Abstract: A security system including: a detector that senses and detects a physical threat to persons in a protected area; and a defensive weapon in the protected area that deploys to disable a detected physical threat. The defensive weapon can be, for example, a guided ordnance, a guided weaponized UAV, or a combination thereof. Also disclosed are methods of making and using the security system.

Abstract: A jet engine includes an inlet that takes air, and a combustor that burns fuel using the air. The combustor includes a fuel injector and an igniter for igniting a gas mixture of the air and the fuel. The igniter ignites and activates automatically by heat and pressure created by compression of the air that has been taken in through the inlet.

Abstract: A separate-loading firearm uses a battery-powered electric resistance heating element to ignite a propellant charge. Both ignition reliability and ballistic reproducibility are enhanced when a first portion of the propellant charge is consistently and firmly packed into a cavity formed in a rear surface of a bullet. This first portion may be sealed in the cavity by a membrane. A second portion of the propellant charge is packed within a firing chamber so that it abuts both the heating element and the first portion of the propellant charge.

Abstract: A combustor of a jet engine includes a fuel injector, an igniter for igniting a gas mixture of air and fuel, and a flame holder. The igniter is disposed in the flame holder. After an activation of the igniter, the igniter disappears, and a space after the disappearance functions as a flame-holding space.

Abstract: A jet engine includes an inlet (11) which takes in air and a combustor (12) which combusts fuel with the air. The combustor (12) has an injector (20), a plurality of flame stabilizers (21, 22) and a vanishment section (31). The injector (20) injects the fuel. The plurality of flame stabilizers (21, 22) can maintain the flame (F) used for combustion in the combustor (12). The vanishment section (31) is provided to cover the dent of the first flame stabilizer (21) which is situated on the side near to the inlet in the plurality of flame stabilizers (21, 22), and vanishes with the passage of time in the flight.

Abstract: A containment canister is provided for loading a vehicle. In the canister, the vehicle is restrained by a nose cap and a ring which conforms to an aft section of the vehicle. Longitudinal leads support the vehicle and provide glide surfaces during a launch. A casing with flow ports is affixed to an aft end of the containment canister with the casing encompassing an actuator with an extendable arm and an attached plug. The plug is sized to move in alignment with each canister toward a sealing ring. When the arm is extended; the plug seats against the ring. To eject the vehicle, a signal is sent an actuator to retract the plug aft of the flow ports. As the canister is flooded by a water impulse thru the flow ports; the impulse contacts the aft end of the vehicle to expel the vehicle.

Abstract: A method for explosive cutting using converging shockwaves, and an explosive cutting device are disclosed. The method includes providing a projectile with an explosive charge, positioning the projectile over the object so it extends along an intended line of cut, and detonating the explosive charge so that the projectile is accelerated toward the object, wherein the projectile either impacts on the object and the projectile includes a wave-shaping element which is shaped such that the impact generates converging shockwaves in the underlying object to be cut causing a crack to be propagated through the object along the intended line of cut; or impacts on a wave-shaping element in contact with the object, the wave-shaping element being shaped such that the impact generates converging shockwaves in the underlying object causing a crack to be propagated through the object along the intended line of cut.

Abstract: A diversionary device has a housing containing a pyrotechnic cartridge (24) with an ignitable fuse (52). A firing arrangement includes an ignition cap (60) containing a primer charge (54). Passageways (74, 82) in the housing and ignition cap define a first flow path from the primer charge to a region of the housing in which the fuse (52) is located through which flash from the primer charge can flow to ignite the fuse (52). A further flow path connects said region of the housing with the exterior of the housing to supply the fuse with oxygen for reliable burning. The device may be a multi-burst device containing a plurality of cartridges (24) and the first flow path may include a flash divider (86) for directing a proportion of the flash from a primer charge on to the fuse (52) of each cartridge. The housing may be separable to allow replacement of the cartridges (24).

