with applying a high voltage electrical pulse to a non-energetic element, specially coated with nano sized aluminum particles, to release and ionized discharge that generate a plasma in order to ignite an environmentally friendly ignition composition mix. The ignition composition is also comprised of aluminum water based nano material combined with oxidizer and binder. In the device's primer head assembly is a brass ignition pin pressed into a (non-electrically conductive) Torlon® material cup. The non-conductive Torlon® material acts as an insulator for the entire system.

Abstract: An electronic detonator control chip (100) includes a communication interface circuit (101), a rectification bridge circuit (102), a charging circuit (103), a charging control circuit (110), a power management circuit (104), a firing control circuit (105), a logic control circuit (106), a non-volatile memory (107), a reset circuit (111), a safe discharging circuit (108), and a clock circuit (202). Wherein, the communication interface circuit (101) includes a data modulation module (210) and a data demodulation module (211) including two data demodulation circuits (212). The logic control circuit (106) further includes a programmable delay module (281), an input/out interface (282), a serial communication interface (283), a prescaler (284), a CPU (285), and so on.

Abstract: A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignitable propellant. The thruster stack assembly further includes electrodes associated with the plurality of grain elements, the electrodes adapted for selectively igniting the plurality of grain elements. In one example, one or more of the grain elements may be ignited and combusted without igniting or damaging adjacent grain elements of the stack. The core region serves to channel combustion gases and exhaust from the thruster stack. Multiple stacks may be assembled together to form three-dimensional thruster arrays.

Abstract: A high impulse fuze booster includes a booster explosive charge positioned within an explosive charge cavity of a booster housing. A substantially planar flyer plate is coupled with the booster housing, and a detonation waveshaper is positioned within the booster explosive charge. A low-sensitivity explosive charge is opposed to the substantially planar flyer plate. The booster explosive charge is configured to generate a detonation wave and the detonation waveshaper shapes the detonation wave into a planar detonation wave, the planar detonation wave is parallel to the substantially planar flyer plate. The planar detonation wave interacts with the substantially planar flyer plate in two or more stages including a planar striking stage and a planar contact stage where the planar detonation wave carries the substantially planar flyer plate into planar contact with a plurality of surfaces of the low-sensitivity explosive charge to initiate the low-sensitivity explosive charge.

Abstract: A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignitable propellant. The thruster stack assembly further includes electrodes associated with the plurality of grain elements, the electrodes adapted for selectively igniting the plurality of grain elements. In one example, one or more of the grain elements may be ignited and combusted without igniting or damaging adjacent grain elements of the stack. The core region serves to channel combustion gases and exhaust from the thruster stack. Multiple stacks may be assembled together to form three-dimensional thruster arrays.

Abstract: A ring-shaped or plate-like element, in particular for a metal-sealing material-feedthrough, for example for devices which are subjected to high pressures, such as igniters for airbags or belt tensioning devices, includes a feedthrough opening, whereby the feedthrough opening is located substantially in the center of the ring-shaped or plate-like element and whereby the ring-shaped or plate-like element has a thickness. The ring-shaped or plate-like element has a relief region in the area of the feedthrough opening. Further, the ring-shaped or plate-like element in the relief region has at least one thickness which is reduced by the height of the relief region and which is selected so that the feedthrough opening can be punched out of the ring-shaped or plate like element having the reducing thickness.

Abstract: Ammunition with structural and functional features such as to optimize the propellant combustion process when the weapon is fired, resulting in accelerated delivery of the combustion gases. For this purpose, advantageously, the ammunition at issue is fitted with an innovative firing system (4), the incendiary operation of which allows to ignite the entire quantity of propellant (7) in a homogeneous and capillary manner. In this operational circumstance, a considerably larger quantity of propellant (than that occurring with the known art) is therefore ignited in a shorter time. This results in accelerated delivery of the gases, such as to transmit to the projectile (5) an extremely fast burst of thrust, resulting in greater ballistic yield of the projectile and greater damage to the target.

