Abstract: Polycyclic spiroorthoester which undergo expansion on polymerization to f resins, rather than shrinkage on polymerization, are employed in fabrication of composite, filament-reinforced, interceptor motor cases. The advantages which accrue to such use of the specified resins relate to the imparting of unique characteristics to the interceptor motor case such as increased structural strength, a reduction in the number of microcracks and voids, and improved bonding between resin and reinforcement. These unique characteristics impart benefits where needed since composite motor cases are fabricated from high strength filaments or tapes such as fiberglass, graphite, poly-p-phenyleneterephthalamide (Kevlar), in a polymeric matrix, and the primary mode of failure is due either to poor adhesion between the matrix and the filament or tapes or because of the development of microcracks or voids in the matrix.The spiroorthoester, 1,4,6-trioxaspiro [4.

Abstract: The conversion of carbon-carbon of a composite material at the surface to licon carbide-hybridized carbon-carbon in accordance with the method of invention is accomplished by reacting the carbon fibers and matrix with silicon monooxide at elevated temperature from about 1500.degree.-1700.degree. C. The conversion of bulk graphite or carbon-carbon composite materials is achieved in 30-60 minutes at 1700.degree. C. With conversion the density is increased from the density of carbon of 1.45 grams/cc to that of silicon carbide of 3.21 grams/cc. The method of reaction in the vapor phase of silicon monooxide with the carbon-carbon bond releases a C atom in exchange for the Si atom with a release of CO from the composite material. Photomicrographic studies indicates a depth of conversion from about 50 to 100 mils.

Abstract: A process for fabrication of a filler for a ballast container used with frescent lighting employs a mixture of a high-density polyethylene in powdered form (derived from recycled milk containers) and dry sand. After loading the specified mixture into a ballast container to fill the unfilled volume remaining after the ballast container has electrical components installed, a closure means is placed on the loaded and filled ballast container, subsequently heated for a predetermined time period to achieve melting of the specified high-density polyethylene and dry sand mixture. After cooling the melted, high-density polyethylene, the high-density polyethylene and dry sand mixture fuses into a solid mass. A preferred mixture is comprised of a 50/50 weight percent ratio of the specified high-density polyethylene and dry sand.

Abstract: Para-polyphenylene sulfide, a non-composite, ultrahigh-temperature-resist, thermoplastic resin, is employed for the manufacture of interceptor motor cases. The thermoplastic resin, para-polyphenylene sulfide, has a combination of properties which are of particular interest in the fabrication of interceptor rocket motor cases. Para-polyphenylene sulfide in ribbonized forth is wound directly onto the required mandrel and then fused into a solid mass. The fused, solid mass has the properties which enables it to serve as both insulator and motor case material. The manufacture of a combination insulated motor case is achieved by the following method: The equipment, first, involves the fabrication of a breakout mandrel by one of several methods. The para-polyphenylene sulfide is ribbonized by extrusion and wound down on the breakout mandrel to the required thickness and fused into a solid mass by heating to its melt temperature of about 285.degree. C.

Abstract: The coacervation of ferrocene and ferrocene derivative is carried out in a ater-soluble polyol, coacervation mixture at a reaction temperature from about 40.degree. C. to about 55.degree. C. The coacervation mixture is comprised of about 70 to about 80 parts of a 1:1 ratio of water and a water soluble polyol selected from glycol, a glycerol, and an erythritol, a urea derivative selected from melamine and triazine, and an aldehyde or ketone selected from the water soluble aldehydes or ketones consisting of methanal, ethanal, propanal, propanone, and 2-butanone. Micro-droplets of the ferrocene derivative, 2,2-bis(ethylferrocenyl)propane, are formed by vigorous agitation of the coacervation mixture containing the ferrocene derivative. A polymeric coating on the outer surface of the micro-droplets produces a coacervate which is separated from the coacervation mixture.

Abstract: Para-polyphenylene sulfide, a non-composite, ultrahigh-temperature-resist, thermoplastic resin, is employed for the manufacture of interceptor motor cases. The thermoplastic resin, para-polyphenylene sulfide, has a combination of properties which are of particular interest in the fabrication of interceptor rocket motor cases. Para-polyphenylene sulfide in ribbonized form is wound directly onto the required mandrel and then fused into a solid mass. The fused, solid mass has the properties which enables it to serve as both insulator and motor case material. The manufacture of a combination insulated motor case is achieved by the following method: The equipment, first, involves the fabrication of a breakout mandrel by one of several methods. The para-polyphenylene sulfide is ribbonized by extrusion and wound down on the breakout mandrel to the required thickness and fused into a solid mass by heating to its melt temperature of about 285.degree. C.

