Abstract: A rapid burning propellant charge for applications including igniters, launch eject motors, and gas generators for automobile air bags. The propellant charge comprises a reticulated substrate having a quantity of interconnected ligaments and a coating of solid propellant material on the ligaments. In order to provide a large amount of surface area for a fast burn time, interstices are between coated ligaments to define propellant surface area for combustion. In applications where minimum smoke is desired, the reticulated substrate is preferably composed of carbon, graphite, or a non-combustible material, and the solid propellant material is preferably a minimum smoke type.

Abstract: Disclosed is a method for ejecting an interceptor missile from the silo in hich it is stored. The method employs an ultrahigh-burning rate (e.g., burning rate 10-20 inches per second) booster solid propellant grain in combination with a fuse or a combination of fuses having a burning rate (e.g. 25 to 100 inches per second) or a rate which is well above that of the ultrahigh-burning rate booster solid propellant grain. The fuses are designed to a predetermined exterior contour which is the same as the exterior contour of the mandrel which would normally be used to provide the contour to the internal perforation of the booster propellant grain. The method include positioning the fuses longitudinally in the booster motor instead of the normally used mandrel, and then casting the propellant around the fuse or a combination of fuses and curing the propellant to yield a booster solid propellant grain.

Abstract: An anti-armor weapon comprises an outer casing in which a non-explosive, armor-penetrating device, suitably a solid rod of heavy, high density metal or metal composite, is mounted. The penetrating device is mounted in a forward portion of the casing while a launch population device is mounted at the rear end for launching the weapon from a launch tube or firing barrel at a first, subsonic launch speed. A second, boost propulsion device is mounted in the casing adjacent the penetrating device for accelerating the weapon to a second, faster speed sufficient for the penetrating device to penetrate a target, and is associated with an igniter for actuating the boost propulsion device. A sensor is provided within the missile for sensing when the weapon is a predetermined distance from the target and subsequently actuating the igniter.

Abstract: A traveling charge projectile utilizes a microprocessor and a plurality of sequentially fired igniting-priming-expelling charges to initiate respective charge segments containing propellant, such as granular propellant, of predetermined grain size, to produce a more nearly constant pressure against the projectile base. Traveling charge propellant segments attached to the projectile move with the projectile as it accelerates in the gun barrel. At appropriate intervals during barrel transit, a firing signal initiates a charge which propels the aft most propellant segment away from the projectile into the hot gases and flame behind the projectile to fully ignite the propellant charge and repressurize the expanding breech volume immediately aft of the accelerating projectile. This design maintains a higher average pressure on the base of the projectile during barrel transit, and results in a higher projectile muzzle velocity.

Abstract: This invention relates to a releasable body, comprising outspreadable arms articulated at one of the ends of said body and actuation means adapted to pass said arms, in the course of aerial descent of said body, from a position folded along said body to a spread out position substantially perpendicular to said body in order to brake descent thereof, wherein it comprises first means for controlling said actuation means to control retraction of said arms along said body when the latter has reached the ground after its aerial descent, said body then being in standby state, and second means for controlling said actuation means to control outspreading of said arms to pass from the standby state to an active state in which the arms support the body on the ground. The invention is applied to releasable bodies provided with aerodynamic braking means.

Abstract: The invention relates to a propellant charge igniter comprising at least two series-connected combustion chambers separated from one another by choke disks, respectively one igniter mixture being housed in these chambers, these igniter mixtures differing from one another with respect to their combustion characteristics and thus exhibiting differing combustion behavior. The combustion chamber volumes are adapted to these igniter mixtures so that the mixture can burn up at the pressure level that is an optimum for the mixtures in each case.

Abstract: A base bleed unit arranged to increase the range of fire or to reduce the time of flight for shells and projectiles includes a housing (1) surrounding a fuel charge (6) and associated igniter (4), extending from the rear portion of a projectile body (2) and including at least one outlet nozzle (5,5',5") for combustion gases, which by means of a mass flow, and possibly combustion adjacent to the base plane, reduce existing base drag. According to an embodiment of the invention, the housing (1) comprises a caseshaped member 1 attachable against a projectile body (2), having at least one igniter (4) arranged adjacent to an internal plane of a restricting wall surface at the housing (1), located in an opposed relationship to the portion of the housing (1) attachable against a projectile body (2). The combustion flame of the igniter (4) is hereby maintained directed towards the fuel charge (6) and away from the outlet nozzle/nozzles (5, 5',5").

