Abstract: A high impulse, non-detonable solid propellant grain is prepared from a cd detonable proepllant composition having a small critical diameter of less than one inch and an uncured detonable propellant composition having a large critical diameter of several inches. The method of preparation comprises grinding or cutting the cured detonable propellant composition into granules less than its critical diameter in any direction. An uncured propellant composition, in a predetermined amount of les than its critical diameter, is prepared, and the granules of the cured propellant are added and blended with the uncured propellant composition (which serves as the propellant binder) to form a homogeneous propellant blend. The homogeneous propellant blend is cured to yield a high impulse, non-detonable solid propellant grain having a critical diameter less than the critical diameter of the uncured propellant composition.

Abstract: An explosive planar shock wave generator produces a planar wave that trav down a shape charge cone to give amplified force on the jet. In all embodiments radial waves are converted to planar waves which react with an explosive shape charge. A planar wave shaper is comprised of a conically shaped planar charge having a predetermined diameter at the base and slant heights terminating at an apex. A cylindrically shaped fast detonating charge which is positioned above the cone shaped planar charge is detonated by a detonator positioned on the surface of the cylindrically shaped fast detonating charge. A sloweer cone shaped detonating shape charge intersecting along the base of the conically shaped planar charge receive the planar shock wave as transformed by the conically shaped planar charge.

Abstract: A rocket motor that has a fast burning propellant therein with a dispenser rrangement for dispensing a fluid chemical suppressant into the exhaust gases of the solid propellant for reducing the flash signature.

Abstract: A method and design are disclosed for the introduction of ammonia gas into he rocket motor gas environment wherein the ammonia gas functions to suppress the flash signature.The firing and pressurization of a sealed container having suppressant vents results in the rupturing of one or more seals for the container containing clathrate means from which adsorbed liquid or gaseus ammonia is boiled out and discharged and mixed with combustion gases prior to being discharged through the exhaust nozzle of a rocket motor.The design for the container for containing clathrate means include as part of one embodiment a toroidal shaped container for installing within the rocket motor exhaust nozzle wherein the container functions as the throat of the exhaust nozzle of the rocket motor. Other embodiments feature the clathrate means in a sealed container which additionally houses the ignitor means.

Abstract: A device in which a solid suppressant is ablated and dispensed into the gs of a main burning rocket motor in which a fast burning smokeless type solid propellant is burning to allow the suppressant to control afterburning of the gases from the burning solid propellant and the suppressant being dispensed by a sustained action igniter pyrotechnic that is also used to ignite the main motor solid propellant.

Abstract: A solid propellant gas generator operating with a calibrated tunable resonator produces a strong sonic field capable of affecting particle coagulation in an aerosol. The resonator is calibrated to produce a sonic field at the optimum frequency for a given aerosol and can be changed according to the aerosol involved. The resultant coagulation increases visibility and/or electromagnetic transmissibility within the sonic field. The device can be used to reduce obscuration during battlefield operations.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: Light shown through a space containing smoke or an aerosol is detected from everal paths through the space. The light may be gathered from physically separated optical fibers feeding a common photodetector, or several physically separated, series-connected photodetectors may be used. The total amount of light reaching the photodetector(s) is directly related to the average density of the smoke or aerosol.

Abstract: A circuit for determining the fire no-fire characteristics of electroexplve devices involves the application of an incrementally adjustable current level automatically to successive electroexplosive devices. The initial predetermined current level is applied to the first electroexplosive device under test. The current level applied to the next and succeeding electroexplosive devices is increased or decreased automatically by a predetermined amount, depending on whether the previous unit functioned or not. This method results in a mean firing current level being obtained with less chance for error and less operator involvement than required by presently established procedures.

Abstract: A rocket motor nozzle closure for controlling the initial release of prese from the rocket motor nozzle to reduce the occurrence of high pressure shock fronts which are detrimental to the weapon operator. The mass and geometry of the nozzle closure are predetermined to fit the desired motor performance. The release of motor pressure is controlled by the rate of change of momentum of the nozzle closure.

Abstract: The hot spall tester comprises a tube furnace portion adapted for retaining a magazine portion for containment of a plurality of steel ball bearings which are heated and individually dropped through a feed tube member to a programmed or manually operated carrousel portion having a plurality of sample cups for receiving and containing individual solid propellant samples to be spall tested in accordance with the method. A torque rod is employed to facilitate rotation of the magazine portion and carrousel portion in a vertically aligned relationship with the magazine portion so that the heated steel ball is delivered by gravity through a feed tube to a sample cup of the carrousel portion positioned below the magazine portion. In operation the magazine portion and carrousel portion are aligned and vertically positioned to provide a calculated transit time for the steel ball bearing to drop by gravity to the propellant in the sample cup. Subsequent rotation of the carrousel of about 22.