Abstract: A rocket without tail flame includes an outer socket which receives an ignition unit, a first bullet, a second powder filling unit, a hollow aluminum tube and a second bullet therein. A rocket head is fixed to the outer socket. The firing pin of the rocket launcher hits the primer of the second bullet to shoot the head of the second bullet, the rocket is launched from the rocket launcher. No tail flame is generated because only the powder in the second bullet is ignited. The head of the second bullet hits the firing pin of the ignition unit to ignite the primer of the first bullet so that the first powder of the first bullet is ignited. The second powder in the second powder filling unit is ignited after the rocket flies 3-5 seconds. There are two stages of ignition, and the rocket can carry heavier load.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion, at least one rocket motor that propels the submunition inside of a target volume, and an oxidizer for the incendiary portion and rocket motor. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure to thermalize the contents thereof without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein.

Abstract: The present invention provides an improved kinematic countermeasure flare and method of constructing the same wherein the housing has integrated internal features. The flare nose weight is set at the end of a die core prior to molding for integration with the housing. Longitudinal grooves and other recesses in the die core allow for the formation of internal longitudinal ribs which propellant can bond to and a retaining bead for retaining the nose weight in the housing which are integrated with the housing. Propellant is cast into the formed housing. A propellant shaping mandrel is then inserted into the formed housing thereby forcing the propellant into the internal cavity created by the integrally molded longitudinal ribs, the shaping mandrel and the wall of the flare housing such that the propellant is bonded to the interior housing wall and the longitudinal ribs.

Abstract: A quaternary salt is added at low concentrations to a solid propellant, thereby increasing the conductivity of the polymeric binder to provide for safe discharge of static electricity at relatively low potentials.

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

Abstract: A missile includes a pyrotechnic charge. The missile is constructed in such a way that the pyrotechnic charge is made to burn deflagratively when the missile is used correctly. The pyrotechnic charge includes a mixture containing at least one metal or a metal alloy as a fuel and at least one metal oxide as an oxidizing agent. The fuel and the oxidizing agent are selected in such a manner that they can react with one another by burning. The mixture is compressed to a density of at least 85% of a theoretical density of the mixture, and the fuel, the oxidizing agent and a quantitative ratio between the fuel and the oxidizing agent are selected in such a manner that a density of the mixture is at least 6 g/cm3.

Abstract: A decoy device and system for anti-missile protection and an associated method are provided. The decoy device includes a propellant and a tank containing the propellant. The decoy device also includes an outlet defined in the tank, and a catalyst contained within the tank and capable of exothermically reacting with the propellant to emit a gas having a heat and pressure. The heat generated by the reaction is radiated by the decoy device is capable of attracting a missile, while the gas is expelled through the outlet to provide thrust to the decoy device.

Abstract: An infrared emitting device produces a certain heat emission. The device has a heat source for generating a specific amount of heat for heating inert material to a given temperature and expelling this heated material to form a cloud. The heated inert material produces an infrared emission for anti-missile operations.

Abstract: A countermeasure for luring an incoming hostile missile away from a vehicle is provided. The countermeasure includes a housing, an infrared-emission body containing a sublimation compound in a solid state, a heating source for converting the sublimation compound into a vapor state, and a case containing the infrared-emission body. The case includes an outlet for discharging the sublimation compound in the vapor state into the atmosphere, where the sublimation compound is returned to the solid state in the form of a discrete cloud of particles. Also provided is a method for using the countermeasure, for example, to evade a hostile missile.

Abstract: A kinetic fireball incendiary munition is provided having an outer shell or bomb casing, one or more incendiary submunitions therein, and an igniter therefore. Each of the submunitions includes an incendiary portion and at least one rocket motor that propels the submunition inside of a target volume. The submunitions liberate sufficient heat to produce elevated temperatures inside of a target structure, without creating a substantial overpressure or explosive effect. The incendiary portion includes a solid propellant and, optionally, one or more energetic materials selected from the group consisting of phosphorous, boron, magnesium, aluminum, Fluorinert™-aluminum and BKNO3. The incendiary submunition may be in the shape of a ball or a circular disk with a rocket motor therein.

Abstract: The pyrotechnic animal dispersal device includes an aerodynamic stabilizer for attachment to a pyrotechnic rocket cartridge and a connector sleeve for joining an explosive cartridge to the rocket cartridge. The connector sleeve has an annular disc disposed therein so that slow burning fuel from the rocket cartridge can pass through the disc and detonate the explosive cartridge when the rocket cartridge nears the end of its flight, thereby extending the range of the explosive cartridge. The cartridges are of the pyrotechnic variety launched from a handheld launcher.