Abstract: A scalable, inert munition data recorder cartridge. This inert cartridge allows users to record data from within a weapon system feed chute, breach, and extractor port. This cartridge is adaptable to any weapon system, packaging unit, environmental chamber, or other ammunition holding and storage device. Although the cartridge is designed to interface with a weapon and ammunition packaging based on its shape, it still functions as designed regardless of its location and application. This would allow the cartridge to be placed anywhere an actual live cartridge of ammunition could be placed.

Abstract: A projectile (10) comprises a cylindrical body (12) with a first (leading) end (14) and a second trailing axially opposed end (16). An internal cavity (18) is formed between the ends (14 and 16) and holds a volume of propellant material (22). The first end (14) is closed by a nose (20) that is fixed to the body (12). The end (14) is sealed with a base seal (26) that seats a primer (24) for igniting the propellant (22). The primer (24) is located inboard of the second end (16) and the base seal (26) to reduce the likelihood of accidental activation. Seals (30) are formed about the body (12) for maintaining gas pressure of deflagrating propellant. The seals (30) may be formed integrally with the body (12) or separately from the body (12) and seated in respective grooves (40) formed circumferentially about the body (12).

Abstract: The present invention relates to a method and a shell (1) for achieving variable firing range and effect when firing from a launcher, which shell (1) contains a firing charge (10), a rocket motor charge (6) with gas outlet (8), a rocket motor nozzle (9) and an active part (5). According to the invention, this is achieved by virtue of the fact that the shell (1) also contains a release mechanism (15) for releasing the rocket motor nozzle (9) from the rocket motor charge (6) after a time delay determined with regard to firing range and effect, and that the rocket motor charge (6) comprises a propellant which is detonable.

Abstract: Projectiles with sealed propellant are described herein. In one embodiment of the invention, a projectile includes a chamber having a propellant charger, an exit from the chamber for release of propellant gases into a barrel when the propellant is ignited to fire the projectile, and a seal to block the exit which is opened by ignition of the propellant within the chamber but is resistant to ignition of other propellant in the barrel, where the seal is carried from the barrel by the projectile after the ignition. Other methods and apparatuses are also described.

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 primer composition that includes red phosphorus having an acid scavenger and a polymer thereon. The primer composition includes at least one other component that is substantially free of lead. The other component is at least one oxidizer, or at least one oxidizer and at least one of at least one secondary explosive composition and at least one energetic binder. The primer composition optionally includes at least one element having an ionic charge to ionic radius ratio of 4 or of 8, such as magnesium, zirconium, aluminum, silicon, titanium, tungsten, alloys thereof, and combinations thereof. The red phosphorus and the at least one oxidizer are present in the primer composition at approximately stoichiometric amounts. An ordnance element including the primer composition is also disclosed.

Abstract: A ram jet engine including a combustion chamber ending in a gas injection nozzle, a cruising propulsion unit fee ding liquid propellant into the combustion chamber, and at least one air duct for feeding air intended for combustion of the fuel in the combustion chamber. A rigid tubular element is incorporated into the ramjet engine, with an interior volume of the rigid tubular element being divided into two spaces by an intermediate transverse partition. One of the spaces houses the cruising propulsion unit while the other space houses the combustion chamber. Passages are cut into the intermediate transverse partition to allow feeding of liquid fuel into the combustion chamber, and the air duct is mounted on the tubular element to feed the combustion air through the tubular wall of the tubular element.

Abstract: A projectile (10) comprises a cylindrical body (12) with a first (leading) end (14) and a second trailing axially opposed end (16). An internal cavity (18) is formed between the ends (14 and 16) and holds a volume of propellant material (22). The first end (14) is closed by a nose (20) that is fixed to the body (12). The end (14) is sealed with a base seal (26) that seats a primer (24) for igniting the propellant (22). The primer (24) is located inboard of the second end (16) and the base seal (26) to reduce the likelihood of accidental activation. Seals (30) are formed about the body (12) for maintaining gas pressure of deflagrating propellant. The seals (30) may be formed integrally with the body (12) or separately from the body (12) and seated in respective grooves (40) formed circumferentially about the body (12).

