Abstract: This disclosure relates to a plasma generation device particularly adapted to an electrothermal-chemical propulsion system. The device comprises a membranous conductive substance having structural compositions which enable the formation of a continuous and volumetrically distributed plasma arc. The membranous substance is versatile and operates, inter alia, as a fuse wire, plasma incubator, plasma container, plasma distributor, plasma infusion and permeation media as well as a fuel container.

Abstract: The invention relates to an electrical initiator which can be used with an automobile air bag or seat belt pretensioner. The initiator comprises a header, a cup, conducting pins, epoxy pin seals, a bridgewire, a primer, and an output charge. The header and the cup are composed of an insulating dielectric material capable of being ultrasonically welded together. The header secures the pins. Each pin is electrically conductive and each is formed with a buttress knurl to form a seal when each pin is inserted into the header. Additionally, the pins are further sealed to the header by an epoxy sealant. The bridgewire connects the pins together on one side of the header. An electrical signal through the bridgewire generates heat igniting the primer. Primer reacts with the output charge that in turn ignites a solid gas generant that produces gas that fills air bags or activates the gas generator that drives seat belt pretensioners. The primer contacts the bridgewire. The output charge contacts the primer.

Abstract: The inflator for air bags according to the present invention includes a cylindrical housing, an inner cylindrical member provided in the housing, a central cylindrical member provided in the inner cylindrical member, a gas generant packed in an annular space between the central cylindrical member and inner cylindrical member, and an ignition structure for igniting the gas generant. The ignition structure comprises booster charge provided in one end portion of the central cylindrical member, an igniter for igniting the booster charge, and a booster member provided in the part of the central portion of the central cylindrical member which is close to the booster charge, the booster member being made of a nonexplosive material so as to constitute a rod type member extending over substantially the whole length of the central cylindrical member. The ignition structure is capable of generating lengthwise uniform ignition energy.

Abstract: A priming mechanism for a propellant charge, notably for field artillery ammunition, comprising a tube (2) made of a combustible material, whose inner wall is lined with a priming charge which marks out a central channel (5) inside the tube (2), characterised in that the priming charge is formed of several successive layers (3) of black powder granules with a binder (4).

Abstract: An autoignition charge for pyrotechnic automotive airbag in inflation devices is provided in the form of a foil of a synthetic polymer or of a metal, having an adhesive on one surface of the foil and an autoignition material on the opposite surface of the foil. Pieces of foil are readily attached to inflator housings at any suitable location and are secured to the housing by the adhesive on one surface of the foil.

Abstract: A fuse (12) detonates a spin-stabilized projectile (10) after the fuse (12) experiences a preset number of turns. The preset number is communicated (64) to the fuse (12) prior to launch. A semiconductor piezoelectric strain gauge (26) senses stress and provides a signal which is responsive to centrifugal forces experienced by the sensor (26) as a result of projectile spin. A microcontroller (30) repetitively digitizes and translates the sensor signal to determine turn numbers, which the microcontroller (30) integrates to determine the total number of turns experienced by the fuse (12) since launch. When the accumulated turn number reaches (94) the preset number, the fuse (12) detonates the projectile (10). However, an arming duration (76) must have expired before the projectile (10) can detonate, and the projectile (10) can detonate at any time following the expiration of the arming duration when an impact is detected.

Abstract: An igniting unit for a propellent charge, including a central perforated flame guiding tube having propellant rods which are oriented in an axial direction arranged on the outer surface thereof. On the inner surface of the flame guiding tube and on the casing surface of the propellant rods, however, not on the end surfaces of the latter, there is provided an igniting coating, and in which the igniting coating which is provided on the inner surface of the flame guiding tube is enhanced by an igniting powder strip which is oriented to extend in an axial direction.

Abstract: An ignition tube for use with electrothermal chemical combustion ignition projectiles in guns, comprising a tube positionable in a combustion chamber for receiving plasma ignition from a plasma chamber. The tube is formed from high density polyethylene or other materials adapted to release plasma upon contact by plasma ignition electrical energy or pulses. The tube is specifically designed to provide an increasing exit area from the proximal end of the tube toward the distal so as to act upon the longitudinally attenuated plasma, thereby substantially decreasing the amplitude of any reflected shock in the plasma stream. The exit area comprises a plurality of radially extending orifices or holes that have a decreased angle of inclination to the longitudinal axis from proximal end to distal end, such that the orifices form a spiral pattern on the circumference of the tube. This pattern provides a uniform action of plasma on the propellant over the entire length of the ignition tube.

