Abstract: An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions charge. In a preferred embodiment, the rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions charge. In a preferred embodiment, the rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions charge. In a preferred embodiment, the rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: An embodiment of the rocket motor of this invention employs an insensitive munitions approach that, when subjected to elevated external temperatures, is activated by thermal expansion of the main propellant and gas generation from a secondary insensitive munitions charge. In a preferred embodiment, the rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: One embodiment of this novel rocket system employs at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at lunch. Another embodiment of this novel rocket involves an insensitive munitions approach that does not require use of such retainers by developing different normal and abnormal burn paths. The rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well varying gas pressure inherent in gun-launched systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: A rocket system employing at least one rocket motor closure that includes low and high load capability retainers that, respectively, provide an insensitive munitions system during storage and positive locking of a nozzle assembly at launch. The rocket motor also includes a pressure equalizing system that accommodates changing temperature conditions during storage as well as varying gas pressure inherent in gun-launched rocket systems in a manner that allows for thinner case cylinder design and increased propellant volume.

Abstract: A missile diverter for controlling yaw and pitch includes several valve housings secured to an inside surface of a bridge or to a removable cylinder. The valve housings are secured in aligned positions by a layer of integral cured insulation. Gas valves are placed in the housings, and control lines are connected to the valves to allow remote control of the valves during flight. Cups loaded with propellant are secured in place near the valve housings. The valve housings, valves, cured insulation, and propellant cups are then overwrapped and secured within the outer shell of a missile. One method for making the missile diverter includes the step of applying a quantity of uncured insulation to an inside surface of a bridge and to an outside surface of each valve housing. Each valve housing is then positioned within the bridge and the insulation is cured to form an integral layer that holds the valve housings in their aligned positions and forms a hot gas seal.

Abstract: A propellant system is disclosed which includes a propellant applied to at least one surface of a substrate which is in the form of a strip. The propellant strip is adhesively attached to itself in a configuration which conceals propellant within the configuration and which allows the attached strip to peel away from itself under applied forces thereby resulting in smooth and continuous exposure of propellant for burning. The system is directed to use with ejectable projectiles which are slidably disposed within a canister or casing. The propellant system is interconnected between the projectile and the cannister which houses the projectile. The propellant is urged to peel, and thus expose propellant for burning, as the projectile is ejected from the canister. Alternatively, the propellant is telescoped and covered with a sleeve which peels away as the projectile is ejected.

Abstract: A propellant system is disclosed which includes a propellant applied to at least one surface of a substrate which is in the form of a strip. The propellant strip is adhesively attached to itself in a configuration which conceals propellant within the configuration and which allows the attached strip to peel away from itself under applied forces thereby resulting in smooth and continuous exposure of propellant for burning. The system is directed to use with ejectable projectiles which are slidably disposed within a canister or casing. The propellant system is interconnected between the projectile and the canister which houses the projectile. The propellant is urged to peel, and thus expose propellant for burning, as the projectile is ejected from the canister.

Abstract: An archery target is disclosed that is formed from multiple front layers formed from a woven material having laterally displaceable strands to permit penetration of an arrowhead, multiple backing layers formed from material which resists penetration of an arrowhead and a plurality of aligned pockets formed between the front and backing layers. Stuffing material such as raw cotton is compressibly forced into each of the pockets resists lateral displacement of the stuffing material upon penetration of an arrowhead and causes the stuffing material to be compressed in front of the arrowhead to effectively stop the arrow.

Abstract: The functions of a diverter valve and a variable orifice valve are combined in a single valve including an elongated magnetic member that is pivoted at a first end with a portion of the second end being positioned between opposed restrictors, a coil assembly for producing a magnetic field for selectively pulling the magnetic member toward one of the restrictors, sealing the restrictor it is pulled against thereby enabling the diversion of fluid flow, for example, from one nozzle to another, and further including a ball screw and torque motor attached to the first end of the magnetic member for selective movement thereof fore and aft, with the second end of the magnetic member being tapered and positioned in cooperative relation with respect to an orifice in a fluid inlet member whereby the fore and aft movement of the magnetic member controls the size of the orifice and the amount of fluid flow.

Abstract: A solid propellant grain for a gas generator such as a missile canister erection actuator. The grain provides a sustain phase followed by a boost phase which may then be followed by another sustain phase. The aft portion of the grain may have the configuration of an end burner to provide the initial sustain phase. The middle portion contains a longitudinally extending cavity in which is disposed a plug for supporting the grain during the initial sustain phase against collapse or cracking. A gap is provided between the plug and the wall of the cavity to provide effective propellant burnign surface area along the cavity wall for the boost phase. The cavity and plug, which terminate at the aft portion, may extend longitudinally through the forward portion of the grain.