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: An aerodynamically stable, kinematic flare having an enhanced plume signature is disclosed. The flare includes a housing with a flare illuminant disposed within the housing. A primary nozzle is configured in the aft wall of the housing. Four secondary nozzles are configured in the aft end of the side wall of the housing and are positioned aft of the center of gravity of the flare. At least two of the secondary nozzles comprise off-center nozzles having a longitudinal axis which does not extend through the longitudinal axis of the flare. A shroud is attached to the housing and deploys to an extended position upon combustion of the illuminant. The shroud is configured with holes which correspond in size and position to each of the secondary nozzles when the shroud is in its extended position. The primary and secondary nozzles are sized and positioned to spin stabilize the flare during combustion of the illuminant.

Abstract: An aerodynamically stable, kinematic flare having an enhanced plume signature is disclosed. The flare includes a housing with a flare illuminant disposed within the housing. A primary nozzle is configured in the aft wall of the housing. Four secondary nozzles are configured in the aft end of the side wall of the housing and are positioned aft of the center of gravity of the flare. At least two of the secondary nozzles comprise off-center nozzles having a longitudinal axis which does not extend through the longitudinal axis of the flare. A shroud is attached to the housing and deploys to an extended position upon combustion of the illuminant. The shroud is configured with holes which correspond in size and position to each of the secondary nozzles when the shroud is in its extended position. The primary and secondary nozzles are sized and positioned to spin stabilize the flare during combustion of the illuminant.

Abstract: Improvements applied to the case of a smoke bomb.This invention relates to the envelope of a smoke bomb case.It consists, on the one hand, of a traditional wall (1), resistant to the pressure of the smoke bomb constituents (4) when it is the object of the exothermic reaction of the smoke bomb powder, once it has been initiated by an adequate technique. It comprises, on the other hand, at least one area of reduced resistance (3), formed by a relatively fine layer, the said area being covered by a cover (2) of a resistance comparable to the remainder of the traditional wall (1), and which is pierced by a large number of holes (6, 7, and 8).It is characterized by the fact that each hole (6 or 7 or 8) of said cover (2) has a warped form.

Abstract: An infrared decoy flare having enhanced infrared intensity is disclosed. The flare includes a case in which an infrared illuminant composition is disposed. The bore diameter and length of the case are advantageously selected to be compatible with preexisting chaff dispensers and their cartridges located on aircraft. The illuminant composition, the nozzle throat area, the geometry of the illuminant composition, and the volume of the combustion chamber are selected such that combustion of the illuminant composition results in an unstable combustion condition during the first second of combustion, thereby increasing the peak intensity of the radiation emitted by the propellant. Preferably, the flare is configured such that the unstable combustion occurs during the first 0.2 to 0.5 seconds of combustion of the illuminant composition.

Abstract: A munition release system for carrier weapons is disclosed. Mechanisms for disengaging and ejecting munitions from the carrier housing operate in response to a common gas generator. Disengagement from the housing is effected just prior to ejection. Use of a common gas source improves reliability, while coordinated disengagement and ejection minimizes forces exerted on the munitions.

Abstract: A bi-propellant self-contained propulsion system is provided for powering rockets. A plurality of turbopump assemblies are provided to take liquid propellants from low pressure storage tanks to a substantially higher pressure thrust chamber. Substantially all of the liquid propellants are pressurized and gasified within the plurality of turbopumps. Substantially all of the gasified propellants are then used to drive the turbopumps that pressurize the liquid propellants. Gasification preferably occurs within a preburner internal to the turbopump assembly that combines a small portion of one of the propellants with a substantial portion of the other. The proportions are selected so that gasification of all of the propellants is ensured yet relatively low preburner temperatures are maintained. A multi-stage pintle assembly may be provided to vary the exit-to-throat area ratio of the nozzle. The total thrust and the mixture ratio may be controlled by shutting down some of the turbopumps.

Abstract: An improved smoke canister 1 has a high-pressure proof propellant chamber 20 containing a propellant charge 21, consisting of a reduced-smoke generating powder, which can be ignited electrically by an ignition charge 19. Capillary bores 20b and 20c are provided respectively in both end faces of the propellant chamber 20. When a smoke canister 1 is fired, propellant gases under high pressure exit via the capillary bore 20b into the launcher (not shown), and contribute to the uniform acceleration of the smoke canister 1. This makes it possible to launch heavier smoke canisters. The smoke-generating charge 12 is ignited by means of the second capillary bore 20c.

Abstract: An ordnance system which includes a warhead accommodating a number of secondary elements, especially explosive elements as a payload, with the secondary elements adapted to be distributed over a target area. The warhead includes a coaxially arranged rotation-producing propulsion unit such as a rocket engine.