Abstract: An igniting system for a projectile propellant includes a combustible support tube having an outer surface and an inner surface; a plurality of throughgoing apertures provided in the support tube; a free igniting channel coaxially surrounded by the support tube; and an ignition transfer charge formed of a pyrotechnical hard foam layer having a thickness between 1 and 3 mm and being carried on the outer surface of the support tube. The hard foam layer is composed of a large-pore inner layer and two opposite surface layers which are of densely closed structure and between which the inner layer is sandwiched.

Abstract: Integrally incorporated in a squib is a locking feature that allows a projectile to be attached to it any time between assembly of the squib and installation of the squib into the inflator. This design enhances the safety of the squib by permitting handling without the projectile attached. It also minimizes the number of parts required to perform the function of rupturing a burst disk in an inflator by combining the function of the projectile with the protective covering of the squib body.

Abstract: Featured in an air bag inflator in respect of which, during assembly, there is a requirement for the ignition train to be installed last, along with a need to hermetically seal both the gas generant material and the ignition train from the environment, is the use of two independent pressure vessels, one of which contains the gas generant material, filtering and cooling elements and a separate pressure vessel having an open end into which is inserted a squib capable of being activated by an appropriate signal and which contains all of the primary and secondary ignition pyrotechnics, the open end of the pressure vessel being closed by the presence of the squib, the pressure vessel having a necked region in its length which forms a plenum chamber when mated to the second pressure vessel containing the gas generant material, etc.

Abstract: A two-part igniter for inflators used to inflate inflation devices such as air bags, lift rafts, slide chutes, and the like which includes a heterogeneous mixture of an ignition material and a consolidated mass of either i) a pyrotechnic component or ii) a composite propellant. The ignition material can be in a granular form or pelletized. The pyrotechnic component or composite propellant is provided as a pellet which is in immediate contact with the ignition material. The pyrotechnic component or composite propellant lowers the auto-ignition temperature of the two-part igniter. The two-part igniter can be used in inflators which generate all inflation gases from gas-generating compositions and in inflators which include a supply of stored pressurized inflation gases.

Abstract: An igniter holder is designed for use with a model rocket engine for temporarily fixing the igniter in the ignition cavity of the model rocket engine in preparation for launch.

Abstract: A primer including a primer head assembly and a hollow tubular one-piece body attached thereto. The outer surface of the body tapers to its smallest diameter at the forward end thereof and also includes a screw driver tip at its forward end to assist in the insertion of the primer into the propellant charge within the cartridge case as the primer is being attached to the cartridge case. The body is a high temperature, high glass high carbon composite thermoplastic material.

Abstract: A system and method is provided for igniting a propellant with an electrically conductive chemically insensitive polymer. The polymer is an electrical resistance heater to heat the propellant to its ignition temperature. Preferably, the polymer is an organic polymer. Surfaces of the propellant can be coated with the polymer. In the alternative, the polymer can be applied to a hollow bore in the propellant to form a self-pressurizing charge. Advantageously, the present invention controls ignition and prevents unintended ignition of the propellant.

Abstract: An electrothermal chemical cartridge with a fuse of tapering cross section enables higher impulse energy to be imparted to a projectile by means of complete controlled burning of propellant. A long, narrow tube filled with propellant has a fuse on its inside surface with a cross section that tapers toward the discharge end, separated from the electrical ground of the cartridge casing by a layer of insulation sufficiently thin to be destroyed as the fuse ignites the propellant. A high-voltage electrode connected at the back end of the tube provides for application of a pulse of sufficient current density to ohmically heat or burn the fuse in a controlled fashion from the discharge end to the back end. Many such tubes can be bundled together in a large casing for wide barrel guns.

Abstract: An igniter tube for a gas-generating device comprising an elongate cylinder, a primary igniter powder within the cylinder, a closure at one end of the cylinder, and an auto ignition cup disposed at the end of the cylinder opposite the closure is improved by the use of a resin-blocked screen as the closure between the igniter powder and the auto ignition cup.

Abstract: A reusable, semi-flexible molded model rocket engine igniter holder is used to hold an electrically activated igniter in intimate contact with the exposed surface of the model rocket engine propellant until the rocket engine propellant is ignited by passing electrical current through the igniter. The igniter holder, which is inserted in the throat cavity of the rocket engine, is preferably molded with a series of ribs around its periphery which impart a holding force keeping the electrical igniter in place in the engine throat.

