Abstract: A device is provided for cleaning a surface by introducing a highly reactive gas mixture to the surface. The highly reactive gas mixture may include excited species such as ozone and relate excited ions, atoms, and electrons. The excited gas mixture then oxidizes undesirable materials on the surface. The device includes a structure which defines an enclosed space when placed against the surface to be cleaned. A set of one or more electrodes are positioned within the device such that an electrical discharge across the electrodes excites the selected gases species. The electrodes are attached to a power supply capable of generating a high frequency, high voltage discharge. A tube is provided for transporting selected gases, such as air or oxygen, to the enclosed space. Another tube is provide for removing reaction products from the enclosed space. This tube is place in communication with a source of suction for establishing a flow of gases into and out of the enclosed space.

Abstract: This invention is for new compounds, namely, diethanolammoniummethylcubane nitrates, a composition of diethanolammonium methylcubyl nitrates - hydroxylammonium nitrate (HAN) solutions and their method of use as aqueous liquid gun propellant ingredients.

Abstract: An electrically actuated igniter squib is formed by welding a cup containing a pyrotechnic material to a header inserted in the cup, thus forming a hermetic seal. The diameter of the header exceeds the diameter of the cup and the two are joined by forcing, under pressure, the header into the cup to achieve a tight readily welded joint.

Abstract: The invention is a propellant rocket motor case designed to meet insensitive munitions requirements comprising a propellant surrounded by a case having slots therein, and a wrapping around the case, the wrapping comprising a load bearing material which can withstand the hoop load on the case during normal firing of said rocket, the material also having the characteristic of losing strength or melting at undesired temperatures above normal storage temperatures, but below the autoignition temperature of said propellant, so that during undesired high storage temperatures the propellant will exhaust any subsequently generated gases, due to any subsequent propellant burning, by venting through said slots thereby avoiding any explosion or undesired operative one-way thrust.

Abstract: A tool for extracting a helicoil from a threaded hole is provided. The tool includes a wedge member which is configured such that it is capable of wedging one end of the helicoil away from the threads. The tool is also equipped with a pair of jaws which engage the end of the helicoil once it is wedged away from the threads. The tool is then twisted in such a direction that the helicoil tends to be contracted toward its longitudinal axis. Continued turning of the tool in this manner results in extraction of the helicoil from the threaded hole. The tool may also be equipped with a forward cylindrical member for positioning the tool within the interior of the helicoil prior to engagement of the helicoil.

Abstract: A canister loaded solid propellant rocket motor. The canisters are prepared separately and loaded with solid propellant whereby the scrap rate may be reduced after which they are installed in a monolithic case which affords stiffness continuity over the length of the rocket motor to prevent guidance system upsetting free play. In order to reduce the complexity of installation of the membrane seal assembly for each pulse, of a multi-pulse rocket motor the bulkhead therefor is manufactured integral with the case of the respective canister and becomes the forward closure thereof. For a multi-stage rocket motor, the monolithic case may be stepped and tapered, and the stages severable therefrom as they burn out by primer cord.

Abstract: The particle size of a particulate energetic material such as HMX or RDX is reduced by introducing the energetic material as a water-containing slurry at less than 40 percent solids into a high velocity fluid stream in a fluid energy mill and controlling the fluid temperature, fluid velocity, and energetic material feed rate to achieve a particle size of about 10 microns or less.

Abstract: Scavenging and neutralization of HCl from the exhaust plume of a solid grain rocket motor is achieved by including elemental magnesium as the sole metallic component. The magnesium acts both as a propellant fuel and as a scavenger of halogen acids derived form the halogenic oxidizer. Combustion of the high energy propellant produces an exhaust plume from which the halogen acids are scavenged.

Abstract: The insulating coating for an object such as a rocket motor casing is formed by wrapping a strip of insulating material upon the surface of a rotating mandrel. By means of this invention, it is possible to wrap a strip of malleable material such as rubber from an extruder onto a complex shape while exercising precise thickness control, thereby eliminating the need for machining the outer surface. The strip is run through a forming mill of unique construction which shapes the strip during the wrapping process to conform most precisely with the topography of the mandrel. The mill automatically varies both the taper and the width of the strip. The final wrapped product has a smooth outer surface that requires minimal finishing.

Abstract: An igniter which is triggered by a thermocouple for detonating an explosive material for forming an opening in a rocket motor case to render it non-propulsive in the event of a fire dangerously close thereto or for any other suitable purpose. The bridge therefor is preferably a suitable semiconductor bridge for handling a reduced amount of electrical energy which may be provided by the thermocouple. The thermocouple may be a plurality of pairs of dissimilar metal layers or foils alloyed together and the pairs connected in series.

