Abstract: A shaped charge for generating a large hole in material such as well casing downhole in a wellbore. A shaped charge liner is oriented about a longitudinal axis, and a disk is positioned at the liner apex. When an explosive material is initiated the liner collapses into a perforating jet. The disk alters the jet formation process and changes the shape and location of a bulge within the perforating jet. Consequently, the shape of the perforating jet retains a larger diameter for generating a larger hole in the material to be perforated or for controlling the penetration depth. The disk surfaces can be flat, concave, convex or other shapes, and the disk composition can be varied to accomplish different design criteria.

Abstract: The present invention comprises a multiple-component projectile which remains intact after leaving the barrel of a gun. The projectile comprises a core which includes a leading tip and a cylindrical shaft section which extends aft of the tip. A sabot sleeve surrounds the cylindrical shaft section and has a sufficient diameter to engage the rifling on the interior of a gun barrel. A rear cap connects to the aft end of the shaft section and secures the sabot sleeve to the shaft and tip. Preferred embodiments of the present invention comprise an annular lip and slot on the leading tip configured to receive the leading edge of the sabot sleeve and prevent it from separating from the core while traveling through the gun barrel and thereafter. The rear cap may also comprise an annular lip and slot configured to receive the trailing edge of the sabot sleeve and further lock the sleeve to the core thereby preventing longitudinal movement of the sleeve relative to the core.

Abstract: A very highly deformable projectile comprising at least one envelope that is fine, flexible, and elastic, filled with a divided solid substance, deformation thereof occurring only on impact, and of a diameter that is sufficient to limit penetration on impact with energy being rapidly spread out by instantaneous enlargement.

Abstract: The invention relates to a detonator for a pyrotechnical gas generator (3), comprising a squib (9) arranged therein, contact lines (13) for said squib and a high-frequency choke to prevent spurious release, characterized in that the contact lines (13) are extrusion-coated with an electrically non-conducting material (17) or are encapsulated in said material to form a base body, and in that at least one ferromagnetic body (21, 23) and the base body are assembled to form a unit which acts as a high-frequency choke.

Abstract: An initiator (50) for rupturing a burst disk (36) in an air bag inflator (10) includes a body of ignitable material (112) for, when ignited, generating combustion products. A base (52) supports the body of ignitable material (112), and an electrically energizable member (80) for igniting the ignitable material, on the inflator (10). The initiator (50) also includes a cap (90) sealed to the base (52). The cap (90) encloses the ignitable material (112) and maintains the ignitable material in position on the base (52). At least a first portion (94) of the cap (90) is releasable from the base (52) under the force of the combustion products of the ignitable material (112) to enable movement of at least the first portion of the cap away from the base and into engagement with the burst disk (36) to rupture the burst disk.

Abstract: A device for reducing base drag on cylindrical rear truncated objects moving in a fluid, caused by the shedding of vortices at the base of the object. The device consists of ring shaped winglets attached to the rear of the object which may be sub-divided into a plurality of hinged partial winglets. The parameters of distance of winglet from cylinder shaped object, winglet circumference, angle, profile and chord length may be varied automatically for optimum drag-reducing capability.

Abstract: A coordinate transformation apparatus (138) in an aircraft-based missile guidance and tracking system for adjusting aircraft and missile position signals for a roll angle about the line of sight in the guidance and tracking system sight unit (40) caused by roll of the aircraft subsequent to firing of the missile. The apparatus (138) incorporates analog to digital converter means (140), (144), (156), (160) and (180) to convert the analog aircraft and missile position signals to digital signals for input into a microprocessor (168). The microprocessor (168) computes the roll angle as well as a change in roll angle over time around the line of sight of the sight unit (40) and subsequently adjusts the digital signals to compensate for the computed roll angle and change in roll angle. Digital to analog converter means (182), (186) and (190) convert adjusted digital signals to analog signals and output the adjusted analog signals for computation of missile guidance signals by the system.

Abstract: The invention relates to ammunition suitable for firing from a self-loading sidearm comprising a cartridge adapted to fire a projectile, the cartridge case having at one end a portion of reduced diameter, the projectile being held in the said portion of reduced diameter, wherein the ratio of the external diameter of the cartridge case at its widest point to the external diameter of the projectile at its widest point is such that when the projectile is fired into a target high velocity wounding is caused. The invention also relates to a gun barrel for a self-loading sidearm through which the ammunition can be shot, and a self-loading sidearm comprising such a barrel.

Abstract: The hybrid gas generator to inflate airbags comprises two combustion chambers (14, 16), in each of which a solid material charge (15, 17) is placed, and a storage chamber (11) containing a pressurized storage gas. The storage chamber (11) is connected to diffusion chamber (30) by a closing member (29) which can be perforated. The first solid material charge (15), and the second solid material charge (17) can, for instance, can be sequentially ignited by separate igniter elements (18, 19), thereby determining the pressure accumulation.

Abstract: A small caliber shell having armor piercing capacity and extremely high precision. The shell includes a hollow metal shell casing defining an outer shape of the shell. The shell casing has a conical front tip and a rear end, the shell casing comprising an inner surface. An elongate shell core made of an extremely hard and heavy material is centered around a longitudinal axis of the shell between a first bearing surface on the inner surface in the conical front tip of the shell casing and a second bearing surface on the inner surface of the rear of the shell casing and is axially centered inside the shell casing. A support part is arranged inside the shell casing and surrounds at least a very rearmost portion of the shell core for supporting the shell core. A ballast material in the shell casing between the support part and an interior wall of the shell casing holds the support part in place.