Abstract: Ammunition round comprising a forward cartridge 1 including a projectile 6 and a propellant charge 8, a rearward cartridge 2 including a propellant charge 8 and a propellant ignition system 3, 10, 14, and a propellant charge igniter 16 located so as to lie positioned between the first and second propellant charges when the round is loaded, wherein the propellant ignition system includes ignition transfer means 14 for transferring ignition from the rear of the rearward cartridge to the propellant charge igniter and the propellant charge igniter 16 includes ignition propagation means, preferably in the form of igniter cord 26, for spreading ignition laterally to facilitate rapid simultaneous ignition of the two charges.

Abstract: A device is provided for increasing the surface area of the gas generant used in an automotive safety air bag module. Depending on crash conditions, the surface area of the gas generant is increased by shattering the gas generant wafers. One embodiment utilizes a squib having a high brisant zone which upon activation shatters the gas generant wafers. Alternatively, a dual function squib is used which can produce mechanical forces which force a breaking object to impact on the gas generating wafers thereby shattering them and increasing the surface area of the gas generant.

Abstract: A method for confinement of a gun propellant during the initial stage of ignition provides the ignition by electrical, pyrotechnic, or laser irradiation means. A liquid and or a solid propellant is placed in a substantially closed chamber. A portion of the propellant in a conduit of the chamber exits from the chamber and is cooled in the exit conduit by a thermoelectric or cryogenic means to a sufficiently low temperature for producing a viscous, glassy, or substantially solidified condition to enhance the propellant containment. An ignition stimulus is then applied. A closure means in the exit conduit selectively varies the amount of flow whereby a relatively high temperature and pressure are reached from the chemical energy release of the propellant. Venting of the formed combustive products is provided through the exit conduit whereby sufficient thermal energy is generated to sustain combustion and to ignite the next stage.

Abstract: The technical aspect of the invention relates to containers for a propulsive charge in at least two parts. The container (1a-1b)) according to the invention comprises a casing (9a-9b) demarcating an internal space, in which may be positioned, in particular, a propulsive charge, and it is intended to be rigidly affixed to a second container at one of their frontal faces (10a-10b), wherein it comprises means for the conduction of electricity, intended to receive and transmit a signal emanating from the weapon, as well as connecting means for providing, after the first container has been rigidly affixed to the second container, an electrical connection between these conduction means and other conduction means in the second container. Application for tank ammunition.

Abstract: The present invention describes an igniter-destructor device for projectiles, grenades, cartridges, missiles or the like, comprising a thin-walled aluminum capsule, an igniter-destructor charge provided within said capsule, possibly an ignition expediting material within this charge, and a flange piece disposed at the head-end of the aluminum capsule and having an axial bore. The aluminum capsule is coated with a thin-walled plastic jacket which is preferably made from a shrink hose. Furthermore, there is preferably provided a specifically embodied ignition-expediting material which consists of ignition particles statistically distributed within the igniter-destructor charge. Such an igniter-destructor device is characterized by an especially clean and reliable operation as its functional conception, even under high stress occurring in the use of appliances which such igniter-destructor devices are installed into, remains substantionally unchanged.

Abstract: The invention relates to a propellant charge igniter mountable in a propellant charge carrier or in a cartridge. Propellant charge igniter is provided with an expulsion charge to avoid breech flash, said charge being suitable for driving an ignition guide tube completely out of an annular chamber formed between a bottom part and a flame guide tube of the propellant charge igniter.

Abstract: An insensitive pellet ignitor utilizes a slapper type detonator to initiate an insensitive explosive material. The insensitive explosive material is retained in a high strength housing which confines and dissipates the explosion. The insensitive explosive material is retained in a collar placed in a chamber having an orifice leading to propellant. The orifice does not allow the shockwave from the insensitive explosive to prematurely expel the propellant so that the propellant is ignited from the hot gases and particles resulting from the explosion which are ported through the orifice to the propellant.

Abstract: The invention relates to modular containers for propellant charges. The container includes a container casing which partially defines an inner volume for a propellant charge. The container 1a of the invention that shall be rigidly assembled to another container 1b at one of its end surfaces and is characterized in that it comprises electrical connection means ensuring at least one electrical connection to the second container.