Abstract: The invention relates to a pyromechanical separating element having a hermetically sealed pyrotechnic pressure element (2), which is installed in a housing (1) and has a gas-forming pyrotechnic charge, and a detachable latching pin (5) which is separated from the pressure element (2) by a driving volume (19) and is inserted into the housing (1), wherein a first securing point is arranged on the housing (1) and a second securing point is arranged on the latching pin (5), and the latching pin (5) is anchored on the housing (1) by way of an arresting and force-limiting element (8).

Abstract: A lateral thrust control is provided for influencing the flight trajectory of a projectile. The control has a main control unit; a central, axially extending main recess in the main control unit; a plurality of thruster recesses in the main control unit for accepting correction thrusters; an ignition element for one of the correction thrusters disposed in each of the thruster recesses; and at least one tubular conductor support of an electrically insulating material arranged inside the main recess of main control unit. At least some of the electrical conductors are in the form of conductive tracks fixedly arranged on the at least one tubular conductor support such that a particular contact element for a particular ignition element contacts the conductive track assigned to the particular contact element.

Abstract: A fireworks artillery shell for use as a consumer firework which may be propelled by the use of a mortar is provided which includes a casing, a lift charge, an effects charge, a timing fuse and an ignition fuse, and seals. The seals are provided within the casing above and below the effects charge to increase the burst effect of the effects charge. The lift charge is positioned within the casing and below the lower seal, and upon ignition, lifts the fireworks artillery shell into the air. The seals promote a harder break and more explosive effect from the effects charge without interfering with the lifting charge.

Abstract: A fireworks device, including a number of light effect devices as a replacement for traditional pyrotechnic stars. Each light effect device includes electrical/electronic light sources, preferably high-intensity light-emitting diodes, an energy-storage device and a control device. The light effect device for use in such a fireworks device can be used together with a fireworks system, a fireworks rocket and a ground firework in which the firework device is included.

Abstract: A shaped charge tubing cutter includes a minimal contact suspension to isolate the cutter explosive from the housing and sub structure. A charge detonation booster main-cavity is located on the juncture of the charge truncation planes. Explosive in the booster main-cavity is detonated by a shielded primer path. Explosive density in the primer path is less than the main-cavity density. A dense, powdered metal SC liner and an abruptly stepped jet window in the tubing cutter housing improve performance. The axial span of the jet window is preferably aligned with the axial span between the liner bases. A testing apparatus and procedure inexpensively verifies downhole performance.

Abstract: The MLRS1 artillery rockets (11) which are stored in the depots of the consumer can enjoy in a technologically non-critical fashion an increase in performance in the sense of a substantially improved degree of delivery precision, insofar as the ogival head (13) is temporarily cut off so that it is possible to fit into same and thus into the foremost region of the original payload space (15), which is behind the fuse (12), in a position of surrounding the pyrotechnic delivery ejection system, an annular assembly frame (21) for a transverse thrust unit (23) with reaction elements (25), which blow out radially around the rocket, which, in dependence on position, can be individually triggered by a navigation satellite-supported course correction unit (20) which is also fitted there.

Abstract: A fin disengagement device for limiting the range of a projectile uses an electronic safe and arm circuit to sense launch and spin levels. Once armed, the stored energy from the electronic safe and arm circuit is dumped into an initiator or directly to explosive bolts. The initiator ignites an energetic material to separate the fin from the projectile in-flight at a predetermined time. Alternatively, the explosive bolts separate the fin from the projectile in-flight at a predetermined time. In the embodiments using an initiator and energetic material, an opening or cavity in the rear portion of the projectile body or rod adapter acts as a pressure chamber. When enough pressure has built up from the burning of the energetic material, the front hub of the fin section expands enough to disengage the threads and separates the fin section from the projectile body.

Abstract: The product includes a self-propelled aerial pyrotechnic device and an upright launch tube for the device. The device is closely confined within the launch tube so as to be maintained in an essentially truly vertical orientation in preparation for launch. The device itself comprises a body containing pyrotechnic display material and an engine that serves to propel the body when ignited. A stabilizing base, preferably integrally molded from synthetic resinous material, is attached to the lower end of the body and is in the nature of a framework having a plurality of symmetrically disposed, long legs interconnected at various locations by strut structure. The engine is received within a socket at the upper end of the stabilizing base and is adhered to interior surfaces of the legs to provide a secure connection between the body and the base.

Abstract: The invention refers to a headbox device for feeding a pulp suspension to a dewatering installation, particularly for a tissue machine. It is mainly characterized by an eccentric shaft being provided to set the slice gap between a minimum and a maximum height. It also includes a wedge shaped steel lamella tip attached under pre-stress by a tie/rod to a headbox partition.

