Abstract: A fireworks aerial display shell is provided with lift charges positioned at opposite ends of a casing that additionally contains an effects charge. Fuses are operatively associated with the lift charges and the effects charge in a manner to ignite the lift charges a period of time before igniting the effects charge. When either one of the ends of the casing is placed facing a closed bottom of a launch tube of a reusable mortar, the burning lift charge at that end of the casing when ignited exerts a propelling force to propel the aerial display shell upwardly out of the launch tube to an intended height before the effects charge is ignited to create a pyrotechnic visual effects display.

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: The present invention discloses a low foreign object damage nose weight for affixing to a either a standard or kinematic decoy flare comprising a thin walled nose cup having a closed end, an open end, an internal cavity, and at least one sidewall attached to said closed end and surrounding said internal cavity; and a metal powder disposed within the internal cavity for weighing down the forward end of the decoy flare, said nose cup capable of being affixed to a forward end of a decoy flare such that said powder is jettisoned from said nose cup upon burn out of a flare pellet subassembly of said decoy flare thereby reducing the weight of the nose cup and the possibility of foreign object damage to aircraft, ground troops, ground equipment and buildings resulting from the falling nose weight.

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: The present invention discloses a low foreign object damage nose weight for affixing to a either a standard or kinematic decoy flare comprising a thin walled nose cup having a closed end, an open end, an internal cavity, and at least one sidewall attached to said closed end and surrounding said internal cavity; and a metal powder disposed within the internal cavity for weighing down the forward end of the decoy flare, said nose cup capable of being affixed to a forward end of a decoy flare such that said powder is jettisoned from said nose cup upon burn out of a flare pellet subassembly of said decoy flare thereby reducing the weight of the nose cup and the possibility of foreign object damage to aircraft, ground troops, ground equipment and buildings resulting from the falling nose weight.

Abstract: A projectile sealing arrangement for a barrel assembly of a weapon wherein a plurality of projectile assemblies (10) are axially disposed in abutting relationship within a barrel (20), each projectile assembly (10) including a body (11) associated with a discrete propellant charge (15); said sealing arrangement comprising rearward opening (13) communicating with cavity (14) provided in said projectile assembly (10) for retaining the discrete propellant charge (15) and a forward portion (16) of an abutting projectile arranged for operative sealing engagement with a complementary portion (17) of the rearward opening (13). The sealing arrangement suitably includes surface portions of complementary shapes such that, during application of a compressive load (L) to abutting projectile assemblies (10), discrete propellant charge (15) is scaled within the cavity (14). There is also disclosed and claimed a chain of individual projectiles connected head to tail by complementary spigot and socket members.

Abstract: A multiple stage pyrotechnic shell apparatus is disclosed. The invention has enhanced efficiency to increase lift and reduce the risk of one or more of the charges from exploding near the ground. The enhanced efficiency is obtained through the novel use of shaped breaks that conform to the shape of the inner surface of the shell's launch tube, and in particular through the use of cylindrically shaped breaks in round launch tubes. In addition, the present invention further enhances efficiency by configuring the breaks such that all the breaks weigh the same or the upper breaks weigh more than the lower breaks in the launch tube.

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: Pyrotechnic fireworks launch apparatus is provided. The apparatus includes a base to which is affixed a male-configured launching cylinder adapted to accept thereover, in combination, an internally cylindrical, female-configured projectile, wherein the projectile has a proximal and a distal end thereof. The projectile houses a fused pyrotechnic display charge proximate its distal end and also houses a fused launching charge encased therein and partitioned from the display charge. On insertion of the launching cylinder into the proximal end of the projectile, thereby mounting the projectile upon the launching cylinder, the encased launching charge and the launching cylinder are in abutting relationship. Upon ignition of the fused launch charge, the projectile is launched vertically from the launching cylinder. The external configuration of the projectile may have any number of shapes. In a preferred configuration, it is shaped as a rocket.

Abstract: A high-performance propulsion system includes propellant charge powder arranged in a case (1) and multiple pyrotechnic igniters (9) for igniting the propellant charge powder, each igniter (9) containing a primer (5) and optionally a booster charge (6).

Abstract: A multiple effect pyrotechnic shell (20), having a lift chamber (22), primary break (24), secondary break (26), and a tertiary break (28) has a desired weight distribution to inhibit tumbling. The secondary break weight is less than the primary break weight, and the tertiary break weight is less than both the primary and secondary break weights. Thus, the center of gravity of the shell (20) is positioned below a midpoint of the shell height. A first timing fuse (46) extends from a lift charge (30) into a primary break charge (50A) of the primary break (24), and a primary internal timing fuse (64) extends from the primary break (24) to the secondary break (26). Further, a secondary internal timing fuse (70) extends from the secondary break (26) to the tertiary break (28). Fuse fragments (52) are preferably disbursed within the break hulls (48) to provide filler and add an additional effect to each break (24-28).

