Abstract: A vehicle for launching from a gas gun having a housing; preferably incorporating a precessional attitude control system; and utilizing a flared base, fins, or active use of the attitude control system during passage through the atmosphere. Subtly canting the fins can produce desired spinning of the vehicle. The propulsion system can employ liquid, hybrid, or solid fuel. A removable aero-shell assists atmospheric flight with thermal protection being provided by anticipated ablation, an ablative aero-spike, or transpirational cooling. And a releasable sabot enhances the effectiveness of the launch.

Abstract: An integrated warhead and rocket motor subassembly. The novel subassembly includes a warhead, a rocket motor, and a single bulkhead separating the warhead and the rocket motor. The bulkhead is adapted to handle both pressure loads from the rocket motor and missile carry loads transmitted through a hook and hangar assembly, which is bolted into the bulkhead. In an illustrative embodiment, the warhead includes an explosive fill surrounded by a material adapted to form a plurality of fragments upon detonation. In a preferred embodiment, the fragments are formed into small cubes that are 80 to 85 grain in weight, using a material having a density greater than 16 g/cc.

Abstract: A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile.

Abstract: A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile.

Abstract: A method for providing actuation thrust to a projectile. The method including: providing two or more individual actuators movably disposed in a stack housing, each of the two or more individual actuators being separated by a separation layer; accelerating exhaust from the two or more individual actuators with an accelerating nozzle having at least a convergent section terminating at a throat; and maintaining a constant volume in the accelerating nozzle after actuation of each of the two or more individual actuators.

Abstract: Projectiles that include a propulsion system and a launch motor which are located on opposing sides of a payload and a method of directing a projectile toward a target are generally described herein. Placing the propulsion system and the launch motor on opposing sides of the payload may provide many potential advantages when designing the projectile. These design advantages may make it easier to create a projectile that includes more propellant and/or payload while still permitting the projectile to be stored within existing containers having a fixed size.

Abstract: Embodiments of a translating adjacent-blast shield and method of protecting external slots of a missile from a high-temperature, high-pressure gas plume of a missile that is launched from an adjacent or nearby launcher tube of a launcher are disclosed herein. The translating adjacent-blast shield may be provided circumferentially around each of the missiles in a launcher and may cover at least portions of external slots of the missiles. The translating adjacent-blast shield may translate along the missile during launch to expose the external slots and may remain on the missile after launch.

Abstract: A torch igniter and method of cooling the torch igniter includes axially flowing a first stream of gaseous oxidizer through a torch throat and vortically flowing a second stream of the gaseous oxidizer within a combustion chamber.

Abstract: Improvements to projectile devices (particularly air guns) include techniques for measuring and controlling the velocity of projectiles in the barrel and after leaving the barrel, allowing the use of non-toxic projectiles. Tracking of a projectile's flight by its unique sound and/or its unique electromagnetic signal or signal modulation are also provided, along with after-barrel guidance that can be used to improve accuracy. Control for discriminating between authorized and unauthorized users is also provided. A projectile device can also be used for inexpensive and harmless practice using optical and/or acoustic information gathered by targeting and imaging systems built into the device.

Abstract: Some embodiments pertain to a projectile that includes a propellant and a casing that encloses the propellant such that the casing acts as a reaction chamber during flight of the projectile. The casing includes a plurality of flechettes. When the projectile strikes (or is near) a target, a large internal sheer pressure forms within the casing. This sheer pressure causes the flechettes to sheer apart at the thinnest sections of the casing. Once the thin sections of the casing are sheered apart, the flechettes will be unconstrained such that the flechettes take individual flight paths.

