Abstract: Systems, methods, and apparatuses are described for accelerating projectiles at high velocity. A barrel may include one or more heaters configured to heat a bore of the barrel prior to launch of a projectile. The barrel bore may be formed in a tungsten sleeve and may be heated to high temperatures. Heat from the barrel bore may be transferred to expanding propellant behind a projectile as it travels through the barrel bore.

Abstract: A system using Faraday's law to rapidly direct convert the kinetic energy of a magnetized and/or conducting projectile into usable electrical energy. The system includes a barrel comprising a bore; a circuit including a plurality of electrically conductive components distributed along a length of the bore; and a projectile comprising at least one of a conductive material or a magnetic material magnetically coupled to the electrically conductive components when the projectile is moving along the length of the bore. The circuit stores energy generated from an electric current induced in the electrically conductive components when the projectile moving along the length of the bore causes a magnetic interaction between the electrically conductive components and the magnetic material or the conductive material. The magnetic interaction also causes braking of the projectile.

Abstract: A space launch system includes a launch track and an elevating platform for horizontally launching aerospace vehicles at a takeoff velocity. The launch track includes a first portion horizontally oriented with respect to the horizon, a second portion positioned after the first portion and horizontally oriented with respect to the horizon, and a third curved transition portion disposed between the first portion and the second portion. The elevating platform is coupled to the launch track and is configured to receive and position an aerospace vehicle upon the launch track. A magnetic accelerator is disposed along the launch track for propelling the aerospace vehicle down the launch track to reach the takeoff velocity. The magnetic accelerator includes magnetic levitation trains, each comprising a respective plurality of carriers that couple to the aerospace vehicle.

Abstract: A projectile propulsion system comprises a housing defining a chamber, a propulsive charge including a propulsive charge material loadable into the chamber, a projectile loadable into the chamber proximate to the propulsive charge material, an electric pulse discharge subsystem that provides an electric pulse having a specified pulse amperage for a specified pulse period, a current delivery subsystem electrically connecting the electric pulse discharge subsystem to the chamber to deliver the electric pulse to the propulsive charge material, wherein the specified pulse amperage and the specified pulse period are sufficient to cause at least a portion of the propulsive charge material to generate a propulsive force that is at least partially directed onto the projectile to drive the projectile out of the chamber, and a barrel in fluid communication with the chamber configured to receive the projectile as it is driven from the chamber.

Abstract: A cooling system for a cold spray nozzle or a thermal spray barrel and a fabrication method thereof are provided. The cooling system includes a sleeve with cooling fins that encapsulate a spray nozzle or barrel to enable heat transfer from the nozzle or barrel to the fins and then to the external ambient environment. The sleeve may optionally include one or more channels with cooling tubes to enable enhanced cooling with a cooling medium flowing through the tubes and across the fins.

Abstract: A hybrid electrodynamic levitation system that utilizes both superconducting and conductive tracks. The hybrid system reduces the overall drag induced upon the system and reduces the amount of power required to achieve operating speeds, while resolving the issue of requiring velocity relative to the track for levitation. The total initial and operating costs of the hybrid system can be lower than utilizing a superconductive or conductive track alone, while still enabling a fail-safe levitation system for high speed transportation.

Abstract: A recoil managed disruptor includes a disruptor device having a barrel from which a slug of material is fired. A piston is mechanically coupled to the disruptor device. A housing which supports the disruptor on a positioning device includes a deformable recoil absorber (DRA) constraint. The DRA constraint is configured to receive a sacrificial DRA structure comprised of a semi-rigid material. The piston is responsive to a recoil force produced when the disruptor device is fired to travel along an axial length of the housing and permanently deform the DRA structure within the DRA constraint.

Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Abstract: An energy recovery pulse forming network and method that recovers at least a portion of the energy in a railgun by transferring energy dissipated from the railgun inductance back to an initial source of the energy, such as an input capacitor, for use by the network. This reduces the amount of energy required from an external power source to charge the input capacitor during subsequent railgun firings.

Abstract: A power module is disclosed that includes a housing with an interior chamber wherein multiple switch modules are mounted within the interior chamber. The switch modules comprise multiple transistors and diodes that are interconnected to facilitate switching power to a load. In one embodiment, at least one of the switch modules supports a current density of at least 10 amperes per cm2.

Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, and an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of at least one tube, which can be electrically conductive and which can be combined with at least one insulator tube. An electrical energy source, such as a battery bank and associated inductor, can be provided.

Abstract: The present disclosure relates to a launch system, a launch vehicle for use with the launch system, and methods of launching a payload utilizing the launch vehicle and/or the launch system. The disclosure can provide for delivery of the payload at a terrestrial location, an Earth orbital location, or an extraorbital location. The launch vehicle can comprise a payload, a propellant tank, an electrical heater wherein propellant, such as a light gas (e.g., hydrogen) is electrically heated to significantly high temperatures, an exhaust nozzle from which the heated propellant expands to provide an exhaust velocity of, for example, 7-16 km/sec, and sliding electrical contacts in electrical connection with the electrical heater. The launch vehicle can be utilized with the launch system, which can further comprise a launch tube formed of concentric electrically conductive tubes, as well as an electrical energy source, such as a battery bank and associated inductor.

Abstract: The present invention provides a barrel device capable of using various calibers of flanged centerfired ammunition in a breech loaded firearm. The barrel device is able to position and secure various caliber ammunition, whereby the action and firing pin will strike the center of the ammunition and cause it to be fired from the weapon. In some embodiments, the unique barrel device may comprise a non-newtonian type of fluid housed and contained in the barrel by a para-aramid synthetic material. In other embodiments, the barrel device may comprise a mechanical construct and may or may not use a synthetic fiber inner lining. In another embodiment, the barrel device may contain a foam type material to house and center the ammunition. In further embodiments, the barrel device may comprise both a non-newtonian type of fluid and a mechanical construct.

Abstract: The present invention relates to the field of electromagnetic rail launchers, and particularly to a rail launcher and an associated projectile-launching process including at least two longitudinal rails connected to a power supply circuit of these two rails, these rails being at least partially surrounded by superconductor elements able to generate a magnetic induction of a direction perpendicular to the plane formed by the rails and located therebetween during the flow of a current therein, launcher wherein the supply circuit includes the superconductor elements.

Abstract: An apparatus for propelling a projectile. A support structure has a propulsion structure pivotally connected thereto and is movable between an armed position and a disarmed position. In impulse delivery arrangement delivers an impulse force that propels the propulsion structure from the armed position to the disarmed position. A channel is configured to cause the projectile to be in biased contact with the propulsion structure upon the propulsion structure being in the armed position. Wherein, upon the impulse delivery arrangement delivering an impulse force propelling the propulsion structure from the armed position, the propulsion structure propels the projectile through and outwardly from the channel. The channel is selectively adjustable in X, Y, and Z planes to selectively guide the projectile in a generally predetermined direction, upon the projectile being propelled from the channel.

Abstract: A device and method to produce a hot, dense, long-lived plasma. In one embodiment, a large electric current is passed through an outer tube enclosing in part a piston, a notched conducting rod and central electrode. Electromagnetic forces accelerate the piston to a point high enough to mechanically separate the conducting rod at the location of the notch before the conducting rod is melted. On separation, a plasma is generated by the passage of electric current though a gas produced by vaporization of the conducting rod and nearby materials. An insulator enclosed within the tube prevents the plasma from shorting to the outer tube until the current flow has produced a sufficient magnetic field to contain the plasma. The piston is then accelerated by a combination of electromagnetic forces and mechanical pressure from the hot gas through which the electric current is passing.

Abstract: This disclosure relates to launchers and launcher systems for discharging or launching payloads to downrange targets, and associated methods of using such launcher systems. This disclosure further provides methods for attenuating or reducing felt recoil such that relatively large weight payloads can be launched while the launcher is handheld or mounted in any manner. Examples of payloads that can be deployed with the disclosed launcher apparatus include chemical, biological, pyrotechnic, marker, tracer, signaling, non-lethal, anti-personnel, explosive, smoke, and similar payloads.

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: An electromagnetic launcher operable to accelerate launch packages of various transverse sizes, the launcher comprising, in one example, two high-current linear motors having longitudinally extending, laterally open propulsion channels configured to receive and accelerate metal armatures integrated with a launch package; and a power actuated repositioning mechanism for spacing the motors apart as needed.

