Abstract: An incinerator has a spherical chamber body to define an incineration chamber and includes a port structure with an opening that provides access to the incineration chamber. A hatch is pivotably attached to the port structure to provide access to the opening or to close the opening in the port structure. An incendiary device support member located within the incineration chamber to hold an ignitable incendiary device. A flammable panel member is located within the incineration chamber and positioned over the incendiary device support member. The panel member supports IEDs, explosive devices or biological agents for incineration. When the ignitable incendiary device is ignited, thermal energy is produced to incinerate the IEDs, explosive devices or biological agents positioned on the panel member.

Abstract: The present invention relates to compositions that can be used in hydrolyzing biomass such as compositions comprising a polypeptide having glycosyl hydrolase (GH) family 61/endoglucanase activity and/or a ?-glucosidase polypeptide, methods for hydrolyzing biomass material, and methods for using such compositions.

Abstract: The present invention relates to compositions that can be used in hydrolyzing biomass such as compositions comprising a polypeptide having glycosyl hydrolase (GH) family 61/endoglucanase activity and/or a ?-glucosidase polypeptide, methods for hydrolyzing biomass material, and methods for using such compositions.

Abstract: The invention relates to an apparatus for evaluating energetic materials for ignitability, flamespread, pressure and thermal characteristics, energetic material interaction, and other properties. The invention is directed to an apparatus for analyzing the suitability of energetic materials for interactions with other energetic materials, explosive or non-explosive. The invention includes a vented combustion chamber, an ignition tube and a firing mechanism. The invention also includes methods for using the apparatus. For example, the apparatus of the invention may be used to analyze energetic materials for their use in destroying rubble which may contain explosive material.

Abstract: The present invention relates to variant phytase enzymes having altered properties.

Abstract: The present invention relates to variant phytase enzymes having altered properties.

Abstract: An ordnance venting system has one or more adapters that separate the warhead section from other sections of a rocket, or submunition compartments within the warhead itself. The adapters structurally fail at given temperatures and pressures to reduce the danger of explosion from heat induced over-pressurization. By dividing the sections of the rocket with the adapters, the separate sections of the rocket become physically separated by the structural failure of the adapters.

Abstract: The present invention comprises a kinetic energy penetrator warhead that may engage both surface and buried soft and hardened targets. The warhead contains a high-temperature incendiary (HTI) fill capable of destroying chemical and biological agents in such a manner to minimize dispersal of these agents. Bomblets are incorporated into the portion of the warhead that penetrates to the target and are ejected, with the HTI fill, from the warhead in order to provide holes in chemical or biological agent tanks to allow the fill to react with said agents. Finally, a guidance system is provided to direct the warhead to the target.

Abstract: A method for producing a non-welded shape memory alloy ring, such as Nitinol, includes a wire segment. The alloy ring may be used in a venting mechanism for rocket motors or as a coupling device, such as for fitting piping.

Abstract: A high torque nozzle system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible vanes inside of the nozzle. The vanes erode as the rocket exits the launcher. The high torque nozzle system has a first section of a rocket nozzle body, a second section of the rocket nozzle body and a torque ring that contains erodible vanes. The torque ring is fitted into a groove formed by the first and second sections of the rocket nozzle body, which are threaded together.

Abstract: A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned torque ring inside of the nozzle that is anchored with erodible tabs. The tabs erode as the rocket exits the launcher. With the erosion of the tabs, the torque ring is free to rotationally move, which eliminates any torque imparted onto the rocket while retaining the torque ring with the rocket. This increases the reliability of rocket precision.

Abstract: An explosively driven impactor grenade includes a grenade body having a substantially spherical shape and a hollow central portion, the grenade body including a plurality of recesses formed on an external surface thereof with each recess including an opening into the hollow central portion of the grenade body, the grenade body including an opening on the exterior surface that connects with the hollow central portion; a fuze disposed in the hollow central portion of the grenade body; a fuze cap for closing the opening on the exterior surface that connects with the hollow central portion; and a plurality of explosively driven impactors respectively disposed in the plurality of recesses formed on the external surface of the grenade body, the explosively driven impactors being connected to the fuze through the recess openings into the hollow central portion of the grenade body.

Abstract: The invention comprises an improved precision rocket motor and warhead system by increasing the spin rate of the rocket motor. The system comprises an outer housing segment attached to the end of a rocket motor tube and an annular sleeve placed within the end of the outer housing segment so that the end of the sleeve is aligned with the end of the segment. At least two annular bearings are placed around the outer surface of the sleeve. Normally the annular bearings will be made of a plastic type material that can be “stretched” around the outside of the sleeve prior to placing it within the outer housing segment. The inner surface of the sleeve will include a warhead attachment mechanism to secure the warhead to the inner surface. Finally, the invention includes a locking mechanism that locks the sleeve in place within the outer housing segment while attaching the warhead to the sleeve and unlocks to allow the sleeve to rotate independently of the rocket motor.

Abstract: A rocket spin control system for a tube launched rocket has a fixed position nozzle on the rocket and a set of internally positioned erodible or retractable vanes inside of the nozzle. The vanes are removed from the rocket propelling thrust at rocket exit from the tube.

Abstract: An ordnance venting system has a thermally initiated rapid deflagrating composition that detonates a high energy material. The high energy material is configured as a shaped charge and surrounds the ordnance housing of a rocket motor. During cook-off of the munition, the high energy material detonates, rupturing the structural integrity of the ordnance housing sufficiently to release pressure therefrom.

Abstract: An ordnance venting system has an ordnance device having a casing with a vent opening, a dome plug fitted into the formed vent opening and an adapter fitted over the dome plug on the outside of the casing. The adapter connects sufficiently to the casing to retain the dome plug against the formed vent opening for given pressures. The adapter melts at high temperatures and releases the dome plug to reduce the danger of explosion from heat induced over-pressurization.

Abstract: A flashless rocket propellent has a continuous potassium sulfate rod extending though the length of the propellent component. The flashless rocket propellent is particularly useful in the MK 66 Rocket Motor.