Abstract: A device for firing ammunition includes a combustion chamber accommodating several propellant charge members which latter contain a propellant charge and an ignition system for igniting the propellant charge. A fixedly disposed primary coil which receives an ignition signal is provided at the combustion chamber while a secondary coil is arranged in each propellant charge member, this secondary coil being connected to a resistor initiating the ignition system. The magnetic field, changing with time, which is produced by the primary coil penetrates the combustion chamber and induces a current in the secondary coils of each propellant charge member at the same time so that the ignition systems of all propellant charge members are simultaneously activated and ignite all propellant charges at once. On account of the simultaneous ignition of the propellant charge members, rapid firing sequences can be attained.

Abstract: A improved initiator for artillery shell using an explosively generated laser light to uniformly initiate the propellent. A small quantity of a high explosive, when detonated, creates a high pressure and temperature, causing the surrounding noble gas to fluoresce. This fluorescence is directed into a lasing material, which lases, and directs laser light into a cavity in the propellant, uniformly initiating the propellant.

Abstract: A laser actuated thru-bulkhead initiator for transmission of detonation within the initiator without destroying the pressure integrity of the initiator and the seal of the pressure vessel in which the initiator is installed comprises a body portion having an aperture extending throughout the length thereof. This aperture provides an optical path from a laser source to a detonable explosive material positioned within the aperture. The body portion provides a housing for retaining in a first section of the aperture, a primary window element, an attenuator for an explosive shock wave, a second window element, and an explosive material within the aperture and the optical path. A second section of the aperture of the body portion which extends from the outer surface of the second window performs the function of receiving the explosive shock wave energy dissipated from an explosive force released by the detonable explosive composition.

Abstract: An igniter for full head-end web rocket motors comprises two molded urethane hemispherical shells, each of which is lined with a layer of solid propellant fuel, joined together to form a solid propellant-lined spherical pressure vessel, which spherical pressure vessel is strengthened by a wrapping fiberglass around the girth, includes an igniter initiator having an elongated tubular urethane housing that contains ignition material and serves also as a structural tie between the hemispherical shells, and a mounting foot incorporated in the lower portion of the spherical shell to facilitate bonding to the rocket motor's propellant grain, nozzle ports located in the lower portion of the spherical shell being provided for igniter flaming gas discharge and subsequent rocket motor ignition.

Abstract: A safe ordnance initiation system which is safe for normal handling, expoe to strong electromagnet fields, and electrostatic discharge comprises a firing circuit which provides a method for rapidly and efficiently connecting (switching) a charged capacitor to an electrical discharge inititation element; an enclosed and environmentally protected electrical discharge initiation element which provides a means of rapidly dissipating the capacitor charge and converting it to a shock wave and thermal/plasma energy output; a transmission line shock tubing which is connected to the electrical discharge initiation element at one end which is terminated in a target element at the other end thereof; and a target element having the capability for interacting with a predetermined output energy level of shock charge and thermal/plasma energy transmitted through the transmission line shock transfer tube to achieve a desired result for igniting or detonating the target element depending on the type of end termination employe

Abstract: A novel and unique rocket ignition system comprising a novel igniter having copper foil laminated plastic substrate having a electro-conductive pyrotechnic coating disposed on one end thereof and ignitable by means of a special power-supplied igniter clip having offset positive and negative terminals for engaging the igniter and transmitting an electrical current therethrough to initiate combustion of the pyrotechnic coating which in turn ignites a rocket propellant disposed in close proximity thereto. Special means are provided to selectively position and secure the rocket ignition system to a rocket motor.

Abstract: A consumable igniter for a solid rocket motor comprises a substantially spherical reinforced thin case (111) and a combustible charge, in the form of a layer (112), lining the internal surface of the case, with the combustible charge and the case defining a combustion chamber (113). A plurality of through-holes are formed in the case defining respective sonic throats. At least one small container (120) is received in one of the through-holes and projects inwardly toward the combustion chamber (113), the container containing a charge (121) for igniting the combustible charge layer (112) of the igniter (110). An ignition device (125) penetrates into the small container for igniting the charge contained within the small container.