Abstract: A UAV includes: a rocket body, having a rocket motor and a payload section; a parachute coupled with the payload section; an image capture device; a magnetometer to provide a compass reference for images taken from the image capture device; and a transmitter to communicate image and compass data to a remote receiver. Compass bearings are overlaid on image data from the image capture device. A handheld launch unit includes an ignition system, having an activation mechanism and an igniter to activate the rocket motor. A safety pin prevents electrical current from flowing to the igniter until the pin is removed. An accelerometer and/or magnetometer determines an angular orientation of the UAV. Software verifies that the angle is within a user-defined safety limit before activating the igniter.

Abstract: A fuze setting circuit in an artillery or tank shell having a case with a press-fitted head assembly is provided with an electromechanical fuze-wiring link that is completed electrically by mechanical assembly of a tracer-carrying projectile on the shell casing, and by the rotational attachment of a programmable fuze onto the projectile.

Abstract: A sub-caliber bullet with an aerodynamic shape has long-range accuracy due to a high muzzle velocity and reduced time of flight to a target. The bullet has forward and aft portions and a mid-portion. The forward portion has a density in excess of 10/cm3 while the mid-portion has a lower density. The bullet has an aspect ratio of at least 5:1 and a diameter, d, that satisfies a Power Law equation: d=D*(x/L)n where D is a maximum bullet diameter, L is the length, x is a distance rearward from a nose of the bullet and n is a Power Law exponent that is between 0.5 and 0.75. In some embodiments, a blind bore extends into the mid-portion from the aft portion and a sustainer propellant within the bore ignites as the bullet exits a gun muzzle to provide a velocity boost and to overcome aerodynamic drag.

Abstract: Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure to provide low frequency stiffness and strength performance while attenuating high frequency vibrations.

Abstract: Apparatus for providing electrically initiated and/or controlled combustion of electrically ignitable propellants is provided. In one example, the apparatus includes a volume of electrically ignitable propellant (liquid and/or gas) capable of self sustaining combustion, and electrodes operable to ignite the propellant. The apparatus may further include a power supply and controller in electrical communication with the electrodes for supplying a potential across the electrodes to initiate combustion of the propellant and/or control the rate of combustion of the propellant. Various configurations and geometries of the propellant, electrodes, and apparatus are possible. In one example, the electrodes are supplied a direct current, which causes combustion of the propellant at the positive electrode. In another example, the electrodes are supplied an alternating current, which initiates combustion of the propellant at both electrodes.

Abstract: A weapon system and corresponding ammunition for causing less-than-lethal effects to a target employ a projectile fired from a rifle-mounted, rifle-operated or dedicated rifle-like device and configured for generating less-than-lethal effects to a human target. The projectile includes a rocket motor configured to mitigate velocity decay of the projectile. The rocket motor is preferably a sustainer motor for maintaining a roughly constant cruise velocity of the projectile.

Abstract: A multiple-stage solid rocket motor is operated in a manner designed to control its mass discharge profile. This is accomplished by providing means for igniting one stage and then igniting a subsequent stage while the first continues to burn.

Abstract: A sabot projectile with a subcaliber penetrator and a sabot, which has a propulsion element that acts on the rear end of the penetrator, a segmented, essentially cylindrical guide cage, which is connected to the front end of the propulsion element, and a segmented, disk-shaped metal guide element that extends radially inward in the front area of the guide cage and holds the penetrator. The disk-shaped guide element has a slightly convex contour in the direction of flight of the projectile and the material and the wall thickness of the guide element are chosen in such a way that convex area of the guide element is pushed back slightly when the sabot projectile is fired, so that the outer marginal area of the guide element rests against the inside wall of the gun barrel from which the sabot projectile is fired, and/or the inner marginal area of the guide element, which faces the penetrator, rests against the outer surface of the penetrator.

Abstract: An arrow-type warhead (100,200,300,400,500,600,700) comprises an envelope (102,202), a filling (108), a hardened head section (104) to promote penetration of the target and a stabilizing mechanism (106,210,302,402,502,602) to stabilize the warhead in flight, hi some embodiments the filling (108) is pyrophoric and undergoes an exothermic reaction with the envelope upon impact. In other embodiments the filling is incendiary and undergoes reaction with the envelope upon impact in an oxygen rich-environment. In yet other embodiments, the filling is explosive. In all embodiments, the warhead may be equipped with a mini-rocket propulsion mechanism (802) for propelling the warhead to the target.