Abstract: An elongated electromagnetic railgun (1) adapted to propel a moving armature (30) through a bore (11) along the length of the railgun (1) from its breech end (21) to its muzzle end (22). The railgun (1) comprises two elongated mechanically rigid electrically conductive barrel sections (13), said sections (13) being spaced apart from each other along the length of the railgun (1). Mechanically coupled via a dielectric (18) to each barrel section (13) is an elongated current carrying rail (14) for providing electromagnetic propulsive force to the armature (30). The two rails (14) face each other across an elongated open channel, defining the bore (11). The two barrel sections (13) are electrically connected to each other at a maximum of one location of the railgun (1).

Abstract: A railgun launcher with principle rail energization and fielding derived from a co-traveling energy pulse associated with a close-coupled parallel transmission line structure. Enhanced system efficiency, plus amelioration of simple railgun negative features, is enabled via the induction hybrid railgun methodology proposed.

Abstract: Apparatus and methods provide thermal management of a propulsion circuit in an electromagnetic munition launcher.

Abstract: Restraint release devices, systems and methods may enable actuation of a release function without using chemically energetic or thermally sensitive devices, and may employ an electromagnetic (EM) force to mechanically separate components of a fastener. A pulsed power system having a capacitive discharge circuit may be used to supply an electric current pulse to generate the EM force. The EM force can be applied to a retaining wire that surrounds and holds intact a segmented fastener. The EM force may cause the retaining wire to increase in length, thereby relaxing its hold on the segmented fastener and allowing the segments to separate and release the restraint mechanism. Restraint mechanisms using such EM restraint release devices, systems and methods may not need periodic recertification or replacement of energetics and may not have a risk of cook-off resulting from heat soak of thermally sensitive devices during operational and fault scenarios.

Abstract: A system for accelerating an armature to launch a projectile by injecting liquid aluminum between the armature and a pair of electrically conductive rails. A system for accelerating an armature by injecting liquid metal between the armature a plurality of electrically conductive rails and collecting the liquid metal. The liquid metal or liquid aluminum can comprise solid particles. A railgun structure with mechanical guide rails. A railgun structure with a film stack of alternating copper and nickel layers. An armature with guide rail supports. A method of using the system by placing liquid metal in the armature, placing the armature between conductive rails, and applying an electric current to the rails.

Abstract: An electromagnetic railgun (10) comprising at least two elongated high voltage rails (11), a sliding armature (50) making electrical contact with each high voltage rail (11), at least two elongated metal support beams (14) adapted to provide mechanical strength to the railgun (10), said support beams (14) being substantially parallel to the high voltage rails (11), and a plurality of metal support plates (30) aligned circumferentially around the support beams (14) and along the length of the railgun (10), said support plates (30) adapted to provide additional mechanical strength to the railgun (10); wherein the support plates (30) are electrically isolated from each other and from the support beams (14).

Abstract: An improved railgun, railgun barrel, railgun projectile, and railgun system for accelerating a solid-to-hybrid transitioning armature projectile using a barrel having a bore that does not conform to a cross-sectional profile of the projectile, to contact and guide the projectile only by the rails in a low pressure bore volume so as to minimize damage, failure, and/or underperformance caused by plasma armatures, insulator ablation, and/or restrikes.

Abstract: In an electromagnetic rail gun launcher that includes a set of spaced-apart rails defining an inside bore for slidably receiving an armature-type projectile, with the rail gun and armature configured such that when powered up the projectile is forced from a breech of the rail gun toward a muzzle of the rail gun to then launch the projectile, the improvement wherein a lubricant reconditioning pad, containing a lubricant, is secured to the projectile in a location such that it contacts the rails. As the projectile moves through the bore, the pad cleans debris from, and applies lubricant to, the rails to thereby lubricate and recondition the rails during each shot.

Abstract: Embodiments of a canisterized interceptor and method to prevent the launch of a canisterized interceptor that may have been penetrated by small arms fire are generally described herein. In some embodiments, the canisterized interceptor includes a composite canister for housing an interceptor. The canister includes an embedded winding to provide a conductive path and comprises a conductor arranged within composite material of the canister. A maximum spacing may be provided between windings of the conductor and penetration of the canister may be indicated by an open or short circuit in the conductive path.

