Abstract: Carbon fiber material and carbon fiber material that is saturated with hydrocarbon solid-liquid phase change material may be used as thermal management materials for providing a thermally conductive interface between a heat source and its housing. Such carbon fiber material may also be used for mechanical isolation of the heat source from its housing. Carbon fibers used in the carbon fiber material may be unidirectionally oriented to provide for low friction, thus optimizing critically controlled friction tolerances. Additionally the carbon fiber material saturated with hydrocarbon solid-liquid phase change material may be used to transfer heat into the an inherently nonconductive medium.

Abstract: A lightweight aerosol dispenser enclosing a first component of an explosive nature is filled at a factory. A second component is supplied in a smaller container, separate from the dispenser, containing a predetermined amount of propellant. By providing separate containers for each of the explosive and propellant components, both components retain their classification as a flammable substance for transportation and storage purposes. However, in the field, the propellant is injected into the solution container immediately before use. Only after the two substance components have been mixed can an explosive composition be produced. If, for any reason, the explosive composition comprising a foam is not used, it can be washed away with water or will dissipate itself within a few hours.

Abstract: Anti-armor projectiles comprising a main projectile having a single warhe and an additional autonomous precursor warhead which is stowed with the main projectile and attached to the main projectile just before firing, thereby providing a tandem warhead capability and improved lethality for the main projectile. The attachable precursor warhead is packaged with the main projectile so that the length and diameter of the main projectile is not increased while it is stored and until the autonomous precursor warhead is attached just prior to firing. The autonomous warhead may be a chemical energy (CE) warhead or a kinetic energy (KE) warhead so that when attached to existing CE warhead or KE warhead projectiles, tandem CE-CE, tandem CE-KE, tandem KE-KE, or tandem KE-CE warhead projectiles are created. The autonomous, attachable warhead is completely self-contained and prior to firing is affixed to and stowed adjacent the main projectile without exceeding the length and diameter constraints of the main projectile.

Abstract: In accordance with the present invention, a store covering for reducing the radar observability of an externally mounted store is provided with a non-rigid body covering. The body covering is provided with a radar reflective material. The body covering is formed to fit around a portion of the externally mounted store. The body covering is in slidable engagement and disengagement about at least a portion of the externally mounted store to allow repeated installation and removal.

Abstract: A weapon transport device transports along a path toward a target in hostile territory, (1) a target-intended weapon and (2) biological, chemical and/or radioactive agents for attacking the occupants of such territory should they execute countermeasures against the weapon transport device. Separation of the biological, chemical and/or radioactive agents is initiated or, where appropriate, inhibited, by signals from either the guidance system of the transport device or from on-board Global Positioning System (GPS) receivers when the transport device strays by more than a predetermined distance from the path, the sensor is blinded, or the transport device passes beyond a predetermined point while en route to the target.

Abstract: The present invention provides a viable, practical and useful alternative to conventional metal barbed wire that is both portable and easily deployed and has a long storage shelf life. This alternative is a cost effective alternative to metal barbed wire that is reusable, recyclable and unaffected by climactic conditions. There present invention also provides a means for rapid deployment of a permanent or temporary barrier for situations as varied as repairing a breach in a fenced enclosure or providing a no-cross zone in event of civil disturbance. This means is a self-deploying storage canister for the plastic barbed wire which uses a explosive charge for deployment.

Abstract: An ignition system for an ammunition-bearing unit includes at least two casings, an inner and an outer casing, which are arranged to at least partially surround each other and are intended to undergo deformation upon striking a target and thus establish electrical contact, and a detecting unit for detecting when electrical contact is established and for, upon actual striking of the target, emitting at least one initiation signal for triggering the charge of the anmunition-bearing unit. At least one of the casings includes plurality of sections which are spaced around its periphery and which are electrically insulated from each other and, upon deformation of the casings establish an individual electrical contact with the opposite at least one part of the at least one other casing.

Abstract: An projectile and method of using same employ a projectile body; an electric circuit housed within the projectile body; a plurality of electrodes, coupled to the electric circuit, for delivering an electrical shock to the target; and attachment means, coupled to the projectile body, for attaching the projectile to the target.