Abstract: An anti-mine dart includes a body containing an explosive payload and having a flyer-plate port. The dart is operable responsive to the payload being detonated to propel through the flyer-plate port a flyer plate having sufficient energy to detonate an explosive material surrounding the dart. The darts may include a plurality of explosive payloads, flyer-plate ports and flyer plates. The darts may be formed in a stack arrangement within a missile such that the flyer-plate port of each dart is not aligned with the flyer-plate ports of any of the adjacent darts in the stack arrangement. The darts may contain a simplified safe-and-arm mechanism or no safe-and-arm mechanism at all.

Abstract: Embodiments of a missile, an airframe and a structure comprising piezoelectric fibers and a method for active structural response control are generally described herein. In some embodiments, a housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.

Abstract: A rocket includes a front warhead, a rear propellant actuator, and a propulsion enhancement arrangement which comprises at least two propulsion impulse generators longitudinally cascadedly mounted between the warhead and the rear propellant actuator, wherein each propulsion impulse generator comprises a storage barrel for storing a predetermined amount of explosive materials to provide propelling impulse upon controlled explosion thereof, and a time-internal control arrangement comprising a time-interval control device mounted on a bottom of the front warhead, a time-interval trigger wire operatively connected with the time-interval control device, and at least two time-interval triggers mounted along the time-interval trigger wire and inside of each of the storage chambers respectively, wherein the time-interval triggers trigger the explosion of the explosive material stored in the storage chamber from the bottom propelling impulse generator to the top propelling impulse generator one by one at a predetermin

Abstract: A missile component such as a rocket motor case, of an initial transverse cross-sectional shape flexible into another, different cross-section responsive to application of internal pressure from ignition of a propellant grain within the component. A missile launch assembly including at least one missile of a non-circular cross-section disposed within a segment of a partitioned circular launch tube. A multi-stage missile comprising at least a first stage and a second stage having rocket motor cases of non-circular transverse cross-section, the rocket motor case of at least one of the stages being deformable into another, different cross-section. A method of launching a missile including igniting a rocket motor of a component having a first cross-section, internally pressurizing the missile component substantially concurrently with motor ignition and flexing the component rocket motor into a second, different cross-sectional shape.

Abstract: Projectiles are provided having a shell and; one or more actuators for providing thrust disposed inside of a wall of the shell; one or more ring portions forming at least a portion of the shell, the one or more ring portions having one or more actuators formed therein for providing thrust and/or one or more actuator stacks for providing thrust, the one or more actuator stacks each having two or more individual actuators for providing thrust.

Abstract: A propulsion system and method are described configured to exert a force upon a vehicle. The system includes a concentrated mass which may be discharged from the vehicle by a propellant typically via an ejection tube. The system is optimized so that the discharged concentrated-mass imparts a large impulse upon the vehicle. The system and method may be used to alter the momentum of vehicles for propulsion, attitude correction, vehicle separation and the like.

Abstract: Projectiles are provided having a shell and; one or more actuators for providing thrust disposed inside of a wall of the shell; one or more ring portions forming at least a portion of the shell, the one or more ring portions having one or more actuators formed therein for providing thrust and/or one or more actuator stacks for providing thrust, the one or more actuator stacks each having two or more individual actuators for providing thrust.

Abstract: A vibration controlled housing. The novel housing includes a housing structure and a mechanism for receiving a control signal and in accordance therewith electronically tuning a structural response of the structure. In an illustrative embodiment, the housing structure includes a composite material containing a plurality of piezoelectric fibers adapted to generate an electrical signal in response to a deformation in the structure and to deform the structure in response to an electrical signal applied thereto. A control circuit receives the sensed signal from the fibers and generates an excitation signal that is applied to the fibers to increase the stiffness or compliance of the fibers at predetermined frequencies. In an illustrative embodiment, the control signal is adapted to provide low frequency stiffness and strength performance while attenuating high frequency vibrations to protect electronics housed within the structure.