Abstract: A ring portion including: a ring body; and one or more actuators formed therein for providing thrust to a projectile and configured for fastening to a shell of an airborne device to form a portion of the shell. The airborne device can be a projectile.

Abstract: An actuator stack is provided and having two or more individual actuators stacked in a longitudinal direction. Each of the two or more actuators having a solid detonation charge; a primer for igniting the detonation charge; and detonation wiring for powering the primer; and wherein at least one of the two or more individual actuators comprise an accelerating nozzle having at least a convergent section terminating at a throat.

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 gas generating propulsion system includes an igniter containing an igniter propellant and an auto igniter. A rocket motor is coupled to the igniter and has a housing containing a main propellant, a rocket motor throat and a nozzle. A release port extends through a portion of the rocket motor. This gas release port has a variable diameter through bore in fluid communication with the main propellant. In this way, the through bore has a variable area that forms an unobstructed open area with a cross-section effective to discharge gas generated by the main propellant such that a pressure increase within the housing remains below a safety value for the housing.

Abstract: A simple device for generating pyrotechnic effects, in which an enveloping body (11) is formed from a plurality of interconnected plate-like layers between which the pyrotechnic charges (10) as well as the igniter means (12) are embedded. A configuration of the igniter means (12) as heating resistors, in particular as heating resistors whose conductors run in a meandering path. Such igniter means (12) are particularly suitable for use in the formation of a plate-like enveloping body consisting of a plurality of layers. By virtue of this enveloping body, the device assumes a shape comparable to that of a credit card or bank card.

Abstract: A plasma antenna generator includes an ionizable material, an explosive charge capable of projecting the ionizable material upon detonation, and a detonator coupled with the explosive charge. An electromagnetic pulse transmitting system includes an electromagnetic pulse generator and a plasma antenna generator capable of reradiating an electromagnetic pulse emitted from the electromagnetic pulse generator. A method includes providing an explosive device comprising an ionizable material, detonating the explosive device to propel the ionizable material, and ionizing the ionizable material to form at least one plasma trail. A sensing system includes an electromagnetic pulse generator, a plasma antenna generator capable of reradiating an electromagnetic pulse emitted from the electromagnetic pulse generator, and a sensing system capable of receiving and analyzing at least a portion of the electromagnetic pulse after being reflected from an interface.

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 projectile (10) comprises a cylindrical body (12) with a first (leading) end (14) and a second trailing axially opposed end (16). An internal cavity (18) is formed between the ends (14 and 16) and holds a volume of propellant material (22). The first end (14) is closed by a nose (20) that is fixed to the body (12). The end (14) is sealed with a base seal (26) that seats a primer (24) for igniting the propellant (22). The primer (24) is located inboard of the second end (16) and the base seal (26) to reduce the likelihood of accidental activation. Seals (30) are formed about the body (12) for maintaining gas pressure of deflagrating propellant. The seals (30) may be formed integrally with the body (12) or separately from the body (12) and seated in respective grooves (40) formed circumferentially about the body (12).

Abstract: A gas generating propulsion system includes an igniter containing an igniter propellant and an auto igniter. A rocket motor is coupled to the igniter and has a housing containing a main propellant, a rocket motor throat and a nozzle. A release port extends through a portion of the rocket motor. This gas release port has a variable diameter through bore in fluid communication with the main propellant. In this way, the through bore has a variable area that forms an unobstructed open area with a cross-section effective to discharge gas generated by the main propellant such that a pressure increase within the housing remains below a safety value for the housing.