Abstract: A method for initiating a low-sensitivity explosive charge includes initiating a booster explosive charge within an explosive charge cavity in a booster housing, and generating a planar detonation wave. Generating the planar detonation wave includes directing a detonation wave through the booster housing along a first waveshaper surface of a detonation waveshaper. The detonation wave is directed around the first waveshaper surface toward a second tapered waveshaper surface. After progressing around the first waveshaper surface, the detonation wave is directed along the second tapered waveshaper surface. The detonation wave changes into a planar detonation wave as the detonation wave moves along the second tapered waveshaper surface, the planar detonation wave includes a planar wave front. The planar detonation wave strikes a flyer plate coupled over the explosive charge cavity of the booster housing, and the planar wave front makes planar contact along an inner face of the flyer plate.

Abstract: The invention relates to producing a propellant charge igniter tube (2) for a propellant charge igniter (1) by means of hydroforming (high-pressure forming). According to the present invention, a sleeve base (6) is then joined to the propellant charge igniter tube (2) by means of friction welding, for example, and vulcanized without reworking. In this context, the rubber lips of the sleeve base (6) and the propellant charge igniter tube (2) are molded on, or vulcanized, on in one operation. The vacuum-packed benites (8) and the lower part (9) of the propellant charge igniter (1) can then be mounted in the sleeve base (6).

Abstract: A method is provided for an electric activation of a plasma jet igniter for firing Electro-Thermal-Chemical (ETC) guns, machine guns and other equivalent ETC barreled weapons, without complete consumption of any of the components necessary for its activation upon activating the igniter. Each activation of the igniter by means of one or several voltage pulses, which from an electric pulse generator (10) are conducted between an anode (4) and a cathode (5), is preceded by heating of the anode (4) to such high temperature that at least parts of the dielectric material (2) arranged in proximity to the anode (4) have begun to vaporize. The method may be implemented using an adapted plasma jet igniter which has an anode that can be heated to a high temperature so that the igniter can be used for firing whole series of rounds or a full magazine of successively fired rounds in rapid order.

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

Abstract: A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignitable propellant. The thruster stack assembly further includes electrodes associated with the plurality of grain elements, the electrodes adapted for selectively igniting the plurality of grain elements. In one example, one or more of the grain elements may be ignited and combusted without igniting or damaging adjacent grain elements of the stack. The core region serves to channel combustion gases and exhaust from the thruster stack. Multiple stacks may be assembled together to form three-dimensional thruster arrays.

Abstract: A propellant charge for use for ammunition, in which the propellant charge is separate from the projectile, has a propellant charge substance which can be initiated by a fuse. In order to solve the problem of providing a propellant charge for use in a two-part munition, which on the one hand can be produced easily and at low cost and on the other hand does not present any risk of damage when mechanically loaded before use, it is proposed that a propellant charge casing be provided which surrounds the propellant charge substance, with the propellant charge casing being in the form of a plastic part which is composed of a non-combustible, temperature-stable plastic material.

Abstract: Methods and apparatus according to various aspects of the present invention comprise a propelling system for propelling projectiles with variable velocity. In one embodiment, a cartridge comprises a cartridge case, the propelling system, and the projectile attached to the cartridge case.

Abstract: A consumable flash tube for encapsulating igniter material in the propellant beds of propelling charges or rocket motors. The flash tube is constructed of a combustible, plastic material such as cellulose nitrate plastic or ethyl cellulose plastic. The combustible material is furnished with a filler of electrical charge dissipating material which renders the flash tube conductive. The conductive flash tube functions as an environmental housing and additionally as a grounded electrical conductor or Faraday shield so as to bleed off any inadvertent electrical charge presented to the flash tube and thus limit the charge transferred to the igniter material. Formation of the flash tube is by continuous extrusion of a mixture of the plastic material and electrical charge dissipating material into the shape of a hollow tube. After curing of the extruded tube, one end of the tube is flared to allow joining of the tube to a primer after the igniter material is positioned in the flash tube.

Abstract: The present invention relates to the field of propellant devices and more particularly to the propellant devices used in weapon systems and munitions. The invention has the two advantages of minimizing the risk associated with accidental attack to which propellant devices may be exposed thanks to the filling of the central channel commonly provided along the core of the cylindrical explosive charge and of greatly increasing the effectiveness of these propellant charges by the use of explosive materials having a very high burn rate.