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 rocket according to the invention includes a motor having a fuel chamber and an oxidizer tank, a nose portion provided forward of the motor, and a nozzle surrounded by fins provided aft of the motor. The fuel chamber is provided with a relatively central solid propellant, and a hybrid fuel surrounds the solid propellant. The oxidizer tank is filled with a reactant and coupled to the forward end of the fuel chamber. A pathway is provided between the tank and the fuel chamber for the passage of reactant therethrough. At least one of a valve and a barrier is coupled in the pathway to prevent passage of the reactant into the fuel chamber until after the solid propellant is at least partially consumed. After the solid propellant is at least partially consumed, the valve is opened and/or the barrier is removed to permit the passage of reactant into the fuel chamber.

Abstract: An air-delivered infrared anti-ship missile decoy is delivered from an aiaft to a desired location below sea surface ahead of advancing forces and then activated at a later time by a remotely-transmitted encoded signal to separate a payload assembly from the remainder of the decoy, float the payload assembly on the sea surface and then produce a relatively large infrared plume above the payload assembly and atop the sea surface that provides an infrared signature for decoying and deception purposes.

Abstract: A pyrotechnic device includes a launcher for launching and igniting a plurality of pyrotechnic stars for creating an aerial fireworks display. The launcher comprises a launching tube having an igniter that ignites the pyrotechnic stars as they are being expelled from the launching tube under the force of pressurized air. The igniter may comprise a section of the launching tube having a locally reduced diameter so that the pyrotechnic star frictionally engages it during launch, causing a striker composition on the interior of the launching tube to ignite a prime composition on the exterior surface of the pyrotechnic star. Alternatively, the igniter may comprise a flame within the launching tube to ignite the prime composition on the star. Various feeding mechanisms are provided to rapidly feed a large number of pyrotechnic stars for launching from the launching tube. The launcher utilizes pressurized air to launch the pyrotechnic stars and, thus, minimizes adverse environmental impact.

Abstract: A remotely-actuated fireworks launcher apparatus includes a housing assembly, a signal receiver housed within the housing assembly, an ignition servo electrically connected to the signal receiver and housed with the housing assembly, and a servo-actuated ignition switch operated by the ignition servo. The servo-actuated ignition switch is in an ignition circuit which also includes an electric igniter assembly, and a power supply. A fireworks receiver assembly is attached to the electric igniter assembly. The fireworks receiver assembly receives a fireworks device that is ignited by the electric igniter assembly. A manually operated ignition signal transmitter is actuated to transmit signals for activation of the signal receiver. The servo-actuated ignition switch includes a first switching element operated by the ignition servo and a second switching element selectively connected to or disconnected from the first switching element.

Abstract: A follow-through grenade is provided which utilizes a primary fuze to trir both the main warhead and a delayed secondary fuze system. The main warhead explosion is used to breach barriers behind which enemy personnel are located. When the primary explosion occurs, the primary fuze simultaneously activates a delay timer and slide detonator. The slide detonator provides a means to keep the secondary explosive in a safe mode until the explosion of the primary warhead. The delay timer triggers the follow-through explosion after the primary explosion has breached the barrier. This behavior allows the follow-through device to penetrate the barrier and explode on the far side of the barrier for maximum effectiveness against personnel located behind the barrier. The present invention uses a standard dual mode fuze as its activator and is based on the McDonnell Douglas Shoulder-launched Multipurpose Assault Weapon (SMAW).

Abstract: A pyrotechnic device for launching at least one projectile includes, in a longitudinal launcher tube closed at the rear by a rear wall, a closure member expelled when subjected to a longitudinal force exceeding a predetermined threshold and retaining at least one projectile on opposite sides of which are a front chamber and a rear chamber in which an impulse cartridge builds up a gas pressure simultaneously. In this way a plurality of projectiles can be fired sequentially by means of a single impulse cartridge.

Abstract: The member bearing electromagnetic decoys comprises a sliding member (23 to 27) having an open major face closed by a cover of which an extension projects opposite an opening (21A) in a compartment (21) provided for a pyrotechnic portion. When the pyrotechnic charge there disposed has caused ejection of the decoy-bearing sliding member, and after a given delay, it will act on the extension of the cover in order to remove the latter and thereby release it from the electromagnetic decoys. This ensures that the decoys are deployed at the end of a given delay after ejection of the decoy-bearing member from the 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: A propellant igniter that is controlled by temperature and is activated by cceleration. The igniter includes a booster or primer for igniting a propellant charge. A spring-loaded firing pin is cocked by a rotating sear that, when released, energizes the booster. Rotation of the sear is controlled by a plurality of springs one of which produces a moment on the sear that is a function of temperature while others, a plurality of captive springs, produce restoring forces that are inversely proportional to acceleration as detected by an acceleration sensor. When the captive springs are sufficiently relaxed by the acceleration sensor, due to an increased acceleration, to allow the sear to rotate, the cocked firing pin is released, the booster is activated and ignition occurs.

Abstract: A rocket system wherein a frustoconical or cylindrical casing contains fi and second rocket stages in series, with each stage having a nozzle extending in an aft direction. Each stage contains a solid rocket fuel, with the forward end of the fuel in the first stage filling and surrounding the nozzle of the second stage so that when the casing is severed along a plane aft of the second stage portion of the case the pressurized combustion products in the first stage forces the stages to separate.