Abstract: A projectile having variable kinetic energy contains multiple propellant charges (14) that are able to be individually selected for ignition. Each charge (14) has a selectable initiator (15) that may be triggered by a wired or wireless firing system, preferably an inductive system, in order to determine the kinetic energy of the projectile. The projectiles are axially stacked for firing from the barrel of a weapon, with nose portion (11) shaped to seal against tail portion (12) of a leading projectile. Ignition gas exit ports (17) are located in nose portion (11) for propulsion of a leading projectile from the weapon. Alternative, the ports may be located in tail portion (12) for propulsion of each respective projectile. Charges (14) may be distributed around the longitudinal axis of body (10) of the projectile.

Abstract: A projectile (10) comprises a cylindrical body (12) with a first (leading) end (14) and a second trailing axially opposed end (16). An internal cavity (18) is formed between the ends (14 and 16) and holds a volume of propellant material (22). The first end (14) is closed by a nose (20) that is fixed to the body (12). The end (14) is sealed with a base seal (26) that seats a primer (24) for igniting the propellant (22). The primer (24) is located inboard of the second end (16) and the base seal (26) to reduce the likelihood of accidental activation. Seals (30) are formed about the body (12) for maintaining gas pressure of deflagrating propellant. The seals (30) may be formed integrally with the body (12) or separately from the body (12) and seated in respective grooves (40) formed circumferentially about the body (12).

Abstract: A long range artillery shell having a rocket motor which comprises a combustion chamber (shown filled with solid propellant 9, burn inhibitor 10, igniter material 13 and propellant support 11,12) which has at one end a plenum chamber 8 and a rocket nozzle 14 for venting the plenum chamber 8. The propellant 9 is arranged in an end-burn configuration and housed within the combustion chamber and the propellant support 11,12 is located between the propellant 9 and the plenum chamber 8 and is capable of preventing entry of unburnt propellant into the plenum chamber 8 while permitting, in use, the substantially unhindered transfer of propellant combustion products to the plenum chamber 8.

Abstract: An assembly for indicating when a transient electronic event has occurred on a mobile platform is provided. The assembly includes a housing and a flash-producing device that communicates with the mobile platform and produces a flash approximately when the event occurs. The housing couples to the body of the mobile platform and contains the flash-producing device in such a manner that the flash is observable. Preferentially, the assembly also includes a faceplate that couples to the housing and maintains an aerodynamic profile associated with a surface of the body when the assembly is coupled to the mobile platform. In another preferred embodiment, the assembly is adapted for use with an inert JDAM weapon and the event is the fuze command of the weapon.

Abstract: This invention relates to a gas generator having two or more compartments, each with a separate initiator, with one compartment discharging before another, i.e., the compartments discharge sequentially. Each compartment has the same propellants, but the propellants have different geometries in each compartment, which results in different rates of gas evolution from each compartment. The gas generator has a rapid initial inflation, followed by a more gradual inflation rate in the subsequent stages, improving safety to occupants. One propellant used for the gas generator comprises (1) ammonium nitrate as the oxidizer, (2) a fuel such as CL-20. and (3) a binder such as polycaprolactone. A second propellant comprises by weight approximately 70-95% energetic nitrate fuel, 5-25% energetic polymer binder and 0.1-5% flash suppressant. No hot metal particles (e.g., CuO) are generated in the new systems.

Abstract: A propulsion-assisted projectile has a body, a cowl forming a combustion section and a nozzle section. The body has a fuel reservoir within a central portion of the body, and a fuel activation system located along the central axis of the body and having a portion of the fuel activation system within the fuel reservoir. The fuel activation system has a fuel release piston with a forward sealing member where the fuel release piston is adapted to be moved when the forward sealing member is impacted with an air flow, and an air-flow channel adapted to conduct ambient air during flight to the fuel release piston.

Abstract: A propellant burning system and method useful in a rocket motor or projectile firing device burns a continuous main propellant grain of relatively soft propellant material selected from uncatalyzed or partially catalyzed propellants. A separating device divides the propellant grain into a large number of fragments of high-surface area during the burn and an activation mechanism for causing said separating device to operate on the main propellant grain and to ignite and control the burning thereof.

