Abstract: An aerial shell comprising at least one combustible layer of combustible material, the at least one combustible layer including an outermost combustible layer surrounding the at least one combustible layer, the outermost combustible layer configured to ignite on substantially an entire outer surface, the outermost combustible layer including a relatively higher combustion rate than the at least one combustible layer; the at least one combustible layer including an innermost combustible layer surrounding and containing at least one pyrotechnic effect and a dispersive explosive charge; the at least one pyrotechnic effect is preferentially disposed with respect to the innermost combustible layer at least one of immediately adjacent including integral with an inner surface of the innermost combustible layer and spaced away from the inner surface of the innermost combustible layer; the at least one combustible layer configured to burn substantially throughout the at least one combustible layer.

Abstract: A non-pyrotechnic flare system and method includes at least one flare member that is configured to be deployed. The flare member(s) includes a head having a light-emitting diode (LED) that is configured to emit light when activated, and a wing-shaped appendage extending from the head. In at least one embodiment, a casing retains the flare member(s) in a stowed position. The flare member(s) is configured to be deployed from the casing.

Abstract: A dividable parachute grenade is provided including a grenade casing, a nose cone, a detonating fuse, a dividing charge, a payload, a parachute device, a grenade bottom, and a supporting device, wherein the supporting device is annular and includes pretensioned sector elements fixed to a fixing ring in the recess on the inner side of the grenade casing, the sector elements are pretensioned with a tension ring arranged around the annular supporting device via recessed grooves in the sector elements, whereof the supporting device is arranged extensibly in the radial direction in a recess on the inner side of the grenade casing behind the payload and supports the payload in the extended position during the acceleration phase of the grenade, and stays in the grenade after the separation of the payload from the grenade.

Abstract: A trip flare with flash bang has a body having a sidewall and a hollow interior, a lid releasably attached to the body, the lid including a fuse, the interior of the body containing an illuminant composition in communication with the fuse, and a flash bang charge composition in communication with the fuse and attached to the lid by an elongated flexible tether. The tether may be a coil when received within the interior of the body. There may be an ignition composition proximate the illuminant composition such that combustion of the ignition composition ignites the illuminant composition. The flash bang charge composition may have a pyrotechnic fuse proximate the ignition composition such that combustion of the ignition composition ignites the pyrotechnic fuse. There may be a first fire composition proximate the ignition composition such that combustion of the first fire composition ignites the ignition composition.

Abstract: An indirect fire munition non-lethal cargo carrier mortar deploys non-lethal sub-munitions to an intended target. The cargo carrier mortar includes a deceleration system which allows for the discarded mortar to descend at a controlled non-free fall velocity thereby minimizing the risk of injury or collateral damage from the mortar. The cargo carrier mortar is adapted to be compatible with existing standard military equipment such as standard mortar caliber sizes.

Abstract: In one aspect, the present disclosure relates to protective canisters for incendiary devices, said canisters comprising a sidewall and two endcaps, said endcaps attached to said sidewall so as to form a substantially enclosed canister; wherein one or both of said endcaps is removably attached to said sidewall; and wherein said sidewall comprises a plurality of transverse holes through it. Optionally, one or both of said endcaps comprise one or more transverse holes through them.

Abstract: The present invention relates to an improved apparatus for safely igniting a pyrotechnic device such as a flare which is suspended by a parachute following deployment from an air craft. More specifically, the present invention relates to a two stage ignition train mechanism for use with parachute suspended illumination flares with an in-line firing pin and physical safety mechanism which blocks movement of the firing pin until the parachute is deployed. The present invention also discloses an embodiment of a two stage ignition train mechanism for use with parachute suspended illumination flares with out-of-line firing pin and physical safety mechanism which blocks the firing pin from striking the primer until the parachute is deployed.

Abstract: A parachute flare igniter assembly includes a novel safety for arresting the motion of a slider when subjected to external forces, but allows slider motion when subjected to intended cable actuation forces. The igniter safety includes a housing, a slider, a cable and a sleeve. The slider, connected to the cable, is slidably received within the housing. The cable moves the slider by applying a cable force conventionally obtained by actuation of a parachute associated with the flare and connected to an end of the cable opposite an end connected to the slider. The sleeve is connected to the cable and is disposed between the housing and the slider, so that the sleeve will arrest the slider with respect to the housing when the cable force is not present. A flare and a method of providing a safety in an igniter assembly is also provided.

Abstract: This parachute flare igniter assembly has a novel slider for attaining high reliability in firing efficiency. The slider moves along a raceway of an igniter assembly housing. Also disposed in the housing is a cartridge retained in a stationary state relative to the housing. The cartridge includes a stationary primer and a spring. A striker arm connected to the cartridge is movable into a cocked state in which the spring urges the striker arm towards the primer. The slider has an igniter composition chamber and a cocking wall portion, and is movable in tandem with the igniter composition chamber along at least a portion of the length of said raceway from a loaded position to a firing position. In the loaded position, the striker arm is maintained in the cocked state by the cocking wall portion.

Abstract: An IR radiating decoy for an IR seeking anti-ship missile (ASM) includes a propulsion section, safe and arming section, gas generator section, fuel tank section, and flight stabilization section to ignite and continuously maintain an IR plume for decoying the ASM away from the targeted ship. The IR radiating decoy ignites the IR plume immediately when the decoy reaches a safe separation distance from the targeted ship. The IR plume continues to be emitted as the decoy flies away, as it lands on the water, and while it floats upon the water until all the fuel is used from the fuel tank. The fuel can be changed to change the signature of the IR plume so that different ASM missiles can be drawn away from the ship.

