Abstract: An ignition device (1) for military or police used having a mechanical trigger (2), a shock tube (3) of variable length, blasting cap (4), whereby the blasting cap (4) with the trigger (2) and the shock tube (3) are accommodated in a protective pipe (8) sealed at both ends by means of sealing discs (13) or end plates (10). The shock tube (3) surrounds the trigger (2) and blasting cap (4) and so can be easily pulled out of the protective pipe (8) after the locking device (16, 52) is released. The protective pipe (8) is enclosed in a shrink sleeve (34), as is the shock tube (3), so that the system is suitable for underwater use as well.

Abstract: The Spin-stabilized Projectile for Smoothbore Barrels would provide for improved accuracy and a flatter trajectory in comparison tot current Foster design projectiles or statically stabilized finned projectiles. The method achieved for spin stabilization here can easily be up-scaled for larger caliber artillery projectiles for when a spin-stabilized projectile is desired from a smoothbore weapon.

Abstract: A system and method for guiding a projectile is presented. A method for guiding a projectile includes storing a gas in a chamber that is attached to the projectile. The projectile has an explosive front end and a rear guidance kit consisting of a body extension and a tail boom. The chamber is located in the body extension with the control electronics. Two or more fins that are configured to stabilize the projectile while the projectile is in flight. Pulses of gas are released out of the chamber through a nozzle at the end of the tail boom to control an angle of attack to control the lift of the projectile to guide the projectile to a target while the projectile is in flight.

Abstract: A system and methods for fluid dynamically controlling a projectile are disclosed. At least one actuator coupled to at least one common actuation structure is actuated to provide an actuation force via the common actuation structure. The actuation force is transferred through at least one linkage structure to at least one fluid dynamic control surface coupled thereto.

Abstract: The present invention relates to a method for measuring a time delay between two output signals measured by two adjacent optical sensors, the time delay resulting from a movement of an object moving in a given direction. The method comprises the steps: carrying out a spatial filtering of the signals Ph1 and Ph2 delivered by a first and a second optical sensor; calculating a first order derivative and carrying out a temporal low-pass filtering of the signals; calculating the second order derivative of the signals; measuring the delay between the signals; and is characterized in that the step of measuring the delay is a feedback loop based on an estimated delay between the temporally filtered signals. Device and set of devices for measuring the angular velocity of a luminance transition zone and steering aid system for fixation and tracking a target comprising at least one such luminance transition zone.

Abstract: A system and method for guiding a projectile is presented. A nozzle system includes a boom assembly body that can be attached to a rear end of a projectile. A gas tank in the boom assembly contains pressurized gas. Fins are attached to the boom assembly body to guide the projectile. A valve lets a pulse of gas out of the gas tank. A nozzle expels the pulse of gas to control an angle of attack and lift of the projectile to guide the projectile to a target.

Abstract: An afterbody device for a spacecraft fitted with at least one rocket engine at the rear of the craft includes at least one movable cover element designed to take a first position, masking and reducing the vehicle's rear drag, where it prolongs the vehicle's fuselage around at least one part of a rocket engine nozzle of the vehicle and extends beyond the rear of the vehicle's fuselage, and to take a second position fully deployed, increasing the vehicle's aerodynamic drag.

Abstract: A projectile for launch from an apparatus is disclosed herein. In some embodiments, the projectile includes a body; a boom having a first end extendable from the body; and an armature coupled to the first end of the boom, wherein the armature is configured to be moveable along and launchable from the apparatus and the armature is configured to be separable from the first end of the extended boom after launch from the apparatus.

Abstract: A steerable container delivery system (“CDS”) includes a pallet configured with a pallet steering mechanism and a range extension device for steering a CDS cargo bundle during free fall when airdropped. The pallet steering mechanism and range extension device may be inflated shortly after deployment using compressed air carried by an air tank in the pallet. A flight management computer (“FMS”) continuously monitors the location of the CDS bundle using GPS technology and determines a vector to a drop location based on stored GPS measurements. The FMC continuously monitors and positions the CDS bundle over the drop location, and is able to independently control the position of the CDS bundle, either by rotating the CDS bundle or moving it laterally. At the appropriate altitude, the FMC causes the main parachute to open to slow the descent of the CDS bundle for impact.

Abstract: A device for evaluation of the operational capabilities of an aircraft for informing a user about the capabilities of the aircraft to carry out a mission. Included are means for detecting malfunctions of aircraft equipment adapted for functioning during a mission. An evaluation device includes means for acquisition of information about the mission; a means for calculating observed feasibility level of the mission on the basis of at least one detected malfunction and the information obtained about the mission of the aircraft; and a means for presenting a synthetic reactive indicator, representative of the observed feasibility level of the mission in at least one instant of the mission. The means for acquisition, calculation and presentation are adapted for functioning during the mission, to inform the user about the observed feasibility level of the mission depending on the detection of new malfunctions and/or the modifications of the mission in course.