Abstract: An aerial target vehicle has an aerodynamically stabilized body carrying plural rocket motors. An ignition system for the motors serves to fire the motors in selected groups at selected time intervals. The ignition system uses a capacitor as its sole power source. The capacitor is charged only after the motors are in place and the vehicle is ready for launch. A capacitor-powered logic circuit ignites the motor groups at the selected time intervals. The sequential firing of the rocket motors provides a quasi-maneuverable target with relatively long range and flight time. The capacitive power arrangement is a safety factor that prevents premature firing of the rocket due to transient currents.

Abstract: An enabling device 24 for a gas generator 42 of a forced dispersion munitions dispenser 10 includes a housing 58 in which and formed a bore 60, an outlet lead 88 and a detonator opening 68 in which is positioned an electrically initiated detonator 70. A piston 62 is located in the bore 60 and has a disabled position and an enabled position. A safety groove 64 is formed in the outer surface of the piston 62, and a safety passage 72, a safety aperture 74, 75 and a transfer lead 86 are formed in the piston 62. A gas generator 42 containing a quantity of pyrotechnic material 84 is mounted on the housing 58. The gas generator 42 is provided with a safety outlet 46, 47 and an inlet lead 44.

Abstract: A gun barrel and projectile system utilizes a smooth central bore gun barrel fitted with a short rifled insert near the breech end. A projectile fitted with a perforated skirt and driving band about the base of the skirt are loaded into the gun barrel so that the driving band just engages the rifled insert, and the warhead portion of the projectile extends into the smooth bore portion of the barrel. Upon firing of a breech charge, gases from the breech charge are ducted to the space between the thin side walls of the projectile and the smooth central bore, thereby establishing a gas bearing. The gas bearing provides lateral support to the projectile and lubricates the projectile in the smooth central bore. Because of the lateral support the projectile receives from the gun barrel and the gas bearing, much less projectile structural strength is required to resist set-back forces. Mass fraction ratios of ordnance payload mass to structural mass in the projectile are on the order of ninety percent.

Abstract: The pyrotechnic igniter comprises a strong outer casing (3) whose bottom is equipped with divergent peripheral openings (4) and an ignition charge (5) placed in this casing. In order to obtain reproducible thermodynamic characteristics during the firing of the gas-generating charge (1) with a central channel, while withstanding the very high accelerations produced when the gun is fired, the inner surface of the casing comprises a means of axial positioning of the charge which provides a free space (6) between the downstream face of the charge and the bottom of the casing, the ignition charge (5) comprising a peripheral sleeve (7) resting on the said means of axial positioning.

Abstract: A partially combustible propellant charge igniter has a bottom piece with primer charge and an ignition gas guide tube adjoining this primer charge, with a combustible tube containing the booster charge, the internal diameter of this latter tube being larger than that of the ignition gas guide tube, and a cavity containing a separating charge between the ignition gas guide tube and the combustible tube. A communicating opening is provided between the propagation charge and the separating charge. The communicating opening comprises at least one bore in a valve bonnet, valve means being provided which, in case of excess pressure in the cavity with respect to the booster charge close the bores at least partially, so that ignition of the separating charge takes place essentially through the bore.

Abstract: An igniter for use in conjunction with a model rocket engine. The igniter includes a housing having an adhesive ring and a fuel container. The adhesive ring supports and secures the open lower end of the rocket engine casing to the housing such that the fuel in the container is in communication with a propellant charge held in the engine casing. A pair of electrical pins extend through the base of the container and are interconnected by a nichrome wire which carries a flammable material known as an initiator. The portion of the pins extending exterior of the container are configured to be received in a standard female electrical receptacle which is connected to a battery and firing panel.

Abstract: Our invention comprises a launcher which takes the form of a holster carried firearm and a rocket propelled missile slidably mounted within the launcher. Features of our invention include electrical ignition of the rocket propelled missile, waterproof electrical connectors and switches, an impact actuated warhead, a warhead firing mechanism, electrical and mechanical safety devices, and automatic warhead arming upon rocket motor ignition. Additional features include rapid reload capability, illuminated sight lights, ease of carry and one hand operation. Our design incorporates only two moving parts in the launcher, and one moving part sealed within the missile body. Advantageously, none of the components are subject to corrosion or contamination, and no special materials are necessary in its fabrication.