Abstract: Base bleed unit comprising a surrounding housing (1) surrounding at least one mass flow generating gun powder charge (7), and having at least one outlet hole (6, 6′) extending through a rear wall (3) of the housing (1), in which also at least one igniter charge (4) is arranged. According to the invention, an internal and the rear wall (3) adjacent portion of the mass flow generating gun powder charge (7) is arranged abutting a preferably substantially conically narrowing supporting wall surface extending from the rear wall (3). The preferably substantially conically narrowing supporting wall surface may comprise a centrally located member (5), extending from and integrated with the internal surface of the rear wall (3) of the base bleed unit, arranged to act as a supporting surface with its external surface, or with such a member attached to said internal surface. The preferably substantially conically narrowing wall surface may also comprise a collar shaped member.

Abstract: A rocket launching system employing ignition apparatus that is used with a small rocket to launch the rocket from a gun. The rocket is equipped with acoustic (pressure) and optical (thermal) sensors that detect a pressure pulse and light flash of a primer charge used to fire the gun. The simultaneous detection of the pressure pulse and the light flash by the sensors generates output signals that are used to complete an electrical circuit in an electronic ignition circuit that activates an igniter that ignites a rocket motor.

Abstract: A device for initiating burning of an explosive or propellant material subjected to external heating prior to detonation is described, the device comprising at least two materials, at least a first one of which materials melts at a temperature below the temperature at which detonation of said explosive or propellant material is induced and reacts with said second material to produce an exothermic reaction to cause initiation of burning in said explosive or propellant material.

Abstract: A rocket ignition system adapted for use with a missile having a rocket motor is provided. The rocket ignition system comprises (a) a first circuit for detecting an optical impulse and providing a first signal in response thereto; (b) a second circuit for detecting a pressure wave and providing a second signal in response thereto; and (c) a third circuit for launching the missile in response to the first and second signals. The rocket ignition system, which is easily adapted to existing missiles and rocket propelled devices, can reliably distinguish between the firing of a primer and other acoustic events occurring in noisy environments, such as a battlefield.

Abstract: A pyrotechnic ignition device for a gas generator (G), in which: (i) at least in the vicinity of the primary charge (CP), the transmission line (L) is at least substantially perpendicular to the longitudinal axis (X--X) of the outer case (E) of the generator (G); (ii) the end of the transmission line, provided with a deflagrating terminal lead charge (r), emerges in a sealed intermediate chamber (CI); and (iii) the intermediate chamber (CI) is connected to the primary charge (CP) via at least one throttling vent (e) having an axis (1--1) at least approximately parallel to the longitudinal axis (X--X) of the outer case (E).

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: A gun launched rocket motor is provided with a filler material to fill all f the free volume in the rocket with a void-free incompressible "filler". The described filler material is selected from a solid, semi-solid, or liquid having many properties closely comparable to the rocket propellant, especially match the density, chemical compatibility, coefficient of thermal expansion, and thermal stability. The filler material functions to provide the required physical support to various propellants to survive gun launch. A preferred filler material is a completely fluorinated organic material which is a liquid which is compatible with various solid rocket propellants and can readily be ejected from the chamber by pressurization from conventional igniters or combustible cords such as Rapid Deflagrating Cord, RDC. These completely fluorinated perfluoro compounds, which are designated as C5-18 compounds, are marketed as Fluorinert Brand Electronic Liquids by 3M Corporation, St. Paul, Minn.

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: A penetrating vehicle having a rocket motor includes an elongated projectile body with a forward section for holding a payload and a rearward section for housing the rocket motor. The vehicle contains a fuse that ignites the propellent of the rocket motor during impact of the projectile body with a surface barrier. The propellent provides high thrust in a rapid burn time and thereby counteracts undesirable deceleration forces acting on the body during impact. The high thrust also promotes a maximum penetration of the projectile body within the surface barrier.