Abstract: A base cone for a projectile including: a cone member being movable between a retracted position and an extended deployed position, the deployed position being longer in an axial direction than the refracted position; a member adapted to connect the cone member to a trailing portion of the projectile; and a release mechanism for releasing the cone member from the refracted position to the extended deployed position.

Abstract: The method for generating an integrated guidance law for aerodynamic missiles uses a strength Pareto evolutionary algorithm (SPEA)-based approach for generating an integrated fuzzy guidance law, which includes three separate fuzzy controllers. Each of these fuzzy controllers is activated in a unique region of missile interception. The distribution of membership functions and the associated rules are obtained by solving a nonlinear constrained multi-objective optimization problem in which final time, energy consumption, and miss distance are treated as competing objectives. A Tabu search is utilized to build a library of initial feasible solutions for the multi-objective optimization algorithm. Additionally, a hierarchical clustering technique is utilized to provide the decision maker with a representative and manageable Pareto-optimal set without destroying the characteristics of the trade-off front. A fuzzy-based system is employed to extract the best compromise solution over the trade-off curve.

Abstract: A system and method of detecting, processing, and selectively responding to radio frequency transmissions detected by at least one projectile deployed above a geographic area.

Abstract: A projectile may include a base drag reduction fairing preform adapted to be plastically deformed into a base drag reduction fairing after the projectile is launched from a gun barrel.

Abstract: A position sensing assembly includes a bearing element and a helically shaped rotational member used to drive a portion of a sensor assembly, such as a Digital Rotary Magnetic Encoder. Interaction between the bearing element and a helically shaped rotational member minimizes the presence of backlash in the position sensing assembly. Accordingly, as an actuator assembly drives both a control element, such as a flight control surface, and the position sensing assembly, the sensor assembly generates an output signal that accurately reflects the position of the control element.

Abstract: A deployable fairing is driven off of high-pressure gun gases to reduce aerodynamic drag and extend the range of the artillery shell. An artillery shell is provided with a fabric fairing and a piston attached thereto in a rear section of the shell in a stowed state and a chamber. During launch high-pressure gun gasses are captured and stored in the chamber. Once the shell clears the end of the artillery tube, the pressure aft of the shell drops from the high pressure inside the tube to atmospheric pressure outside the tube. The high pressure gun gasses stored in the chamber act over the top surface of the piston to drive the piston aft against the much lower pressure behind the projectile to deploy the fabric fairing attached thereto to reduce the base area of the projectile creating or extending the boat-tail of the shell, hence reduce aerodynamic drag. The aft driven piston engages a locking mechanism that locks the piston in a deployed position.

Abstract: There is provided a ring tail for a ballistic projectile and an associated method that facilitate maneuverability of the ballistic projectile. The ring tail comprises a ring member having a generally cylindrical wall and at least one rod joined to an aft section of the ballistic projectile and the ring member. The rod defines an adjustable length, wherein an actuation device joined to the at least one rod adjusts the length to thereby maneuver the ballistic projectile during flight. The ring tail may include generally radially oriented panels and may also include a second ring member joined to the distal ends of the panels such that the ring members are coaxial. Once the projectile has been launched, the ring member extends aftward to provide aerodynamic stability, which may be measured by a guidance sensor in electronic communication with the actuation device that adjusts the length of the at least one rod.

Abstract: The present invention relates to a fin-stabilized artillery shell (1) comprising a body part (8, 26, 36) which can be axially displaced rearwards, in the direction of flight of the shell, once the latter has left the barrel from which it has been fired, and which in the original position is fully retracted in the shell (1), and in which a number of deployable fins (18, 24, 29-30, 42-47) are in turn secured, and from which the fins are automatically deployed as soon as the body part has reached its rear position in which it is locked relative to the rest of the shell. One of the advantages of the invention is that in the flight position it gives the shell a greater length than is permitted by the charging position of the artillery piece launching the shell. This gives the shell considerably better stability in its trajectory towards the target.

Abstract: The invention is, in its various embodiments and implementations, a method and apparatus for planar actuation of a flared surface to control a vehicle. In one aspect, the invention comprises an apparatus for controlling a vehicle capable of moving through a fluid medium. The apparatus includes a flare; a planar yoke operably associated with the flare; a plurality of actuators capable of moving the planar yoke to manipulate the flare through the operable association between the planar yoke and the flare; and a load bearing structure through which the translating means imparts a moment from the flare to the vehicle. In a second aspect, the invention comprises a method for controlling the maneuvering of a vehicle capable of moving through a fluid medium. The method includes moving a planar yoke to deflect at least a portion of a flare.

Abstract: Tracer visibility of APFSDS projectiles can be enhanced through a combination of increased steady state spin rate, reduced muzzle obscuration, and optimized airflow over the stabilizing fin geometry of the sub-projectile. The preferred means to increase steady state spin rates of the sub-projectile is to incline or deflect the fin blade tip portion, creating a larger, hotter burning, tracer plume.

