Abstract: A multiple-stage solid rocket motor is operated in a manner designed to control its mass discharge profile. This is accomplished by providing means for igniting one stage and then igniting a subsequent stage while the first continues to burn.

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: A decoy flare ignition system is disclosed which includes an ignition initiator disposed at the aft end of the flare housing. An illuminant igniter is positioned in direct contact with the flare illuminant. The illuminant igniter includes at least one illuminant igniter pellet selected such that the firing of the ignition initiator triggers combustion of the illuminant igniter pellet if the safe-and-initiation device has been actuated. The igniter pellet is preferably configured as a circular cylindrical shell and is positioned over the bore of the flare 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: 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.