Abstract: Embodiments may take the form of a perforating gun of modular assembly. The perforating gun may include at least one centralizing member at an interface between a loading tube and a carrier. Among modular components, the gun may also include an initiator assembly module that is electrically coupled to a modular feedthrough with a connector. The insert and the centralizing member may enhance axial cohesiveness of the modular gun. A shock absorbing mount may be located within the carrier and may receiving the initiator assembly module to provide added axial cohesiveness to the modular gun.

Abstract: A smoke detector system 20 is disclosed, including a beam detector unit 10 having a moveable portion 14 comprising at least one light transmitter 16, a base portion for fixing to a surface, and a motor configured to rotate the moveable portion 14 relative to the base portion. The system also has at least one receiver for detecting light transmitted by the transmitter.

Abstract: A gatebox for an aircraft comprises an opening operable to allow material to flow out of the gatebox, a hopper operable to direct material in the gatebox to the opening, a door coupled to the hopper and operable to move between an open position and a closed position by sliding along a surface of the gatebox, wherein the door comprises a front edge, a rear edge wider than the front edge, and at least two side edges that taper between the front edge and the rear edge, and a seal coupled to the hopper and operable to, when the door is in the closed position, engage the edges of the door and compress to prevent material in the gatebox from being released through the opening along the engaged edge of the door.

Abstract: An apparatus for correcting trajectories variations of projectiles launched from a firearm is disclosed. The apparatus includes a control circuit for determining an appropriate impulse to be imparted into a projectile based on the measured velocity of the projectile, at least one steering coil, and a pulsed-power supply for discharging an amount of energy commensurate with the determined impulse to the steering coil such that a set of magnetic fields is produced to impart an amount of corrective kinetic energy into the projectile as the projectile passes the steering coil.

Abstract: A hand grenade comprising a detonator, an explosive charge having a periphery, a hollow shell having an inner surface and an outer surface, an electronic circuit, and a power source. The hand grenade has at least two environments of control.

Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

Abstract: A method for deploying a control surface from an exterior surface of a spinning projectile during flight is provided. The method including: moving the control surface in an interior of the projectile such that a portion of the movement retracts the control surface into the interior and a portion of the movement extends the control surface from the exterior surface of the projectile; determining a roll angle of the projectile; and synchronizing the movement of the control surface with the roll angle of the projectile.

Abstract: A means of increasing the velocity of projectiles using multiple charges ignited at different times to facilitate a sustained pressure pulse in the barrel is provided. The propellant charges are separated with one or more rigid barriers and ignited in series; igniting the propellant nearest to the projectile first and the propellant that is farthest from the propellant last. By timing the ignition of the charges a higher average pressure is sustained in the gun tube without risking a breach blow. After the peak pressure of the first propellant charge is reached the second propellant is ignited. The energy of the second propellant causes the pressure in the gun tube to fall more gradually. Thus the average pressure that acts on the projectile is safely increased. The following includes several methods of accomplishing this.

Abstract: The present invention relates to a penetration assistance kit fitted to a bomb, notably an anti-infrastructure bomb. The kit includes launch tubes mechanically secured to the bomb. In each of the launch tubes is positioned a detonating projectile and its propulsive charge. A detonating projectile can be ejected from its tube by initiation of its propulsive charge. A system is provided for controlling the initiation of each propulsive charge prior to impact of the bomb with a target. The invention applies notably to the penetration of very thick walls made of non-metallic material such as concrete, for example. The invention also relates to a penetrating projectile equipped with such a kit and to a method of getting such a projectile to penetrate a target.

Abstract: A projectile deployment system for use in intercepting a target (32) wherein the system includes a body (10) defining a body axis, and a number of barrels (30) circumferentially spaced around the body axis. Each of the barrels (30) contains a number of projectiles (31) axially stacked therein, with a corresponding number of charges being provided such that each charge is associated with a respective projectile (31) along barrel (30). Each of the charges is individually activated to deploy a respective projectile (31) in response to a signal from a controller.