Abstract: Isotactic poly(glycidyl nitrate) useful in solid propellants is produced by polymerizing chiral (R) glycidyl nitrate or its enantiomer, (S) glycidyl nitrate. Chiral (R) glycidyl nitrate or its enantiomer is prepared by sequential treatment of chiral (S) glycidyl tosylate or its enantiomer with nitric acid and sodium hydroxide. Chiral (S) glycidyl tosylate or its enantiomer, (R) glycidyl tosylate, can be produced by Sharpless epoxidation of allyl alcohol or by direct tosylation of commercially available chiral glycidol. Likewise, chiral (R) glycidyl nitrate or its enantiomer, (S) glycidyl nitrate, can be prepared direcly via nitration of (S) or (R) glycidol, respectively.

Abstract: A composition which is capable of producing an obscuring white smoke is disclosed which employs a dicarboxylic acid as the primary smoke producing agent. It is found that by using a dicarboxylic acid smoke producing agent, a generally non-toxic and non-corrosive smoke is achieved. Also included within the composition are a binder, a fuel or coolant, and an oxidizer. The binder may be any one of a number of binders such as nitrocellulose or a polymer binder. A low energy fuel is preferred in order to minimize heat and flame produced. Such fuels may include, for example, starch, dextrose, lactose, sucrose, or sulphur. The presently preferred oxidizer is KCLO.sub.3. Other substances may also be added to the composition. For example, sodium bicarbonate may be added to act as a buffer for the KCLO.sub.3 and as a further coolant. In some cases it may also be desirable to add aluminum for purposes of producing more uniform burning and increased thermal conductivity through out the composition.

Abstract: An igniter for full head-end web rocket motors comprises two molded urethane hemispherical shells, each of which is lined with a layer of solid propellant fuel, joined together to form a solid propellant-lined spherical pressure vessel, which spherical pressure vessel is strengthened by a wrapping fiberglass around the girth, includes an igniter initiator having an elongated tubular urethane housing that contains ignition material and serves also as a structural tie between the hemispherical shells, and a mounting foot incorporated in the lower portion of the spherical shell to facilitate bonding to the rocket motor's propellant grain, nozzle ports located in the lower portion of the spherical shell being provided for igniter flaming gas discharge and subsequent rocket motor ignition.

Abstract: A combination filament winding and tape laying apparatus and method for applying matrix impregnated fibrous material to a generally cylindrical mandrel which is rotated about its cylindrical axis in a stationary horizontal position. A filament winding head is moved horizontally along the length of the mandrel by a carriage for filament winding. A platform is attached to the carriage. A tape applying head is mounted on the platform for applying tape whereby it is unnecessary to move the mandrel from a filament winding machine to a tape laying machine when both operations are required. The tape laying head is preferably portable.

Abstract: A linerless rocket motor is provided by the bonding of a reticulated support structure, which is embedded in an homogenous mass of propellant material including an oxidant, to the inner wall of the rocket motor case. An inexpensive, safe, and easy to manufacture igniter is comprised of an homogeneous mass of propellant material including an oxidant and a reticulated support structure embedded therein. A light weight, high crush strength, and high strain capability sliver for a rocket motor comprises a block of inert material and a reticulated support structure of carbon, graphite, or a non-combustible material embedded therein. A rocket motor is prevented from accidental propulsion during a fire by attaching a propellant block to the outer side of the rocket motor base. The propellant block burns and produces heat during the fire to weaken the motor case so that pressure resulting from burning of propellant in the rocket motor will burst a hole in the rocket motor case to relive the pressure.

Abstract: An improved process for producing poly(glycidyl nitrate) having a functionality substantially equivalent to the hydroxy functionality of the initiator employed in which a catalyst-initiator complex is reacted with glycidyl nitrate and wherein the ratio of mols catalyst/mols hydroxyls in the initiator is <1:1, the gylcidyl nitrate monomer is added to the catalyst-initiator complex reaction mixture at a rate in which the monomer is used up (reacted) essentially as fast as it is added, and the reaction temperature is maintained at a temperature within the range of from about 10.degree. to 25.degree. C.

Abstract: Improved resistance of fiber filled insulation to erosion from combustion gas flow ina solid propellant rocket motor is produced by orienting the fiber direction of the grain of the fibers in the insulation to a direction in which the direction of the fiber grain is substantially perpendicular to the direction of the flow of combustion gas in the rocket motor. Unvulcanized fiber filled insulation sheet stock is folded and compacted in accordion-like style such that the fiber grain direction is reoriented eassentially 90 degrees in the roll direction of the sheet stock.

Abstract: Polymers are produced from 4 and 5 member cyclic ethers, which polymers have hydroxyl functionalities of 4.

Abstract: The insulating coating for an object such as a rocket motor casing is formed by wrapping a strip of insulating material upon the surface of a rotating mandrel. By means of this invention, it is possible to wrap a strip of malleable material such as rubber from an extruder onto a complex shape while exercising precise thickness control, thereby eliminating the need for machining the outer surface. The strip is run through a forming mill of unique construction which shapes the strip during the wrapping process to conform most precisely with the topography of the mandrel. The mill automatically varies both the taper and the width of the strip. The final wrapped product has a smooth outer surface that requires minimal finishing.

Abstract: High performance solid propellant compositions producing halogen-free exhaust products comprised of Ammonium Nitrate and powdered magnesium and optionally containing polyoxypropylene glycol as a binder.