Abstract: A system for accelerating an armature to launch a projectile by injecting liquid aluminum between the armature and a pair of electrically conductive rails. A system for accelerating an armature by injecting liquid metal between the armature a plurality of electrically conductive rails and collecting the liquid metal. The liquid metal or liquid aluminum can comprise solid particles. A railgun structure with mechanical guide rails. A railgun structure with a film stack of alternating copper and nickel layers. An armature with guide rail supports. A method of using the system by placing liquid metal in the armature, placing the armature between conductive rails, and applying an electric current to the rails.

Abstract: An electromagnetic rail gun launcher for launching an armature attached to a projectile includes a barrel, having a bore, and a body that includes a pair of main rails, a first pair of augmenting rails one of each lying outboard of and coextending with each of one of the main rails from the breech to the muzzle, a second pair of augmenting rails one of each lying outboard of and coextending with one of each of the first pair of augmenting rails, a first pair of electrically-conducting crossovers proximate to the breech and a second pair of electrically-conducting crossovers proximate to the muzzle and connected in series when the armature is positioned in the bore with power provided to the launcher. The exit speed of the projectile from the launcher is controlled by controlling the current to the launcher.

Abstract: Gas guns and methods for accelerating projectiles through such gas guns are described. More particularly, gas guns having a first injection port located proximate a breech end of a barrel and a second injection port located longitudinally between the first injection port and a muzzle end of the barrel are described. Additionally, modular gas guns that include a plurality of modules are described, wherein each module may include a barrel segment having one or more longitudinally spaced injection ports. Also, methods of accelerating a projectile through a gas gun, such as injecting a first pressurized gas into a barrel through a first injection port to accelerate the projectile and propel the projectile down the barrel past a second injection port and injecting a second pressurized gas into the barrel through the second injection port after passage of the projectile and to further accelerate the projectile are described.

Abstract: Gas guns and methods for accelerating projectiles through such gas guns are described. More particularly, gas guns having a first injection port located proximate a breech end of a barrel and a second injection port located longitudinally between the first injection port and a muzzle end of the barrel are described. Additionally, modular gas guns that include a plurality of modules are described, wherein each module may include a barrel segment having one or more longitudinally spaced injection ports. Also, methods of accelerating a projectile through a gas gun, such as injecting a first pressurized gas into a barrel through a first injection port to accelerate the projectile and propel the projectile down the barrel past a second injection port and injecting a second pressurized gas into the barrel through the second injection port after passage of the projectile and to further accelerate the projectile are described.

Abstract: The present invention enables the passive initiation of a deployment sequence for a countermeasure payload. The invention comprises an initiator coil that is positioned inside an electromagnetic countermeasure launcher. When the electromagnetic countermeasure launcher electromagnetically generates propulsive force to propel a payload to its deployment position, inductive coupling between one or more propulsion coils of the launcher and the initiator coil induces current to flow in the initiator coil, which thereby initiates the deployment sequence.

Abstract: A system includes a housing and an electromagnetic coil within the housing. The electromagnetic coil is arranged in a coil stack. A thermal damper is positioned adjacent to the electromagnetic coil, and a thermal structural plate is positioned adjacent to the coil stack. The thermal damper manages temperature rise of the electromagnetic coil and the thermal structural plate provides cooling to the coil stack. In an embodiment, the system is used to launch projectiles.

Abstract: A restraint for immobilizing a projectile with respect to its launch system is disclosed. When electromagnetic force is applied to the restraint, the restraint releases the projectile, thereby enabling its launch.

Abstract: An apparatus for moving a mass, the apparatus having an arcuate track, a clamping member attached to a section of the arcuate track, an arm assembly pivotably connected to the clamping member, and a counterweight connected to the arm assembly. A projectile for use in a mass accelerator having an arcuate track, the projectile having a core and at least one of a low-friction layer, a propellant layer, and a polycarbonate layer.

Abstract: The present invention generally concerns systems and methods for supplying electric power using supercapacitors; and more particularly, representative and exemplary embodiments of the present invention generally relate to improved methods and systems for supplying power to a guided rocket.

Abstract: A system for launching a countermeasure device is disclosed. In the illustrative embodiment, the system uses an electromagnetic catapult to throw a countermeasure payload, wherein the azimuth, elevation, and propulsive force of the electromagnetic catapult are controllable.

Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.