Abstract: A projectile (10) for firing from a barrel, said projectile including a multiplicity of barrel assemblies (12, 13, 14) radially disposed from the centre of mass of the projectile, wherein each of said multiplicity of barrel assemblies includes a plurality of sub-projectiles (16) axially disposed within a barrel; each of said sub-projectiles associated with a discrete propellent charge (17) for propelling a respective sub-projectile from the barrel, wherein said projectile is capable of selectively firing sub-projectiles (16), suitably with the aid of primers (18) each coupled to an electronic controller (15). to provide a predetermined pattern of deployed sub-projectiles. A defence system employing projectiles of the type described is also disclosed, together with a method for disguising the launch location of a projectile utilising divert propulsion.

Abstract: An explosively driven impactor grenade includes a grenade body having a substantially spherical shape and a hollow central portion, the grenade body including a plurality of recesses formed on an external surface thereof with each recess including an opening into the hollow central portion of the grenade body, the grenade body including an opening on the exterior surface that connects with the hollow central portion; a fuze disposed in the hollow central portion of the grenade body; a fuze cap for closing the opening on the exterior surface that connects with the hollow central portion; and a plurality of explosively driven impactors respectively disposed in the plurality of recesses formed on the external surface of the grenade body, the explosively driven impactors being connected to the fuze through the recess openings into the hollow central portion of the grenade body.

Abstract: An anti-missile missile (10) includes a missile configured to track and intercept an incoming missile travelling along path (12). Missile (10) includes at least one barrel assembly (13) having a multiplicity of projectiles stacked axially within barrel assembly (13), together with discrete selectively ignitable propellant charges for propelling the multiplicity of projectiles sequentially through the muzzle of barrel assembly (13). The multiplicity of projectiles produce a fragment column (20) along path (12) to destroy the incoming missile. Alternatively, anti-missile missile (10) can be guided to produce a direct hit at point (18) on the incoming missile. Barrel assembly (13) can include an aiming mechanism so that barrel assembly (13) can be rotated through sector (15, 16) to target path (12).

Abstract: A multiple module EFP warhead comprises a tubular body having a central axis with a plurality of explosively formed penetrator modules arranged tandemly within the body along the axis. Each of the modules includes a curved, dish shaped support disk having a unique forwardly convex curvature. The support disk is focused on the axis at a point behind the module. Each module has a set of circumferentially spaced apertures therethrough, each having a central aperture axis intersecting the central axis. Each aperture supports a separate ductile metal disk therein and an explosive charge behind and against the metal disk. Each of the aperture axes forms an acute angle of inclination with the central axis which is uniquely offset from the axes of the other modules so that each EFP travels along a unique forward path.

Abstract: A projectile has a nose portion and a body portion. A plurality of winged, fin-stabilized flechettes are releasably mounted in the body portion. Each flechette is mounted with its longitudinal axis at a pre-set pitch to a longitudinal axis of the projectile. In use, with the projectile moving on a projectile trajectory, each released flechette follows a respective trajectory parallel to and at a predetermined distance from the projectile trajectory. The predetermined distance for each flechette is determined by its pre-set pitch to the longitudinal axis of the projectile.

Abstract: Coating compositions containing identifier particles are disclosed for the retrospective identification of articles. The compositions comprise a clear lacquer binder, visually-readable microparticles and reflective spotting particles. The reflective spotting particles facilitate location of the coating on the surface of the tagged article.

Abstract: A method is provided for destroying a target that includes dispersing submunition fragments in an array that is directed to intercept the target, and engaging said fragments to collide against an outer shell of the target, wherein said array distributes said fragments as having a ratio between a characteristic length of said fragments and a separation distance of at most 2.5 and a collision velocity of between 1.8 km/s 2.0 km/s. The ratio is preferably at most 1.9. The characteristic length corresponds to a spherical radius of the fragment. Each fragment has a mass between 150 grains and 300 grains. The array is preferably aligned to intercept the target at an angle offset by between 15° and 45° from perpendicular to a longitudinal axis of the target. Each fragment has a preferable shape of a prism, a trapezoid or a pyramid.