Abstract: A hard-target penetrating warhead (10) adapted for use with length constrained warhead payload bays. The warhead (10) includes a warhead case (12) for containing warhead explosives (22, 27). A tungsten ballast (16) is disposed within the case (12) for providing a high warhead sectional pressure upon impact of the warhead (10) on a target. A fuse (19) detonates the warhead explosives (22, 27) upon penetration of the target. The fuse (19) is housed by a fuse well (18) that is attached to the case (12) at one end. A slip fit section of the fuse well (18) provides structural support to the case (12) and prevents dislodging of the fuse well (18) and the fuse (19) from the case (12) upon warhead target impact. Explosives blowout ports (24) included in the fuse well (18) inhibit undesirable explosion or detonation of the warhead explosives (22, 27) by accidental exposure to high heat or fire. In a specific embodiment, the case (12) has a 6 caliber radius head nose (14).

Abstract: An improved shoot-through warhead cover is constructed of a low density material, such as polyethylene foam, in a dome-like shape. An anterior surface of the shoot-through cover is configured so as to be in proximate mating relationship with the exterior surface of an EFP liner member. The exterior surface of the cover is also aerodynamically contoured to match the external shape of a receiving warhead delivery vehicle body.

Abstract: A ballistically deployed restraining net system including a cartridge receivable within a barrel, the cartridge having a base and an opposing open end. There is a restraining net packaged in the cartridge and a set of weights attached to the restraining net and packaged within the cartridge between the base of the cartridge and the restraining net. A deployment charge ejects the restraining net and the set of weights out of the barrel and out of the cartridge and a spreader charge deploys the weights after the net and the set of weight exit the cartridge so that the weights overtake the net in flight.

Abstract: A missile having an improved dome mounting arrangement, and a method for mounting a sapphire dome to a titanium missile turret that provides for minimum surface deformation and environmental sealing of the dome. A sealing material such as silicone rubber compound that is capable of enduring high temperatures attained during high speed missile flight is employed. The missile has a body with a nose and the dome mounting arrangement is attached to the nose. The dome mounting arrangement comprises a turret secured to the nose, the dome, and a retainer ring attached to the turret for securing the dome to the turret. An annular gap is formed between an outer surface of the dome and an inner surface of the retainer ring. The silicone rubber compound is disposed in the annular gap and cured to seal the dome. A plurality of shims may be disposed between the dome and the turret in a radial gap formed therebetween.

Abstract: A range correction module which is designed to fit onto a spin stabilized llistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, sixteen semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: A range correction module which is designed to fit onto a spin stabilized ballistic projectile for correcting range error. The range correction module is a self-contained module within the fuze which screws into the forward portion of the projectile. The range correction module is designed such that changes are not required to the existing projectile. During the course correction phase, semi-circular plates will deploy from the module. The plates create a blunt cross-sectional area in front of the projectile, thus creating more drag and effectively slowing the projectile.

Abstract: The present invention pertains to a device with nonlethal interference active bodies for combating aircraft, which violate or do not heed flight bans, etc., and can be forced to land due to vibrations and interferences in the air current on the aerodynamic surfaces. A series of embodiments are described and depicted in the figures of the drawing.

Abstract: Rapidly deployable restraining systems and methods for rendering personnel, nimals and other objects immobile includes an assembly of confinement devices housed in a dispersion package. Each confinement device has a propellent, a primer and an inflatable bag that is rapidly inflated by the propellent when fired by the primer. A detonator, located in the package, is discharged to open the package, disperse the confinement devices and cause the primers to be energized, thereby inflating the bags. The package is pre-emplaced in a target area or it is projected into the area via a fired projectile of which it is a part.

Abstract: A barge strike system for clearing an obstacle-filled region of water inces a floating barge having at least one hollow region defined therein. The barge is equipped to move under its own power to the obstacle-filled region at various speeds, including speeds in excess of minimum planing speed. Explosive material is contained in the barge's hollow region(s). A plurality of detonators are coupled to a top surface of the explosive material and are initiated to generate a coalesced planar wave downward through the explosive material.

Abstract: A non-lethal incapacitating device comprises a pair of projectiles and trailing wires packaged in a cartridge mountable on the head of a stungun. The cartridge assembly includes a pair of light and directionally stable and non-invasive projectiles having tubular plastic flares, expanded trailing wire coiled in double layers on a rotating magazine, a simple gas capsule side-piercing mechanism, and a compact housing.