Abstract: Systems and methods for improving the current pulse from multiple pairs of pulsed alternators used for driving large loads such as an electromagnetic launcher (i.e., “rail gun”) load. Conventional current pulse ripples are reduced by interleaving pulses from multiple pairs of contra-rotating pulsed alternators. Current pulses supplied by different pairs of pulsed alternators are timed so that they are interspersed between one another to provide more pulses for a given launch time. The interleaved current pulses increase the frequency and reduce the magnitude of the ripple on the average load current.

Abstract: An electrically powered launcher is disclosed that can accelerate small payloads to orbital velocities. The invention uses a novel geometry to overcome limitations of other design, and allows full exploitation of existing superconducting materials.

Abstract: Launching payloads at high velocity uses high-pressure gas or combustion products for propulsion, with injection of high pressure gas at intervals along the path behind the payload projectile as it accelerates along the barrel of the launcher. An inner barrel has an interior diameter equal to the projectile diameter or sabot containing the projectile. An outer casing surrounds the inner barrel. Structures at intervals attach the outer casing and the inner barrel. An axial gas containment chamber (AGC) stores high pressure gas between the inner barrel wall, the outer casing wall, and enclosure bulkheads. Pressure-activated valves along the barrel sequentially release the high pressure gas contained in the AGC in to the barrel to create a continuously refreshed high energy pressure heads behind the projectile as it moves down the barrel. A frangible cover at the exit end of the barrel allows the barrel to be evacuated prior to launch. The launcher is rapidly recyclable.

Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.

Abstract: An electromagnetic launcher having a longitudinal axis includes a pair of longitudinally extending rails; a pair of longitudinally extending insulators disposed between the rails; a bore defined by interior surfaces of the rails and the insulators; and a jacket extending around exterior surfaces of the rails and the insulators; wherein the exterior surfaces of the insulators are substantially flat and further wherein a distance between the exterior surfaces of the insulators is substantially equal to or less than a maximum thickness of the rails.

Abstract: In an exemplary electromagnetic launcher, a housing with breech and muzzle is slidably supported in a carriage supported on a trunnion. First and second electrical contacts are mounted in the carriage toward an axis of the trunnion. The first and second contacts are electrically connectable to receive electrical power from an electrical power supply. First and second augmentation conductors are disposed aft of the trunnion and are electrically connected to the first and second electrical contacts. First and second main conductors extend from the breech toward the muzzle. A current cross-over connection is disposed toward the breech and electrically connects the first and second augmentation conductors with the first and second main conductors, respectively. The first and second electrical contacts and the first and second augmentation conductors may be engaged in slidable electrical contact over a portion of the first and second augmentation conductors, thereby accommodating recoil motion.

Abstract: An electromagnetic missile launcher is disclosed that provides greater flexibility for use with a variety of missile types and also provides potentially higher performance and efficiency as compared to prior-art electromagnetic missile launchers.

Abstract: A restraint for immobilizing a projectile with respect to its launch system is disclosed. When electromagnetic force is applied to the restraint, the restraint releases the projectile, thereby enabling its launch.

Abstract: A rock pulverizer device based on a superconducting linear motor. The superconducting electromagnetic rock pulverizer accelerates a projectile via a superconducting linear motor and directs the projectile at high speed toward a rock structure that is to be pulverized by collision of the speeding projectile with the rock structure. The rock pulverizer is comprised of a trapped field superconducting secondary magnet mounted on a movable car following a track, a wire wound series of primary magnets mounted on the track, and the complete magnet/track system mounted on a vehicle used for movement of the pulverizer through a mine as well as for momentum transfer during launch of the rock breaking projectile.

Abstract: An electromagnetic launcher comprising, an electric power supply, a conductive, stationary guide operatively connected to the power supply and forming a flowpath for current from the power supply, and a non-conductive projectile disposed adjacent to the guide and which is accelerated along the guide when current flows through the guide. The guide includes a plurality of conductive rails disposed in spaced, substantially parallel relation to each other, a plurality of conductive rungs interconnecting the rails and disposed in spaced relation to each other along the rails, and normally-open switches operatively associated with the rungs for selectively permitting current flow through different ones of the rungs. The projectile includes a main body and a magnet supported by the main body such that the magnet faces the guide with a small gap therebetween.

Abstract: A technique for launching a missile that avoids some of the costs and disadvantages for doing so in the prior art. In particular, the illustrative embodiment of the present invention uses an electromagnetic catapult to throw the missile clear of the launch platform—with sufficient velocity to attain aerodynamic flight—before the missile's engine is ignited.