Abstract: A cartridge assembly (10) for firearms or weapons, said cartridge assembly including a support body (11) having a central longitudinal channel (16) housing a plurality of projectiles (20, 22, 24) in end-to-end orientation and having a plurality of circumferential chambers (14), wherein each chamber houses (14a, 14b, 14c) at least one propellant charge (12a, 12b, 12c) and is located adjacent to a respective projectile; fluid communication means (18) included in the support body for communicating the products of a gaseous expansion of said propellant from a respective chamber (14) into said central longitudinal channel (16); whereby, upon initiation of a selected propellant charge (12a, 12b, 12c), the communicated products of gaseous expansion from a circumferential chamber force or eject a respective projectile (20, 22, 24) from the cartridge assembly (10). The propellant charges may comprise a volume of propellant material encased in a bag with an igniter.

Abstract: An ignition charge for an initiator provided with an igniting mechanism for setting aflame an ignition charge by the heat generated by an exothermic element connected via a pair of current conducting pins in response to an electric signal is a slurry ignition charge which is formed mainly of a mixture consisting of zirconium as a fuel component and potassium perchlorate as an oxidizing agent component. The ignition charge for the initiator contains nitrocellulose as a binder component in an extrapolated compounding ratio of 0.1% by weight or more and 0.5% by weight or less based on the total amount of zirconium and potassium perchlorate and isoamyl acetate as a solvent in an extrapolated compounding ratio of 12.5% by weight or more and 14.0% by weight or less based on the total amount of zirconium and potassium perchlorate. The ignition charge is spread on the exothermic element and dried. The ignition charge is for the initiator of a gas generator, particularly an electric gas generator.

Abstract: A pusher plate assembly for launching a projectile includes a pusher plate, a pressure seal circumferentially extending about the pusher plate, a cage extending from an aft side of the pusher plate, and a plurality of propellant portions disposed in the cage. A projectile system includes a launching tube, a projectile disposed in the launching tube, a pusher plate assembly disposed between an aft end of the projectile and the launching tube, a fuze, a charge igniter operatively associated with the fuze and the plurality of propellant portions, and a retainer disposed within the launching tube proximate a mouth of the launching tube. The pusher plate assembly includes a pusher plate, a pressure seal circumferentially extending about the pusher plate to seal an annulus between the pusher plate and the launching tube, a cage extending from an aft side of the pusher plate, and a plurality of propellant portions disposed in the cage.

Abstract: An artillery charge includes a generally cylindrical body with a hollow core; propellant disposed in the body and first energetic material disposed in the hollow core; and a seal disposed over one end of the hollow core, the seal including second energetic material disposed therein. A laser igniter ignites the second energetic material in the seal, thereby providing more reliable ignition of the first energetic material and the propellant. The artillery charge reliably ignites using a lower powered laser than known charges.

Abstract: A propellant charge, a priming cap including the propellant charge and a weapons training system including the priming cap are characterized in that the propellant charge contains a soft friction agent. The propellant charge can contain at least one impact-sensitive explosive substance as a heavy-metal-free priming compound, and the soft friction agent can be marble, calcite, dolomite, soft carbonates and/or mixtures thereof.

Abstract: This invention relates to a breech assembly of a gun adapted to fire caseless charges, ignited and enhanced with electrothermal chemical (ETC) charges. The gun utilizes charges as propellant and a plasma generator cartridge (PGC) for generating plasma when an electrical current is applied thereto. The breech assembly comprises a breech ring, a tilting block assembly, with a spindle installed and a sliding block for supporting or locking the tilting block assembly in a sealed position. The tilting block assembly is movable between a PGC firing orientation and a PGC loading/removal orientation. The breech assembly further includes a crank means, which includes a guide means for rotating the tilting block assembly from the PGC firing orientation to the PGC loading/removal orientation.

Abstract: An inflator for an air bag which can be assembled easily is provided. An igniter 30 is fixed inside a closure 20 using a resin 28 by charging molten resin through a resin charging hole 24 provided in the closure 20, and hardening the resin. The closure 20 is fixed to an inflator housing 12 by welding at a connecting portion 18. Since the number of components and the number of steps are smaller, favorable assembly workability is achieved.