Abstract: A device for imparting non-explosive and non-propulsive properties to a warhead during a slow cook-off test, which comprises a pyrotechnic pellet located inside a tube having a predetermined ignition temperature of at least 130.degree. C. but below the violent ignition temperature of the material under slow cook-off conditions, whereby the venting holes present in the aft closure of said tube, are covered by a composite material that loses its strength below the predetermined temperature, causing a pressure relief and a non-propulsive burning of said warhead.

Abstract: A method for converting mortar shells into shells for use in smooth-bore gun barrels having an interior surface. The mortar shells include a warhead having a front end, a rear end, a tail fin, and a propellant charge. A guide casing is attached to at least the rear end of the warhead. The guide casing includes an outside surface. The guide casing supports at least the rear end of the warhead and is adapted for use with the smooth-bore gun barrel that the converted shells are to be fired from. A bourrelet is attached to the outside surface of the guide casing for sealing between the converted shells and the interior surface of the smooth-bore gun barrel that the converted shells are to be fired from.

Abstract: Technology for in situ remediation of undetonated explosive material. A bioremediating apparatus in the form of a storage chamber houses in moist condition type of microorganisms capable of metabolizing the explosive material. Examples of such microorganisms include Pseudomonas spp., Escherichia coli, Morganella morganii, Rhodococcus spp., Comamonas spp., and denitrifying bacteria. The bioremediating apparatus is joined with an explosive apparatus that houses a charge of explosive material. A solution released into the storage chamber by opening a first valve hydrates the microorganisms. The explosive assembly has an actuation means for opening the first valve and a second valve that releases the microorganisms from the storage chamber to begin metabolizing the explosive material, when the explosive apparatus is joined with the bioremediating apparatus. If the explosive material fails to detonate, the explosive is remediated by the action of the microorganisms.

Abstract: A ballistically deployed restraining net system including a projectile, a net packaged in the projectile, a net deployment device for unfurling the net in flight, and a fuze for triggering the net deployment device upon the occurrence of a preestablished criteria such as the impact of the projectile with an object, the expiration of a preestablished time period after launch or upon the projectile reaching a predetermined distance to an object.

Abstract: Technology for in situ remediation of undetonated explosive material. A bioremediating apparatus in the form of a storage chamber houses in moist condition type of microorganisms capable of metabolizing the explosive material. Examples of such microorganisms include Pseudomonas spp., Escherichia coli, Morganella morganii, Rhodococcus spp., Comamonas spp., and denitrifying bacteria. The bioremediating apparatus is joined with an explosive apparatus that houses a charge of explosive material. A solution released into the storage chamber by opening a first valve hydrates the microorganisms. The explosive assembly has an actuation means for opening the first valve and a second valve that releases the microorganisms from the storage chamber to begin metabolizing the explosive material, when the explosive apparatus is joined with the bioremediating apparatus. If the explosive material fails to detonate, the explosive is remediated by the action of the microorganisms.

Abstract: An electronic projectile (10) for use with a standard cartridge (1). Projectile (10) and cartridge (1) are loaded into standard firearms and fired like a standard bullet. After leaving the barrel of a firearm, plastic sheaths (8L) and (8R) fall away and electrodes (19L) and (19R) extend outward on wires (40L) and (40R). On impact the electrodes penetrate the skin of the target making electrical contact with internal tissue of a target. Within projectile (10) a battery (50) powers internal electronics (30) to charge output capacitors (22) and (24) to high voltage. When the capacitors are fully charged a switch (58) completes the circuit and discharges the capacitors through the target. Switch (58) discharges the capacitors 20 to 100 times per second. These pulses continue for several seconds to incapacitate the target. The polarity of the current is changes once or twice per second to alternate between acidic and basic ions being formed around the electrodes to sterilize the puncture sight.

Abstract: A dome subassembly (10) for missiles consists of a dome (12) and a holding ring (14) connected thereto, The dome (12) is made of sapphire. The holding ring (14) is made of oxide ceramics reinforced by fibre or whisker. Dome (12) and holding ring (14) are connected to each other by brazing. Two brazing methods are indicated.