Abstract: A training rocket for smoke development. The training rocket includes a rocket tube which contains powder and constitutes a propulsion motor for the rocket. The rocket includes a forward training head which contains a smoke composition adapted to emit visible smoke upon impact. An igniter charge, such as a tracer charge, which can be ignited by the propellant powder is situated in the rearmost of the training head, behind a bursting charge which can be ignited by the igniter charge. The igniter charge and the bursting charge are situated behind the smoke composition in the training head, for igniting the smoke composition, in a capsule which can be forced rearwardly from the training head due to the increased pressure caused by combustion of the smoke composition, whereby an aperture is formed for passage of smoke gases rearwardly in the rocket, through the rocket tube and out of it.

Abstract: A skyrocket is provided which provides a first fireworks effect prior to launch as well as a second effect after launching. The skyrocket includes a body which houses or is coupled to a rocket motor, a first effect and a second effect. A transparent or translucent nose cone is placed on the top end of the body which provides both the ability to view one of the effects placed therein but also maintains the aerodynamic properties of the skyrocket. The first effect may be a strobing effecting which during burning provides a pulsating intensity of light visible through the nose cone prior to lift-off of the skyrocket, and the second effect may be a bursting charge which explodes after the rocket is in flight. An ignition fuse leads to the first effect and a second fuse leads to the rocket motor so that by lighting the first fuse, no further fuses need be lit and a delay is provided before the rocket motor ignites.

Abstract: A device for retaining an element ejected by a pyrotechnic device when it is fired comprises at least one metal cap placed behind the nozzle of the device and designed to receive the ejected element, the cap being held in position by curved rigid links. The kinetic energy of the captured element carries along the cap and the captured element and the motion of the assembly is braked by the deformation of the rigid links. Application especially to the retaining of the rear igniter of a missile.

Abstract: A retainer for model rocket motors having a flange (10) with a concavity (18). Several supports (12) extend perpendicular from the flange (10) and extend to the rocket frame (20). Mounts (14), parallel to the flange (10), abut each of the supports (12). Each mount (14) contains a longitudinal through-hole (16) as a means for attachment to the rocket frame (20).

Abstract: A toy gas-fired missile and launcher assembly whose missile is composed of a soft head and a tail extending therefrom formed by a piston. The piston is telescoped into the barrel of a launcher having a closed end on which is mounted an electrically-activated ignitor, the air space between the end of the piston and the closed end of the barrel defining a combustion chamber. Joined to the barrel and communicating with the chamber therein is a gas intake tube having a normally-closed inlet valve. To operate the assembly, the operator places the inlet tube with its valve open adjacent his anal region from which a colonic gas is discharged. The piston is then withdrawn to a degree producing a negative pressure to inhale the gas into the combustion chamber to intermix with the air therein to create a combustible mixture. The ignitor is then activated to explode the mixture in the chamber and fire the missile into space.

Abstract: A propellant composition comprising an admixture of a first hydrogen rich material and a second metal material which is capable of reacting exothermically with the first material. The ratio of the first material to the second material is selected such that the exothermic reaction forms a solid phase and a gas phase which contains substantial amounts of hydrogen. Preferably, the first hydrogen rich material comprises a material capable of providing nitrogen upon decomposition thereof, and the second metal material comprises a material capable of reacting exothermically with the nitrogen generated by the decomposition of the first material such that the solid phase comprises a solid nitride of the second metal material.In a preferred embodiment, the first material comprises ammonium azide, and the second material comprises boron, titanium, titanium hydride, or mixture thereof.

Abstract: A novel dosimeter capsule for indicating the condition of the solid propellant contained within a rocket motor to provide a measure of the remaining service life of the motor is described, which comprises a sealed expandable container and a portion of the solid propellant sealed therein and sized to fill the available volume within the container, the propellant portion containing a smaller concentration of chemical stabilizer than that which characterizes the solid propellant contained in the rocket motor, so that the propellant portion will deteriorate at a predictably faster rate than the rocket motor propellant, resulting in an increase of pressure within the expandable container of evolved gaseous products of the decomposition of the propellant portion and an accompanying bulge or protrusion of the container from its receptacle on the rocket motor casing corresponding to the increased internal pressure.