Abstract: A cooling fin for a mortar tube comprises a plurality of discrete nibs disposed on an external surface of the mortar tube wherein the nibs are arranged in longitudinal rows spaced circumferentially around the mortar tube. Preferably, the number of longitudinal rows of nibs is thirty-six. The nibs have a substantially square cross-section.

Abstract: An unmanned air vehicle for military, land security and the like operations includes a fuselage provided with foldable wings having leading edge flaps and trailing edge ailerons which are operable during ascent from launch to control the flight pattern with the wings folded, the wings being deployed into an open unfolded position when appropriate. The vehicle is contained within a pod from which it is launched and a landing deck is provided to decelerate and arrest the vehicle upon its return to land.

Abstract: A method of manufacturing ammunition 10 for firing from the barrel of a weapon comprises forming a mould 32 having an interior surface, placing a core 42 in the mould 32 to produce a casting void 43 and pouring a liquefied solidifiable material into the casting void 43. Upon solidification of the material, the core 42 is removed to produce a projectile body 12 having a closed end and an opposite end. The removal of the core 42 also creates the cavity 18 in the projectile body 12 that opens onto the opposite end. The projectile body 12 is removed from the mould 32 and a quantity of propellant 22 is deposited into the cavity 18 through the opposite end. A seal 26 which incorporates a primer is pressed into the opposite end. Circumferential flanges 30a and 30b are integrally moulded with the projectile body 12.

Abstract: A solid-fuel rocket assembly including an elongate fuel container having a long axis, and an inner surface spaced outwardly from, and generally circumsurrounding, that axis, and a continuous, elastomeric, heat-insulative, intumescence-behavior jacket adhered to the container's inner surface and defining a central chamber for receiving an elongate body of solid fuel. This structure implements a method for minimizing, in a solid-fuel rocket, heat damage to the wall of a solid-fuel container during burning of contained solid fuel including the steps of (a) producing dual-interface, continuous-presence, heat-insulative barriering in the zone existing between the container and burning fuel, with such barriering being characterized by (1) interfacially following any heat-produced deformations in the container wall, and (2) interfacially confronting the burning fuel with a tendency for intumescence-driven barrier-thickening.

Abstract: A projectile may be used in a boat tail or base bleed configuration. The projectile includes a warhead casing having a nose end and a base end; a payload disposed in the warhead casing; a motor body attached to the base end of the warhead casing and having an igniter disposed therein; a base closure attached to the motor body, an exterior surface of the base closure being tapered to form a boat tail, the base closure and the motor body defining an interior volume; a propellant disposed in the interior volume, the propellant being used for base bleed operation; and a converter attached to the base closure and extending into the interior volume.

Abstract: A rocket motor case includes a plurality of plank sections which provide a structural key for locking metal and/or composite end enclosures in place as part of the motor case. The plank sections are sized longitudinally to form venting spaces in the motor case sidewall to allow passive venting in the event of propellant ignition during cook-off. The plank sections have plank legs which are surrounded by tailorable roll-bonded sheet material to complete formation of the motor case sidewall.

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: The invention relates to a flying object (1) comprising a lift and displacement motor (3) which has a combustible propelling charge and direct thrust flight control and can ensure the lift and displacements of said object (1) in an observation position for which the object is at least approximately vertical with the rear part (2R) thereof oriented downwards; an attitude motor (5) with a combustible propelling charge and conventional thrust vector control; and observation means (14) which are arranged in the rear part (2R).