Abstract: A delivery apparatus (11) for full-calibre submunitions or the like payloads (12) which are coaxially stacked in its load space (19) results in a system which operates in a fault-free manner when, for ejecting the payloads (12), detachment of the load space (19) from the rocket motor (17) disposed therebehind and detachment of the ogive (14) from the opposite end of the load space (19) are each promoted by a pyrotechnic charge (28, 31), with the load space (19) being braked as a result of being positioned transversely beside the trajectory (26) of the separated motor (17) which flies further along the trajectory and past the load space in a stable configuration and with the load space (19) only then being turned by a braking parachute (23) connected to its end (22). The load space tail (18) which thereafter then faces forwardly in the direction of flight is opened by detachment of a cover (25) and the load space (19) is pulled away from the payload stack (12--12) by means of the braking parachute (23).

Abstract: A covert, i.e., no visible light emitted, multispectral day/night target marker is disclosed. The marker emits a signature detectable in the electromagnetic spectrum including visible, near infrared, middle and longwave infrared, and radar regions. The marker is particularly useful for marking of target areas so that they can be easily detected from the ground or the air. The visible spectrum is marked by a white or colored pyrotechnic smoke generant. The near infrared region is marked by near infrared emitting photodiodes encased in a hardened polymeric molding compound. These diodes are only visible through night vision devices (image intensifiers). The middle through the far infrared regions are marked by the heat generated from the combustion of the pyrotechnic smoke generant. The smoke generant is housed in a canister having a highly emissive surface. The radar region is marked using radar chaff. The target marker is configured for use with conventional mortar or rocket delivered flare systems.

Abstract: A parachute deployment system for use with an illuminating flare warhead propelled by a rocket motor. The system employs a compact two-stage parachute system which includes a main parachute arranged within a main parachute cover and a drogue parachute arranged within a drogue chute cover. The main parachute pack and the drogue parachute are configured to be positioned in a side-by-side, detached relationship within the warhead. An extraction line separably connects the drogue parachute pack to the rocket motor and a support line connects the drogue parachute pack to the main parachute pack such that upon separation of the rocket motor from the warhead, the drogue parachute pack is extracted from the warhead prior to extraction of the main parachute pack. Upon deployment of the drogue parachute, the drogue parachute cover remains attached to the extraction line and acts as a deflector, inducing radial forces which act upon the rocket motor to prevent it from colliding into the warhead.

Abstract: Parachute ejection and recovery system for rockets which protects and permits recovery of the entire rocket after launch including means for cooling ejection gases, means for directing the cooler ejection gases for using in ejection, the nose cone and parachute therefrom during flight, and means for controlling descent of the rocket body, its nose cone and a parachute associated therewith.

Abstract: Illuminating flare has an igniter in which a two-part inertial mass is gud for relative aftward movement from a safe position to an armed position under launching forces. One part of the mass undergoes relative forward movement to an ignition position under parachute-opening, deceleration forces while the other part of the mass is restrained from moving as far forward as the first part. This separation of the parts of the mass releases locking balls to unlock a firing pin, which stabs a primer and initiates ignition of the flare. The primer is contained in a rotor, and as the mass traverses from the safe position to the armed position it rotates and the rotor rotates with the mass. In the safe position the primer is out of communication with an ignition passage through which ignition of the illuminant composition occurs. Rotation of the rotor as the mass traverses to the armed position places the primer in communication with the ignition passage where it remains until activated by the firing pin.

Abstract: A compact laser flare illuminator includes a semiconductor diode laser array radiation source, an energy source for the radiation source that can be switched on and a housing which holds the array and energy source, while allowing egress of a beam. This illuminator may be used to facilitate night vision by persons wearing night vision goggles or using other types of wavelength-selective night vision devices. The housing may serve as a heat sink and may be equipped with a propulsion device and with fins for flight stabilization, as well as with a parachute for slowing descent from an altitude above an area to be illuminated. A wavelength filter that passes radiation only in a predetermined wavelength range and a lens or optical element to focus the laser radiation toward the area to be illuminated are optional features.

Abstract: The present invention relates to a novel type of flare charge insulation for retally burning flare charges. The flare charge insulation according to the present invention is produced by compaction of a particulate material or granulate of a mean particle size which does not exceed 1 mm. The major component parts of the granulate are an organic metal salt, and minor amounts of a combustible binder. Moreover, particulate melamine may be included in an amount of up to 20 weight per cent.The present invention also includes a novel method of producing flare charges in which both the flare charge and flare charge insulation are terminally compacted together to form a continuous unit.Consequently, the present invention also relates to the finished flare charge manufactured according thereto.

Abstract: A pyrotechnic, aircraft carried bomb such as a smoke bomb, illumination b, flare bomb and the like. The bomb comprises detachable delay and nose sections and two main body sections separable from each other and each holding a pyrotechnic charge. The tail section houses a braking parachute which is deployed by the action of a time fuze upon release from the carrier aircraft. The tail and nose sections further house each a main parachute associated each with one of the main body sections. After a certain delay the deployed braking parachute starts an ignition train which causes ejection of the tail and front sections, deployment of the main parachutes, separation of the two main body sections from each other and ignition of the pyrotechnic charges therein. The two main body sections parachute down and reach the ground in soft landing with the pyrotechnic charges burning during the descent and, if desired, they may be arranged to continue to burn for a while after landing, e.g. in case of a smoke bomb.

Abstract: Within a cylindrical container or canister, closed at both ends by a respective cover member, there is located a flare or illuminating rocket. For firing the flare rocket it is sufficient to remove the rear cover and by pulling at a tear line there is activated a tear ignition device or fuze. The ignited flare rocket then pierces the front cover member. This front cover member preferably possesses a ring-shaped or annular reference fracture location which subdivides the cover member into a disk-shaped inner portion and a ring-shaped outer portion.