Abstract: A closed urethane cylindrical case includes a mounting base or foot which runs parallel to the axis of the case and is bonded to the surface of the propellant grain of a full head-end-web rocket motor. Contained within the case are one or more spaced tube initiators and concentrically positioned discs or webs of high energy propellant. Flaming gases resulting from actuation of the tube initiators and consequent burning of the propellant wafers are projected over the surface of the rocket motor propellant from a plurality of nozzle ports that are provided in the cylindrical case, in the quadrants thereof adjacent the surface of the rocket motor propellant. Cylindrical case length and the number of tube initiators and propellant wafers including their spacing can be selected as required to achieve a desired mass flow rate.

Abstract: A low cost easily installed and reliable weather seal for the nozzle throat of a solid propellant rocket motor which uses an aft end ignition system. The igniter cartridge, known per se, which is located in the throat of the rocket motor is provided with an elastomeric O-ring in the base of the cartridge thus sealing the gap between it and the inside surface of the exit cone of the nozzle. This structure not only provides an effective weatherseal but also provides a convenient means of positively retaining the igniter cartridge in place.

Abstract: A consumable sealed plastic cup containing ignition pellets is assembled into end cap at the forward end of a solid fuel rocket motor with sufficient clearance to allow leak test gas to bypass it and thereby expose the port seals of the through bulkhead initiators for leak checking.

Abstract: A self-propelling projectile comprising a projectile body at the normally forward end of said projectile, a propellent charge at the normally rearward end of said projectile, and a primer element located between the ends of said projectile for ignition by side firing or percussion; there being means for maintaining said components in integrated relationship and with communication between said primer element and said propellent charge whereby upon explosion of said propellent charge the force of the latter will be directed against the base of the projectile body.

Abstract: A device for underwater missiles for use against submerged submarines, said missiles including a housing (1) having a front portion, intended to contact the outside surface of a submarine. According to the invention, a tubular ring member (6) is rotatably attached to the front portion of the housing (1), said ring member (6) being arranged to take up a rotary movement in relation to the housing (1) when contacting the outside surface of a submarine. In order to facilitate rapid acceleration of the ring member (6) into said rotary movement, the ring member (6) is attached to the housing (1) by means of a ball bearing joint (7) or any other known low-frictional rotary joint or connection, and the mass of the ring member (6) is also considerably smaller than the total mass of the missile. The outer surface(s) of the ring member (6) is/are also preferably arranged with means intended to increase the frictional contact between the ring member (6) and the outer surface of a submarine on impact, e.g.

Abstract: An improved booster construction having a metallic covering with a plural of apertures therein encases a booster charge which, in turn, is encased in a nonmetallic cup having a low temperature melting characteristic permitting the booster charge to expand during thermal cook-off to prevent reaching critical temperature pressure relationships.

Abstract: An end cap for a tubular container having a deep drawn flanged cup adapted to receive an igniter device for igniting the explosive contents of the container, such as the propellant for generating gas for expanding an air bag in a vehicle passenger restraint system. The cup has in its bottom wall, a centrally located aperture normally sealed by a composite laminate of plastic film and metal foil that is rupturable by the signal from the igniter device. A plastic annulus interposed between the igniter device and laminate protects the latter against frictional erosion by rubbing action of the igniter device through environmental vibrations transmitted to the propellant container.

Abstract: A self-propelling projectile comprising a projectile body at the normally forward end of said projectile, a propellent charge at the normally rearward end of said projectile, and a primer element located between the ends of said projectile for ignition by side firing or percussion; there being means for maintaining said components in integrated relationship and with communication between said primer element and said propellent charge whereby upon explosion of said propellent charge the force of the latter will be directed against the base of the projectile body.

Abstract: The invention relates generally to a small model rocket motor. The motor includes a plastic composite propellant, and plastic ablative nozzle, and provides means for producing thrust, a time delay, and a charge to activate external devices of desirable design.

Abstract: An improved arming-firing device that provides handling safety in a rocket otor. The arming-firing device provides pyrotechnic (out-of-line) and electrical (open and shortened initiator circuits) safety features wherein the arming-firing device is armed by rotating an assemblage of a mechanical rotor switch assembly, and solenoid wherein the solenoid aligns multiple cavities of the mechanical rotor with multiple prongs of a kinetic energy barrier assembly ad this action simultaneously electrically arms (closes circuits and removes shots) and mechanically enables the initiator whereupon receiving a firing signal fires and in turn ignites the ignitor of the rocket motor. The mating of the kinetic energy poppet-sleeve squib assembly's barrier prongs with the rotor cavities obviates rebounding, thus affording proper ignition. The mechanical barrier and a solenoid return spring prevents inadvertent firing from any cause.