Abstract: An improved high energy impulse rocket includes a motor case containing propellant composed of individual, free flowing granules of a predetermined shape and unbonded to said motor case. The propellant has a high burning rate of 100 milliseconds or less and generates chamber pressures of up to about 50,000 psi. The rocket motor includes a reentry nozzle open at one end and connected to an exit nozzle, the reentry nozzle forming an annulus to contain the propellant and also forming a barrier to prevent ejection of the propellant during burning. Acceleration of the rocket assists in maintaining the propellant within the motor case, which acceleration may be as high as 20,000 g generating a velocity as high as 10,000 fps. Such a rocket offers unique advantages, especially as a device to punch an opening in a wall structure, the details of which are described as well as other details of the improved and relatively inexpensive impulse rocket.

Abstract: A multifunctional case that is suitable for storing, carrying or launching marker beacon. The launching could be in a dense jungle to place the marker beacon atop tree branches to make it visible from the air, or the case may be adapted for a launching at sea. The case has a triggering mechanism for launching the marker beacon. It has alignment means that comprises a first alignment position for inhibiting a launch when storing or carrying the marker beacon within the case. The alignment means has a second position for placing the marker beacon in position to be launched. The launching takes place upon activation of a triggering mechanism that forms part of the case.

Abstract: Rocket motors are constructed by encasing a solid porous poly(vinyl alcohol) core in the shape of the propellant grain with motor casing material in the same manner as motor casing material is conventionally applied over a disposable or removable mandrel. The motor is then completed by filling the open passages of the core with liquid oxidizer. When the liquid oxidizer permeates the poly(vinyl alcohol), the result is a solid continuous propellant grain of rubbery consistency. Aluminum powder may be incorporated in either the porous poly(vinyl alcohol) or the liquid oxidizer to achieve a fuel-enhanced propellant.

Abstract: A rocket glider stabilization system wherein a releasable, granular, counterweight, or ballast material is provided in the forward end of a model rocket aircraft to offset the weight of a tail mounted rocket motor assembly. The counterweight ballast material is releasably maintained in a counterweight bay formed at the opposite end of the model glider fuselage from the rocket motor. A rocket body tube connects the rocket motor with the counterweight bay and, when the ejection charge of the rocket motor is ignited, the ejection charge pressure ruptures or opens a retaining structure to release the ballast and maintain the desired center of gravity for glide flight of the rocket back to the ground. At least one adjustable or fixed trim tab is employed on at least one of the flight surfaces to induce the desired glide path return for the model aircraft.

Abstract: In detonator ignition circuitry, reliability is enhanced by significantly creasing the ignition energy voltage. Application of the high voltage ignition energy to the detonator is accomplished through a breakdown device which passes the ignition energy to the detonator only when the voltage thereof reaches its conductive threshold. To avoid the complications of high voltage design in the preferred embodiments, the ignition energy is stored at less than that threshold voltage and is boosted thereto when detonator ignition is desired.

Abstract: Composite polar bosses applied in rocket motor cases have very desirable characteristics. The lead time for a boss can be reduced from 6-12 months to 2-3 months. Weight savings for the boss are about 20-40%. A composite polar boss which attaches closures to solid fueled rocket motor cases is disclosed. This polar boss is a carbonized fabrication which sits within a circumferential indentation within the motor case, and has a threaded inner circumference which permits the closure to be attached thereto. The materials of the boss are selected to permit a service temperature of 350 degrees F.

Abstract: A holder for fireworks comprising a pair of rigid uprights of sheet material and a number of rigid plates or shelves of sheet material extending between the uprights. Slots in the respective components provide for assembly into a self-supporting fireworks holder by the relative telescoping of the uprights through the slots. Legs of sheet construction are also telescoped through slots in the upright and interlock with slits in the baseplate to rigidify the structure. Holes in some of the plates hold the fireworks in position for firing. The baseplate is substantially free of holes to serve as a shield to prevent inadvertent ignition of materials proximal to the holder.

Abstract: The acceleration applied to an ejection seat during the catapult phase of emergency escape from an aircraft is limited to a maximum value which can be tolerated by the ejectee by incrementally venting exhaust gas from the high pressure chamber of the ejection catapult. Such venting may be accomplished mechanically by a mass which acts in response to acceleration to open venting orifices, the mass being preloaded to prevent its movement until a desired acceleration is experienced. Alternatively, venting may be accomplished electromechanically.

Abstract: Improved method of manufacturing composite rocket motor cases and laminated tructures is disclosed which includes a layered procedure wherein a high percentage of a highly flexibilized, low-modulus epoxy blend of a resin composition is employed in the matrix of the innermost layer section with a subsequent, gradual addition of a toughened (or hard) high-modulus resin to the filament impregnating bath during the filament winding process to achieve a higher-modulus resin composition in the intervening layers with the highest modulus resin composition being in the outermost layer section to achieve a gradation in mechanical properties to mechanical behavior.