Abstract: A firearms safety device in the form of remotely armed ammunition includes a firearms cartridge for use in a use with a conventional firearm having a trigger-actuated hammer with a firing pin. The cartridge includes a firing circuit that is operatively associated with a primer for igniting a conventional propellant charge. A firing sequence is initiated by the impact of the firing pin with the base of the cartridge. An arming circuit allows the firing sequence to proceed to ignition of the propellant only if a receiver within the arming circuit receives an appropriate arming signal transmitted by a remote control module. In the absence of an appropriate arming signal, the cartridge is permanently disabled.

Abstract: Coating composite material sabot parts for reducing depleted uranium corrosion and sealing the surface of a machined composite sabot commences with cleaning the composite material sabot parts. Rinsing the composite material sabot parts, drying the machined composite sabot, and wiping the composite material sabot parts with a solvent follows cleaning. A moisture resistant insulator film is applied on the composite material sabot parts. Excess material is abrasively removed and additional coats are applied. The parts are wiped with a solvent between coats.

Abstract: There is provided a countermeasure defense system against hostile missiles by employing non-explosive intercepting (“NEI”) elements 14 deployed by the spin stabilized rocket 10. The NEI are carried in a payload section 17 and contained by a sleeve assembly 16 which is removed by a drive mechanism 20 or a pyrotechnic device 152 after a countdown time delay programmed into the trigger release assembly 46 as controlled by the control unit 150. The drive assembly includes a drive rod 26 that is releasably held by a release assembly 46 a compressed coiled spring unit 30 drives the sleeve assembly 16 forward exposing the payload section 17 to the centrifugal force of the spin stabilized rocket propelling the NEI elements out from the rocket at constant angular velocity creating an interceptor cloud of elements.

Abstract: A generally cylindrical hydrophone configuration provides compensation for longitudinal accelerations by placing four identical solid piezoelectric transducer elements along its axis with each transducer element being bonded to a head member, two of which are located generally centrally of the cylindrical housing and fastened thereto and two of which are located near the outside edges of the housing and having slight clearance therewith. Flexible polyurethane boots are clamped to the ends of the housing. The volumes between the centrally disposed and outer transducer head members and between the outer head members and the boots are filled with methyl silicon fluid. Each head member is electrically connected to one side of the electrical output, and the junction between the transducer members is connected to the opposite side, both sides being wired to an electrical contact plate located between the two centrally disposed transducer head members, this volume being filled with electrical potting material.

Abstract: An electro-explosive device (“EED”) having resistors fabricated on a thermally conductive substrate and interconnected by a central bridge element. The resistance of the bridge element is lower than that of the resistors, which have a larger surface area to volume ratio. A layer of zirconium is placed on the bridge element and explodes into a plasma along with the bridge element in order to ignite a pyrotechnic compound. The substrate using integrated circuit fabrication techniques and the conductive bridge of the EED is overcoated with a composite overcoat comprising a metal and an oxidizer, which produces a chemical explosion upon plasma vaporization of the conductive bridge.

Abstract: A tracer sleeve having a self-destruction charge, for use with a projectile. The tracer sleeve is screwed into a threaded bore in a rearward end of the projectile. The self-destruction charge is situated in a recess in a forward bottom of the tracer sleeve. A closed bushing bottom in the projectile separates the bore from a more forwardly situated charge member. The recess being a blind bore from the front side of the bottom of the tracer sleeve, and the blind bore being closed by a disc which is sealingly attached in front of the blind bore.

Abstract: Electric primers for the discharge of ammunition suitable for use with small arms.

Abstract: A training rocket for smoke development. The training rocket includes a rocket tube which contains powder and constitutes a propulsion motor for the rocket. The rocket includes a forward training head which contains a smoke composition adapted to emit visible smoke upon impact. An igniter charge, such as a tracer charge, which can be ignited by the propellant powder is situated in the rearmost of the training head, behind a bursting charge which can be ignited by the igniter charge. The igniter charge and the bursting charge are situated behind the smoke composition in the training head, for igniting the smoke composition, in a capsule which can be forced rearwardly from the training head due to the increased pressure caused by combustion of the smoke composition, whereby an aperture is formed for passage of smoke gases rearwardly in the rocket, through the rocket tube and out of it.

Abstract: A locking device is provided for preventing adjacent threaded fasteners from rotating while not bearing any of the preload stress of the fasteners. The locking device includes: a plurality of locking rings, each locking ring being of sufficient diameter to surround the sides of one of the adjacent fastener heads and wherein each locking ring is made from a pliable material such that the locking ring may be deformed to closely fit its associated fastener head; and a torque member, connected to each locking ring, for providing torque to prevent each locking ring and its associated bolt head from rotating.

Abstract: A clockspring including a housing, a hub, and flexible printed wiring. The flexible printed wiring electrically connecting the hub to the housing. The hub mounted in the housing. The hub being able to rotate relative to the housing. The flexible printed wiring able to be affixed with components such as resistors, capacitors, inductors, and integrated circuits.