Abstract: A filler combined with a quick-setting adhesive such as a cyanoacrylate asive, or an anaerobic adhesive forms an adhesive composite having high compressive strength suitable for immobilizing a mechanical fuze.

Abstract: A resupply projectile is described which can deliver critical logistic supplies rapidly and accurately to forward combatants with minimum risk to supply personnel or equipment and which is not hampered by either weather or terrain.

Abstract: A device for detecting and neutralizing an explosive device concealed in cargo by directing a plurality of energies or fields including electromagnetic, electrostatic, magnetic, or acoustic toward the cargo thereby externally inducing detonation. A blast containment enclosure is used to protect surroundings by containment and redirection of a resulting explosion. A method for the detection and neutralization of explosive devices is also provided.

Abstract: A rocket-fired visual signalling apparatus and method includes a rocket, an elongated streamer having a first end portion connected to the rocket and a rocket launcher for launching the rocket so that the rocket pulls the streamer into the air such that when the rocket burns out, the streamer is spread out over the surrounding ground cover to facilitate visibility of the streamer.

Abstract: Rapidly deployable restraining systems and methods for rendering personnel, nimals and other objects immobile includes an assembly of confinement devices housed in a dispersion package. Each confinement device has a propellent, a primer and an inflatable bag that is rapidly inflated by the propellent when fired by the primer. A detonator, located in the package, is discharged to open the package, disperse the confinement devices and cause the primers to be energized, thereby inflating the bags. The package is pre-emplaced in a target area or it is projected into the area via a fired projectile of which it is a part.

Abstract: The non-explosive core of a reentry projectile is fixedly positioned within hollow casing of the projectile at a location maximizing conversion and transfer of kinetic energy to an earth bound target in response to the projectile's impact at a hypersonic velocity and at a steep impact angle to the surface of the earth. The hollow casing is formed of a material capable of withstanding high temperatures, therefore, not requiring any cooling and allowing for the hollow casing to be free of heat transfer medium that might otherwise impede the desired quick release of the core upon impact of the projectile. The core is in the form of a single dense metallic slug having a mass establishing a center of gravity and moments of inertia for the projectile as a kinetic energy warhead corresponding to that of an explosive or nuclear warhead without weapon system modification.

Abstract: An explosive device for attachment to a user engaged in underwater demolition operations is disclosed comprising, in combination, an explosive charge, a buoyant carrier for carrying the explosive charge, and a detonator for detonating the explosive charge. The buoyant carrier includes a variable ballast pouch containing lead shot which can be removed therefrom using a control valve, thereby permitting fine control of the overall weight of the explosive device. The buoyant carrier also includes a plurality of magnets and/or suction cups for permitting the explosive device to be attached to a swimmer's backpack or to either a target surface.

Abstract: To mitigate groove drag in a kinetic energy projectile, an intumescent maial is inserted in the grooves wherein the material will expand to fill the grooves once the sabot has been discarded. The groove material inhibits aerodynamic recirculation that can occur in the grooves, fills the groove and keeps out freestream gasses. The expanding groove material occupies the space previously filled by the sabot tooth. The groove-filling material expands quickly, because the flight of the projectile is typically on the order of one to two seconds. The groove filling material may also be an elastic material.

Abstract: In a set of airbag igniters, each igniter has a mounting ring connected to and surrounding a portion of its body. Each igniter is supported in a retainer having an X-ray permeable wall surrounding the mounting ring. The mounting ring has a radially outwardly facing surface having a pattern of annular grooves hidden from visual inspection by the wall of the retainer. The pattern of grooves is the same for all of the igniters in the set having the same sensitivity, and any two igniters in the set having different sensitivities have different patterns of grooves. The grooves are inspected automatically by X-rays.

Abstract: A single-use firing indicator device for a projectile having a hollow rear extension includes a stopper and an indicator member. The stopper is shaped to at least partially cover the rear extension of the projectile. The indicator member is connected to the stopper and may secure the firing indicator device to the projectile. Removing the firing indicator device to prepare the projectile for firing requires permanently deforming the indicator member. As a result, the firing indicator device reliably conveys the firing status of the projectile without requiring costly modification or added parts.