Abstract: A pyrotechnic assembly has an outer container for a plurality of pyrotechnic elements, each of which has a propellant charge, to propel the element out of the container, and a pyrotechnic charge, for example for producing a radiation-blocking screen. The container may be used as a fixed launcher for the elements or may itself be a projectile or missile from which the elements are ejected in flight. A plurality of different pyrotechnic charges may be included in the element.

Abstract: The controlled explosion projectile ejection system utilizes a source of combustible gas through a controllable input valve into a combustion chamber. Inside the combustion chamber is a sparking means. After the chamber is loaded or filled with gas, a spark control signal is applied to the sparking means and the gas ignites. At the output of the chamber is disposed a controllable output valve. In a simple embodiment, the output valve is simply a valve head biased against the output port of the chamber thereby inhibiting any gas flow from the chamber unless the pressure in the chamber exceeds the biasing force against the valve head. After ignition, the gas expands and the resulting pressure is much greater than the biasing force on the output valve head and the valve opens. Downstream of the output valve is a barrel with the projectile loaded therein. The expanding gas passes through the output valve and ejects the projectile from the barrel.

Abstract: A gas generator is provided for ejecting projectiles from a container under utilization of a developing gas pressure in an expansion chamber, using alternating propellant explosive charges hoses and ignition charge hoses in a string. String branching can be provided for.

Abstract: A practice rocket for antitank weapons comprising a head and a support rod fastened to the head, the support rod carrying a tracer charge at its rearward end, and a propulsive charge in the form of gunpowder rods distributed around the support rod. The gunpowder rods are fastened to the head or to a disc attached to the head, and the support rod and the gunpowder rods are surrounded by a sleeve having a cylindrical portion and a narrow portion constituting a nozzle. The tracer charge is situated in front of the nozzle, and is ignited simultaneously with the firing of the rocket.

Abstract: An improved rifle-actuated rocket weapon system and an improved method for iming the system in relation to a short range target by firing one or more tracer bullets until it is aimed at the target for launching the rocket weapon. The system is generally made up of a spotting rifle and a rocket weapon launch tube subassembly. The rifle is provided with a magazine for carrying one or more tracer bullets. Fluid passageway means are provided in the launch tube subassembly, rocket weapon fuse device, and rifle. Interconnection of the passageway means with the bullet accelerating and guiding passageway of the rifle is effected by a manually operated normally closed valve. The valve is disposed in the rifle and is operatively associated with the passageway means.

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

Abstract: A tandem rocket launcher is provided by mounting plural rockets in an elongated launch tube with associated guide and launch equipment for each rocket. A conical shield is placed between the rockets which deflects exhaust gases generated by firing the forward rocket away from the rearward rocket. The shield is then removed by firing of the subsequent rocket or pivoting of two halves of the deflector away from the path of travel of the subsequent rocket.

Abstract: A two stage parachute recovery system for use in recovering fuzes or other ensitive equipment from a projectile that has been launched from a gun barrel wherein explosive means are successively detonated by a timing mechanism and by centrifugal force imparted to the projectile respectively so as to deploy each of the said parachutes and to thereby recover the fuze before impact.

Abstract: A device for simulating hits on a target for example in war games and particularly for simulating hits on armored vehicles comprises a housing which has a plurality of separate spaced apart charge receiving chambers therein. Each chamber contains a distinct charge preferably including but not limited to a so-called fireball type of charge, a smoke type charge and a report type charge. The charges are arranged in separate cups or compartments and the first charge is connected to an igniter which may for example be an ignition system which is set off by an external pulse of light. The other charges are connected to the first charge and to each other through pyrotechnical propagation charges which may or may not have a delay operation so that they are set off in a controlled sequence.

Abstract: A system for safely simulating artillery delivered flare illumination over roops engaged in nighttime tactical training exercises, utilizes a lifting device for carrying a tethered electrically initiated, gravity released flare dispenser system to provide illumination over a target area while substantially reducing the hazard to personnel of flare debris fallout and malfunction danger to the lifting device. A tubularly shaped flare dispenser housing member supports a plurality of reloadable cylindrically shaped parachute flare assemblies. An electrically operated parachute flare initiator is utilized to simultaneously ignite and drop-release one or more combustible case flares by severing a burn-through cord retaining member.

Abstract: A multiple effect pyrotechnic shell (20), having a lift chamber (22), primary break (24), secondary break (26), and a tertiary break (28) has a desired weight distribution to inhibit tumbling. The secondary break weight is less than the primary break weight, and the tertiary break weight is less than both the primary and secondary break weights. Thus, the center of gravity of the shell (20) is positioned below a midpoint of the shell height. A first timing fuse (46) extends from a lift charge (30) into a primary break charge (50A) of the primary break (24), and a primary internal timing fuse (64) extends from the primary break (24) to the secondary break (26). Further, a secondary internal timing fuse (70) extends from the secondary break (26) to the tertiary break (28). Fuse fragments (52) are preferably disbursed within the break hulls (48) to provide filler and add an additional effect to each break (24-28).