Abstract: An advanced internal combustion-electric hybrid airplane, having at least double the flight range and flight duration than a conventional equivalent airplane, while using the same amount of any desirable fuel. This is achieved by using 2-3× smaller and ultra-lightweight engine for cruising, and ultra-lightweight electric motor powered by lithium batteries during take-off and climbing. The electric motor becomes a generator during cruising and descent, recharging said batteries. The airplane has also temporary silent electric stealth capability and added safety by the electric back-up power. Due to its high efficiency, the operational cost is substantially reduced. Additional features include highly advanced, minimum drag and weight airframe.

Abstract: A supercavitating projectile is disclosed and includes a combustion chamber, a forward-directed jet nozzle and a comparatively larger gas duct/rear-directed jet nozzle. The combustion chamber is filled with a propellant having a hollowed core. The core serves as a pathway to fluidly allow combustion gases to the jet nozzles. In operation, the propellant combusts to form gasses forced forward through the forward-directed nozzle to generate a virtual cavitator in the form of a ventilation gas bubble. Combusted gasses are also forced out the rear-directed nozzle forming a propulsion jet. The projectile therefore uses the rear-directed jet to maintain a cruise velocity approximate to the launch velocity and employs a source of ventilation gas using the forward-directed jet for supercavitating of the projectile.

Abstract: The apparatus of the present invention utilizes the heat energy of a weapon propulsion system to produce a vapor explosion. It includes an outer shell with a nozzle port and a body being made from a metal. The body surrounds a propulsion device and captures its waste heat to heat metal within the body. An explosive device is embedded in the body and can explode on transmission of a signal whereby the heated metal within the body produces a vapor explosion that significantly enhances the effectiveness and lethality of the weapon. The apparatus also discloses a second metal in the body and a heat shield for further enhancing effectiveness.

Abstract: A method for ballistic target defense including identifying a launched ballistic target having a target launch point, a target launch direction, a target speed, and a target trajectory; launching a target interceptor in a launch direction that is generally the same as the target launch direction and with a speed that is less than the target speed; providing the interceptor with an approximate target intercept trajectory; and accelerating the interceptor at an approximate point of intercept to substantially match the target trajectory. During a relatively long target engagement time, the interceptor has approximately a zero net relative velocity with respect to the target.

Abstract: A pyrotechnic charge structure, in particular for use as propellant in a rocket motor, is disclosed. The charge structure has a predetermined longitudinal extension and cross sectional area adapted to the intended purpose. The pyrotechnic charge structure (1; 2; 3; 4) is in cross sectional view in cellular form aimed at having similar wall thickness for all the cells of the charge structure. The wall (6) of the cells comprises the pyrotechnic charge, i.e. the propellant, and each cavity of the cells occupies air or oxygen-rich gas.

Abstract: The apparatus of the present invention uses waste heat generated by a weapon propulsion system to melt and ultimately superheat metal. Upon termination of the weapon mission, the apparatus explodes thereby causing molten and superheated metal to be instantly introduced to the liquid medium through which the weapon travels. The reaction of the molten and superheated metal with the liquid medium produces a vapor explosion that significantly enhances the effectiveness and lethality of the weapon.

Abstract: A scramjet has a cowl, a center structure, and a plurality of wide pylons connecting the cowl to the center structure, with scramjet engines positioned between adjacent pylons. Leading surfaces of adjacent pylons converge to one another to provide side wall compression to air entering the engines. The center structure includes a fore body, a center body and an aft body that, with the pylons, define a basic structure either formed entirely from one piece or several securely connected pieces. A method of testing the scramjet projectile comprises using a gun to accelerate the scramjet projectile to the takeover velocity of the engines.

Abstract: A rocket includes a front warhead, a rear propellant actuator, and a propulsion enhancement arrangement. The propulsion enhancement arrangement includes a storage chamber positioned between the warhead and the propellant actuator for storing a predetermined amount of explosive materials to provide propelling impulse upon controlled explosion thereof, and a time-sensitive trigger device operatively communicated with the storage chamber, wherein the time sensitive trigger device includes a timing device and an ignition trigger operatively communicated with each other such that the ignition trigger is arranged to ignite the explosive materials stored inside the storage chamber at a particular predetermined time to generate a propelling impulse to further accelerate and propel the warhead to hit the a targeted object.