Abstract: The present invention relates to a method of increasing the range of air defense and artillery shells of the type which for reasons of firing technology have a rear surface which is at right angles to the shell axis, i.e. most conventional air defense and artillery shells. The invention also includes a design of air defense and artillery shells that corresponds with the said method. The invention is characterized by the rear surface of the shell which at the time of firing is at right angles to the shell axis being reformed to an aerodynamically more advantageous form (5, 9) when it has left the gun barrel and is on the way to the target.

Abstract: A tube launched projectile having a shaft member at the aft section is slidably mounted on a boom extending aft from the body of the projectile. The boom has a cavity in its aft end which receives some combustion gas from the projectile propellant burn and retains this gas at elevated pressure until the projectile exits the tube. Upon reaching atmospheric pressure, the stored cavity gas expands and drives the slidable shaft aft, elongating the projectile to its flight configuration.

Abstract: A fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable fin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted position and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.

Abstract: The invention is, in its various embodiments and implementations, a method and apparatus for planar actuation of a flared surface to control a vehicle. In one aspect, the invention comprises an apparatus for controlling a vehicle capable of moving through a fluid medium. The apparatus includes a flare; a planar yoke operably associated with the flare; a plurality of actuators capable of moving the planar yoke to manipulate the flare through the operable association between the planar yoke and the flare; and a load bearing structure through which the translating means imparts a moment from the flare to the vehicle. In a second aspect, the invention comprises a method for controlling the maneuvering of a vehicle capable of moving through a fluid medium. The method includes moving a planar yoke to deflect at least a portion of a flare.

Abstract: A rudder of a missile, particularly an aircraft born ramjet missile, is attached to the missile by a plug and socket mounting. A bearing socket (B1) is attached to a base plate (B0) which is secured to the missile body (FK). The socket (B1) has a conical cavity (B3) tapering toward the base plate (B0). The plug (W1) is formed by a rudder shaft (W) also tapering toward the base plate and rotatably fitting into the conical cavity (B3). Bearings (L1, L2) in the cavity (B3) hold the plug end (W1) of the rudder shaft axially and permit rotation of the rudder shaft (W) relative to the bearing socket (B1). The socket thus holds the bearings and has an at least partly outer cylindrical contour with a diameter (B2) that fits into a standard 41 mm wide slot (S) in an aircraft that carries the missile, whereby the rudder (R) is recessed in the slot (S) when the missile is mounted to an aircraft.

Abstract: A ramming brake is provided for use with a projectile launched from the barrel of a gun having a tapered portion. The ramming brake includes a braking ring that has a tapered surface configured to wedge into a tapered portion of the gun barrel. In a particular configuration, the braking ring wedges in the tapered breach of the gun barrel. The ramming brake further includes a retaining mechanism that is used to couple the braking ring to the projectile. This retaining mechanism restrains and controls the movement of the projectile after the braking ring wedges into the tapered portion of the barrel.

Abstract: A fin-stabilized projectile includes a projectile body having a rear portion defining a rearwardly open cavity and a stabilizing assembly which has an axially slidable tin support in the cavity. The fin support has a retracted position in which the fin support is withdrawn into the cavity and an outwardly shifted position in which the fin support projects from the projectile body. A plurality of fins are pivotally held in the fin support. Each fin has a folded state in which it is withdrawn in the fin support when the latter is in the retracted posit on and a deployed state in which it is unfolded and extends substantially externally of the fin support when the latter is in its outwardly shifted position. When the projectile has left the weapon barrel, the fin support is axially shifted and the fins move into the deployed state.

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 projectile attachment is disclosed that has open-biased arm members that can be either mounted directly onto the projectile base or may be mounted to a mutual connection means which is then attached to the projectile base. The arms are compressed into a restrained position so that they may be inserted into the casing of the bullet. Upon firing, the arms extend to the unrestrained position. Upon impact the projectile penetrates the target then the extended arm members engage the target surface to cause widespread damage while slowing the projectile. The members may optionally have hook-like ends.

Abstract: A retention and deployment mechanism for pivotable guide fins on bombs or missiles includes a cup shaped yoke slidably mounted on a shaft. The device is mounted in a central region of the bomb tail and engages tabs on each of the fins. The tabs are held between a retaining flange and pusher arms extending radially from the yoke. The retaining flange prevents pivoting of the fins until desired. A drive spring causes the yoke to slide axially, and the pusher arms push on the fins to cause pivoting to the deployed position. The yoke includes a head end with a cone shaped recess. Four balls seated in holes in the shaft contact the cone shaped recess to prevent movement of the yoke. A pin disposed in a bore in the shaft hold the balls in the seats. The pin includes a groove, and is movable by a spring to a position where the balls fall into the groove, thus releasing the yoke. A lanyard is attached to the aircraft and extends through aligned holes in the shaft and pin to retain the pin in position.