Abstract: A combustible ignition system for use in an illuminating flare warhead. The ignition system includes a pickup charge positioned contiguous the separation charge of the ignition initiator. The pickup charge is positioned such that the firing of the separation charge triggers combustion of the pickup charge. The pickup charge extends to a combustible train which comprises a continuous thin-layer explosive composition positioned within a plastic tubing. The firing of the pickup charge creates sufficient shock that the combustible train is detonated. The combustible train extends along the flare casing adjacent the parachute system and the illuminant. At the head end of the warhead, the explosive train connects to an output charge. The explosive shock of the explosive train is sufficient to detonate the output charge. The output charge transfers the combustion to a BKNO.sub.3 pellet basket within the illuminant igniter of the warhead.

Abstract: An igniter (18) provides rapid longitudinal and radial propagation of the ignition reaction. The igniter may comprise a pyrotechnic material and an inorganic binder, such as silica, carried on a carrier web (10) which may be fiber-glass. One or more layers of coated web (10) are disposed to provide an igniter (18) of cylindrical configuration and having a hollow core. The coated layers are permeable to the ignition reaction to facilitate radial propagation of ignition. The hollow core and the continuous nature of the pyrotechnic layers promotes longitudinal propagation of ignition. The igniter may consist mostly or entirely of inorganic materials to reduce or eliminate the formation of carbon monoxide upon ignition, and may be contained within a radially perforated sheath (20) to form a radial ignition device (25).

Abstract: A process of forming an igniter in an aft-end assembly for a solid rocket motor, the assembly having an internal cavity and comprising at least one element selected from the group consisting of a nozzle, a blast tube and an exit cone, which process comprises positioning an ignition package comprising pyrotechnic material and an initiator in the assembly cavity and causing a polymer foam to expand and cure in the assembly cavity and around the ignition package, so as to embed and secure the ignition package, form an aft closure, and for the igniter as an integral portion of the assembly.

Abstract: A device for accelerating a projectile to an extremely high velocity includes a launch tube having electrodes engageable with the projectile assembly for applying a large electrical voltage to it, the projectile assembly includes a pair of travelling electrodes fixed to the rear end of the projectile and engageable with the launch tube electrodes during the travel of the projectile assembly through the launch tube. The travelling electrodes define a spark gap which, under the high voltage applied from the launch tube electrodes, forms a high-temperature, high-pressure plasma arc travelling with the projectile and effective to increase its acceleration.

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: This invention relates to a passive self-contained auto ignition system for a hydrogen-oxygen fueled rocket engine. When the fuel for the engine is turned on, the gas pressure in the inlet tube 1 can be used to heat a small portion of the hydrogen in a resonance tube 4 and inject hot hydrogen into the combustion chamber 11 to ignite the hydrogen-oxygen fuel mixture. Once the ignition has started, the pressure in the combustion chamber changes the pressures in the resonance cavity 3, which then shuts off the resonance tubes' heating ability and so shuts off the ignition. If the fuel supply is shut off the engine is turned off and can be restarted by turning the hydrogen-oxygen supplies back on causing the resonance tube to re-ignite the engine.

Abstract: An electropyrotechnic device for sequentially triggering the operation of a battery of gas generators. The ignition of double-base propellant blocks is obtained by the combination of EFI and an IFOC, arranged so that the airtight barrier between the cavity containing the donor secondary explosive and the downstream chamber containing the secondary receiving explosive is only one part of the closing element of the back end carrying the nozzles, integral with the ring. The control electronics of the EFI are contained inside a housing capping the back end of the powder generator with the entire system being closed by a cap.

Abstract: The present invention relates to a method and an apparatus for producing rapid cross-ignition of preferably elongate powder or pyrotechnic charges, such as the propellant charges in impulse motors for correcting the trajectory of shells, rockets and missiles. The cross-ignition is produced by initiation of an elongate, extremely fast-burning or detonating primer charge with an extremely low explosive force which has been arranged in contact with at least part of the periphery of the propellant charge. The primer charge forms a tube whose cross-ignition effect is advantageously complemented by an inner, slower burning powder core which is combusted with deflagration.