Abstract: Explosive composition, and method for its manufacture, based on an essentially particulate mixture containing a solid oxidizing salt and optionally a fuel, wherein at least a part of the oxidizing salt contains ammonium ion. The mixture contains an additive of acid and may be used in environments with risk of ammonia liberation.

Abstract: A bomb damage assessment system that is carried by a weapon and released to provide imagery of a bombed area before and after bomb delivery. The system comprises a glider that is releasably secured to the weapon that includes tracking and guidance electronics for programmably controlling the flight thereof. An imaging system is disposed in the front end of the glider and a deployable ballute is disposed at the rear end thereof. A data link is provided for transmitting images to a command center for review. The system provides imagery of a target area before, during and after weapon impact. Television or infrared cameras may be used for day or night missions. As a target area is approached, the glider is released, is decelerated by the ballute, wings are unfolded, and the ballute is released, resulting in an aerodynamic vehicle that flies much slower than the weapon. The imaging system tracks the weapon to impact. The explosion of the weapon produces a hot spot that is tracked by the imaging system.

Abstract: An autonomous bomb damage assessment system that is piggybacked to a bomb to provide imagery of a bombed area immediately after bomb delivery. The bomb damage assessment system comprises a housing that is releasably secured to the bomb. An imaging system is disposed at one end of the housing and a folded inflatable balloon is disposed at the other end of the housing. An inflation device is provided for inflating the balloon with a lighter-than-air gas such as helium. A proximity fuze is used to sense the location of the ground, for causing the system to be ejected away from the bomb shortly before bomb impact, and for causing the inflation device to inflate the balloon. A data link is disposed in the housing for transmitting images derived from the imaging system to a remote location. The present invention provides imagery of a bombed area immediately after bomb delivery. The lighter than air characteristic of the system allows a dwell time over the bombed area so debris and dust can settle.

Abstract: A process for photolytic degradation of the organic and nitrogenous components of high explosives in organic solvent is described. The process can be applied with a module photolytic apparatus so that munitions can be destroyed without endangering the environment or toxifying large quantities of water. An apparatus is also disclosed.

Abstract: A munition which remains uninitiated after deployment undergoes a process of self-neutralization. This process is accomplished through the use of environmentally degradable materials in the construction of the ordnance items. The degradable components comprising the device fail in a predetermined manner and within a known time frame. The resultant neutralization may be manifested in a myriad of ways. The type of degradable material, its position within the munition, its mass, and many other factors, will all determine the ultimate characteristics of the device.The neutralization may be realized through detonation, burning and, disassociation of interactive components which will cause deactivation, reduced lethality or intensity of the device, dispersion of the main charge, or the dispersion of one or more of the initiation charges comprising the munition.

Abstract: A clip for the retention of a round of ammunition in a desired position in a barrel is described, the clip being manufactured from a plastics material and comprising a generally cylindrical body portion; the body portion having a plurality of generally radially and axially directed grooves therein, said grooves being adapted to engage the tail fins of an associated round of ammunition; engagement means extending at least part of the way around said body portion, said engagement means having a greater diameter than that of the body portion and being adapted to engage with a recess at the breech-end of an associated gun barrel to prevent forward movement; and a substantially central aperture to allow access to the propellant charge of the associated round of ammunition.

Abstract: An anti-missile missile for preventing an incoming threat missile from impacting a target without requiring impact of the anti-missile missile with the incoming threat missile. The incoming threat missile is provided with a guidance and control system disposed for receiving a source of guidance energy from an external source for guiding the threat missile to impact with the target. The anti-missile missile includes a body having a container carried thereby and a shield device carried in the container for ejection from the container in the vicinity of the threat missile. The shield device is disposed for controlling the amount of guidance energy received by the guidance and control system thereby rendering the guidance and control system ineffective to guide the threat missile to the target. An ejection device is provided for ejecting the shield device in the vicinity of the threat missile.

Abstract: An expandable ogive is disclosed which incorporates a plurality of sections (20, 22, 24) which move into an extended position. The ogive is locked in the extended position by mating tapered surfaces on the piston sections of an actuator (44) which are tapered at an angle of less than about 2.degree. relative to the center line axis of the missile or rocket. The mating surfaces lock sufficiently tightly to resist the aerodynamic loadings on the ogive during missile or rocket flight and therefore maintain the proper ogive configuration independent of the gas pressure in the actuator (44) which initially moves the ogive sections into the extended position.