Abstract: A propellant igniter for a cartridge including an ignition tube which extends into the propellant; and with a booster charge arranged at one end of the ignition tube having a pyrotechnic igniting composition therein, which leaves the presence of a central passageway. The igniting composition or charge is formed from a tubular, hardened or set layer constituted of a pyrotechnic lacquer or varnish. Preferably, the pyrotechnic layer is cast into the ignition tube while in a pourable state, and then hardened or cured within the tube. The pyrotechnic layer can also be applied onto a combustible conduit tube for gas fumes, hardened thereon and then inserted into the ignition tube.

Abstract: A spin-stabilized projectile with a correctable trajectory, wherein the projectile possesses lateral or transverse thrust-propulsion devices which are distributed about the circumference thereof, each incorporating an impulse-generating charge inclusive an electrically-activatable detonator arranged beneath a cover which is radially ejectable relative to the longitudinal axis of the projectile. The detonator, with the presence of a connecting cable which initially extends coaxially with the cover and then thereafter extends at an angle relative thereto, is arranged in the transitional region intermediate the impulse-generating charge and the cover, whereby the cover, with conformance of its external contour to the contour of the encompassing casing surface of the projectile, is fixed to the structure of the projectile across a rupture location, which is hermetically sealed radially inwardly of the impulse-generating charge with respect to the center of the projectile.

Abstract: An igniter which is removably insertable in a rocket motor nozzle throat. The igniter includes a sleeve which has a body portion and a plurality of flexible and frangible tab members extending axially from one end of the body portion and spaced circumferentially thereabout and which have first portions which in combination define a diameter which is greater than the nozzle throat diameter. The frangible portions of the tab members in combination define an outer diameter which is substantially equal to the throat diameter. The body portion of the sleeve has a diameter which is greater than the throat diameter. The sleeve is insertable in the nozzle throat by flexing the tab members so that the first portions clear the throat and so that the frangible portions of the tab members are disposed in the throat. The tab members, in combination, have an inner diameter which is substantially equal to the inner diameter of the body portion of the sleeve.

Abstract: A safe/arm explosive delay path for detonating an explosive device and prnting detonation of the explosive device by extraneous factors present in the internal environment. The delay path comprises a detonator and first explosive trail leading to a delay explosive trail composed of explosive material and reactive material. A second explosive trail is connected to the first explosive trail and parallel to the delay explosive trail. The delay trail and second explosive trail terminate in an explosive junction. The explosive junction or explosive switch is a gated diode with the delay trail leading through the diode in the second explosive trail functioning to gate the diode. The gated diode allows a detonation wave propagating through the delay tail to proceed to the explosive device only when a detonation wave has propagated along the second explosive trail and gated the explosive diode prior to the arrival of the delay detonation wave.

Abstract: This invention relates to a course correction unit, specifically but not exclusively for use on a spin stabilized guided projectile which can produce high speed instantaneous course correction.

Abstract: Ignition of a separating charge in a cavity between a flash-conducting tube and a casing of a propellant charge igniter extending below a combustible tube is brought about by the propellant gases passing through priming bores from the outside of the propellant charge igniter to be used in a breech of a cannon or like weapon. This requires a seal acting in the manner of a valve being positioned at the flash-conducting tube head and being urged towards the casing. An especially suitable sealing means in a sealing ring located in an annular groove having a cross-section shape similar to a trapezoid. In case, for example, on account of low temperatures, the pressure buildup of the propellant gases occurs more gradually, the separation of the combustible tube from the bottom piece is thereby also automatically initiated at a later point in time. Thereby, flashback in the breech zone of the cannon is avoided and ballistics are improved.

Abstract: An igniter for high-performance rocket motors having a full head-end web of propellant in the forward end of the motor includes a shallow cup-shaped fiberglass reinforced urethane container, dual rubber orifice arrangement in a plurality (12) of peripherally spaced exhaust ports, a shear key or lip for interlocking into the rocket motor propellant, and a saddle arrangement for initiator tube retention.

Abstract: A self consumable initiator is comprised of a consumable material selected from pyrotechnics, propellants, exothermic alloys, and primary explosive compositions, and one or more lengths of a fiber optic material in physical contact with or embedded in the consumable material. Uniform density of laser energy is transmitted through the fiber optic material to the consumable material in sufficient amount to stimulate the consumable material to its respective ignition point. The consumable material self consumes as it serves to ignite a larger quantity of material such a solid propellant grain. The consumable material is in the form of pellets powders, or castable shapes. When installed in a rocket motor case, the self consumable initiator is bonded or installed as a castable pyrotechnic which conforms to the contour of the front end of a solid rocket motor case. Subsequently, a solid propellant grain is bonded or cast in place in intimate contact with the initiator.