Abstract: A projectile (100) for piercing armor including a cruise propellant (116) for maintaining a cruise velocity of the projectile. The projectile (100) also includes an acceleration rocket motor (109) activated after launch for accelerating the projectile (100) from the cruise velocity to a penetration velocity, in a final stage of flight of the projectile.

Abstract: A shut-off system for an orifice of a duct, particularly for an orifice of an air inlet passage that allows air into the combustion chamber of a ramjet, includes a shutter for shutting off the orifice of the duct, and a controllable actuating device capable of acting on the shutter to uncover the orifice. The shutter includes a removable cap which is held on the duct and a locking device which keeps the cap on the duct by at least one locked jaw, which is unlockable. The actuating device includes at least one controllable striker which is capable of unlocking the jaw in such a way as to cause the cap to be ejected from the duct and to uncover the orifice.

Abstract: A neutralization device for a payload carried by a vector, such as a rocket. This device incorporates at least one explosively-formed charge, where such charge is made integral with the vector by a positioning device ensuring the orientation of its direction of action towards the payload.

Abstract: A self-propelling projectile allowing restricted local target effects comprises a penetrator core, a charge for at least partially fragmenting the core at a target, and autonomous ignition device for the charge. The penetrator core has a stepped tip with a forward exterior dart angle and a larger following acute angle and a dart shank that tapers towards a rear end of the core. A coaxial cavity is located within at least a rear portion of the core carries an active substance is next to an explosive charge for opening the cavity at the target. The active substance can either be of lethal or non-lethal characteristics. The projectile can be configured to be usable with conventional launchers and auxiliary equipment.

Abstract: The invention comprises an improved precision rocket motor and warhead system by increasing the spin rate of the rocket motor. The system comprises an outer housing segment attached to the end of a rocket motor tube and an annular sleeve placed within the end of the outer housing segment so that the end of the sleeve is aligned with the end of the segment. At least two annular bearings are placed around the outer surface of the sleeve. Normally the annular bearings will be made of a plastic type material that can be “stretched” around the outside of the sleeve prior to placing it within the outer housing segment. The inner surface of the sleeve will include a warhead attachment mechanism to secure the warhead to the inner surface. Finally, the invention includes a locking mechanism that locks the sleeve in place within the outer housing segment while attaching the warhead to the sleeve and unlocks to allow the sleeve to rotate independently of the rocket motor.

Abstract: A self-propelling projectile allowing restricted local target effects comprises a penetrator core, a charge for at least partially fragmenting the core at a target, and autonomous ignition device for the charge. The penetrator core has a stepped tip with a forward exterior dart angle and a larger following acute angle and a dart shank that tapers towards a rear end of the core. A coaxial cavity is located within at least a rear portion of the core carries an active substance is next to an explosive charge for opening the cavity at the target. The active substance can either be of lethal or non-lethal characteristics. The projectile can be configured to be usable with conventional launchers and auxiliary equipment.

Abstract: The Collapsible Support Frame for Kinetic Energy Penetrator supports a long-rod kinetic energy penetrator inside a kinetic energy missile air frame in handling and flight environments but, upon impact of the missile on the selected high-obliquity target, gives way. This greatly reduces the lateral loading inflicted on the penetrator by the interaction of the missile body and the target and consequently maximizes the effectiveness of the penetrator against the target. The Collapsible Support Frame comprises concentric outer and inner rings that are mounted inside the missile and designed to hold and support the penetrator. When the missile strikes the target and the extremely high impact shock loading conditions of the penetrator process occurs, the outer ring captures a high impact shock loading pulse and transmits it to the inner ring, whereupon the inner ring fails in its supportive function, thus freeing the penetrator.