Abstract: An integral missile antenna-fuselage assembly (50) is provided for integration into an armament missile (12) which carries primary missile loads, houses internal electronic assemblies, provides mounting surface zones for external sensor antennas (71) , and protects sensitive antenna components from supersonic aerodynamic heating. Each end of the fuselage assembly (50) is formed from a fastener ring (52,54) having a circumferential recess (84,86) which receives a filament wound main structure (60) to form the missile fuselage tube. Preferably, a titanium liner (58) is first joined to each fastener ring with a step-lap joint (94,96) along which it is adhesively bonded. The liner (58) and adjacent fastener ring portions (52,57) provide a mandrel on which a graphite/Bismaleimide (BMI) resin pre-preg is filament wound and co-cured to form the integral fuselage (60).

Abstract: A wedging device includes bars evenly distributed at an angle. Each bar has a bearing surface designed to come into contact with an internal surface of the envelope and two holding surfaces designed to come into contact with at least two adjacent sub-munitions. Each bar is divided into at least two half-bars that contact one another by at least one slanted guiding surface. By relative sliding of each half-bar, the two holding surfaces forced apart in such a way as to eliminate any radial give in the sub-munition assembly within the envelope.

Abstract: A flexible, aerodynamic inflatable nose fairing for use in combination with flat nosed canister-launched missiles having a wide, circular, cylindrical shape. The inflatable nose fairing is fabricated as a fiber-reinforced elastomeric membrane having a laminate construction which includes a silicone rubber inner or base layer as the gaseous pressure membrane or bladder, surrounded by two or more ply layers made up of resin-impregnated yarns. Also disclosed is a deployable mass assembly and sensor for providing improved missile control. The deployable mass assembly includes a telescoping actuator which is effective to provide stabilization control to the missile by shifting the center of gravity of the missile forwardly to compensate for a change in the center of pressure of the missile due to the change in length of the missile which occurs as the nose fairing is inflated into its deployed position.

Abstract: A flexible, aerodynamic inflatable nose fairing for use in combination with flat nosed canister launched missiles having a wide circular cylindrical shape. The inflatable nose fairing is fabricated as a fiber-reinforced elastomeric membrane having a laminate construction which includes a silicone rubber inner or base layer as the gaseous pressure membrane or bladder, surrounded by two or more ply layers made up of resin-impregnated yarns. In a preferred embodiment, the silicone rubber bladder is applied to a generally conical shaped mandrel. The first ply layer is fabricated by hoop winding resin impregnated yarns on a constant diameter cylinder and then cutting to form gores. The gores are applied to the conical shaped mandrel such that the gore fibers are oriented in the axial direction of the conical shaped mandrel.

Abstract: A flexible, aerodynamic inflatable nose fairing for use in combination with flat nosed canister launched missiles having a wide circular cylindrical shape. The inflatable nose fairing is fabricated as a fiber-reinforced elastomeric membrane having a laminate construction which includes a silicone rubber inner or base layer as the gaseous pressure membrane or bladder, surrounded by two or more ply layers made up of resin-impregnated yarns. In a preferred embodiment, the silicone rubber bladder is applied to a generally conical shaped mandrel. The first ply layer is fabricated by hoop winding resin impregnated yarns on a constant diameter cylinder and then cutting to form gores. The gores are applied to the conical shaped mandrel such that the gore fibers are oriented in the axial direction of the conical shaped mandrel.

Abstract: A gun launched projectile design which imparts forces to a subcaliber protile comprising: a subprojectile, a multi petal sabot, a pusher plate, and an obturator. The petals are of different length and have a scooped-out design on the face thereof, so as to induce a specific level of yaw to the projectile.

Abstract: A connecting assembly serves for connecting a dome covering a seeker head with the structure of a missile. A holding ring extends over the rim of said dome, positively holding this dome and connected with the structure of the missile. An annular recess is provided underneath the holding ring along the rim of the dome. This recess contains a flexible sealing substance for establishing a seal between the holding ring and the dome. It is important, that no additional material bonding such as cementing or soldering is provided between the dome and the holding ring.