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 device for ejecting ammunition containers from a war head has transverse to the war head longitudinal axis a bellows, which holds the ammunition containers in a plurality of concave pockets. The bellows is inflated by a gas generator including a gas-permeable tube extending along the longitudinal axis. In order to achieve a wide range of variations in the behavior of the ammunition containers in the process of being ejected, a propellant charge of the gas generator is particulate, with at least one ignition cord extending along the longitudinal axis of the tube around which a particle ignition mixture is arranged, so that the hot particles during burn-down of the ignition mixture are pressed between the particles of the propellant charge. A daming serves for building up the initial pressure required for the burning down of the propellant charge.

Abstract: A device for ejecting ammunition containers from a war head has, transversely to the war head longitudinal axis a bellows which accepts individual ammunition containers in concave circumferentially sparse pockets (6). The bellows is inflated by a gas-generator including a gas-permeable tube extending along the longitudinal axis. In order to achieve as wide a variation range of ejection behavior of the ammunition container as possible, the propellant charge of the gas generator is particulate and at least one ITLX ignition cord extends along the longitudinal axis of the tube, so that the hot particles during burndown of the ITLX ignition cord are pressed between the particles of the propellant charge (12). A damming serves to build up the initial pressure required for the burn-down of the propellant charge.

Abstract: A method of detonating explosive charges for the breaking of rock and ore comprises the use of two sets of components, one set within the explosive charge and the other set at the surface of the explosive. The set within the exposive comprises a detonator, a first delay element and a passive energy storage device such as a capacitor. The second set which is able to communicate with the first comprises a power source, a second delay element and a means for receiving signals from a remote command source. In a preferred embodiment, the first delay element has a fixed delay and the second delay element has a programmable delay.The method permits of versatility and precision in the use of explosives, using relatively inexpensive components.

Abstract: A propellant charge for the reduction of base eddying or drag of a shell 12 with a centrally disposed ignition conduit and an ignition device for the charge disposed in the conduit. To improve the ignition readiness of the propellant charge, the inner surface of the propellant charge, which surrounds the ignition conduit, is formed so that it conically narrows in the aft direction. Additionally, the inner surface of the propellant charge may be provided with stepped sections. Finally, the ignition conduits disposed in the housing of the ignition device may be disposed at an angle relative to the longitudinal axis of the propellant charge so that they face the inner surface thereof.

Abstract: Pyrotechnic igniter capable of being fitted in, and withdrawn from the throat of the nozzle of a propulsion unit. The igniter comprises parts bearing on the convergent section (1a) and on the divergent section (1b) of the nozzle. In order to permit the fitting and the withdrawal of this igniter at any time, while improving the conditions of ignition of the propellent charge, the igniter comprises, on the one hand, an internal rupture member (2) and, on the other hand, external means of fitting (3) which are capable of expanding radially, this internal rupture member initially maintaining the external means of fitting in a deployed position.

Abstract: A propellant configuration for a solid propellant rocket motor, comprising a generally cylindrical housing containing a generally cylindrical main grain having a central cavity, and an igniter assembly supported in the central cavity and having means therein for bringing about combustion. At the time of actuation of the igniter assembly, hot gases are directed along flutes formed in the interior of the main grain, to cause burning thereof to take place. Advantageously, the propellant utilized in the main grain is the same as utilized in the igniter assembly, with the burn surface area of the igniter grain being in a pre-established relationship to the burn surface area of the fluted main propellant grain, such that the igniter grain will be totally consumed at the time that the flutes of the main propellant are consumed.

Abstract: The present invention relates to a non-primary explosive detonator comprising a hollow tube (1) with a closed end having a chamber containing a secondary explosive base charge (8), an opposite open end provided with or for the insertion of an igniting means (9, 15,16), and an intermediate confinement adjacent said chamber and containing an initiating charge (7), a delay composition (6) optionally being present adjacent said initiating charge.

Abstract: A propellant charge igniter is provided with a metallic igniter tube which is consumed along with the main propellant charge. The combustible igniter tube is flexibly attached to a conventional primer head. An elastomeric tube, a springreinforced tube, or a tube impregnated with a wire mesh can be used to achieve a flexible connection. These tubular elements may be bonded to the primer head and igniter tube, or mechanically attached by means of threaded couplings which are crimped over the elastomeric tubing.