Abstract: A method of providing a very strong mechanical interlock between the insuor and propellant of an interceptor rocket motor by employing a first lay-up material comprised of a cloth mat of woven cotton cloth (muslin) over a release liner with bleeder which covers a mandrel shell with a boss and a second lay-up material of an uncured vulcanizable rubber insulator, e.g., ethylene-propylene-diene-monomer (EPDM) with additives and curatives. The lay-up materials are subjected to a vacuum bag and autoclave curing environment to complete a vulcanization cycle to vulcanize and consolidate the insulator to the cloth mat. The vulcanized insulator/cloth mat is installed in a rocket motor case. The muslin cloth mat has many protruding microfibers which will be in the interface section when an uncured propellant composition is cast onto and cured to the vulcanized insulator/cloth mat. A very strong mechanical interlock is achieved which exceeds breaking strength of propellant and insulator.

Abstract: Edible coatings for protecting perishable foods against spoilage and for significantly extending the life of such foods as fruits and vegetables. A protein derived film is prepared from soybeans, wheat, corn, and mixtures thereof by a process of soaking the grain in water to soften the layer, subjecting the grain-water mixture to the shearing action in a blender to form a milky suspension which is filtered to remove the solids. The residual liquid is heated to denature the higher molecular constituents which are coagulated, allowed to float to the surface, and removed from the denatured proteinaceous solution. The denatured proteinaceous solution is cooled and subsequently employed to coat fruits and vegetable with coatings which function as excellent barriers for preventing the fruits and vegetables from reacting with atmospheric oxygen or carbon dioxide while providing barriers which are permeable to water which precludes their drying out due to dehydration during storage.

Abstract: Tris(N-nitrosophenylhydroxylaminium)aluminum is employed in amounts from about 0.1% by weight to about 0.2% by weight to inhibit the polymerization reaction during propellant mixing. With a weight percent of 0.2 percent, the inhibitor inhibited polymerizaiton to control end-of-mix viscosities to 12 Kp and 13 Kp compared to control propellant viscosities of 26 Kp and 39 Kp after 8 hours and 10 hours respectively. The test propellant and control propellant contained the name ingredients with the exception of the 0.2% additive of the inhibitor in the test propellant. The propellant composition for control and test comprised ammonium perchlorate of 400 micrometer, 200 micrometers, and 20 micrometers in weight percent amounts of 29.5,30.0, and 5.0 respectively, aluminum powder 14.0 weight percent, cyclotetramethylenetetranitramine oxidizer of 4 micrometers particle size in amount of 10.0 weight percent, and hydroxyl-terminated polybutadiene prepolymer binder in a weight percent amount of 11.

Abstract: An apparatus for testing candidate rocket nozzle materials includes an elated member having a combustion chamber extending therethrough, with an inlet at the forward end of the combustion chamber for admitting and igniting a gaseous mixture of hydrogen and oxygen and a nozzle secured to the combustion chamber at the aft end thereof. The nozzle is made of wafers or petals of materials to be tested, with the wafers being secured together at the edges thereof and having a configuration such that the wafers in transverse cross section form a polygon which has an area which increases with distance from the combustion chamber.

Abstract: The trimer of 1,6-hexanediisocyanate, which has the chemical name in acconce with (International Union of Pure and Applied Chemistry) (IUPAC) nomenclature of 7-aza-8-oxo-7[1-isocyanato-6-oxohexyl]pentadecanediisocyanate, is employed in a method of chemical bonding of solid propellant grains to the internal insulation of an interceptor motor. Both the propellant composition and the insulation are chemically reactive with the trimmer identified hereinabove. The method comprises providing a solid propellant rocket motor case having the internal insulation installed therein. Following degreasing of the insulation outer surface, the trimer identified hereinabove is spray coated onto the insulation, and the solid propellant composition is placed onto the trimer. A chemical bond is formed between the propellant and the trimer and the insulation to achieve the chemical bonding of an isocyanate curable solid propellant composition to the internal insulation.

Abstract: Gem-difluoroamino compounds are employed as a partial or complete replacement for TVOPA (trisvinoxypropyl adduct), tris-1,2,3-[bis(1,2-difluoroamino)-ethoxy]propane, in accordance with the nomenclature established by the International Union of Pure and Applied Chemistry. A partial or complete replacement of the vicinal-(1,2-)difluoroamino plasticizer of a difluoroamino-based propellant with its structural isomer or a related structural isomer, namely, a geminal-(1,1-)bis-difluoroamino compound has resulted in two beneficial effects, namely, a marked reduction in pressure exponent and an enhancement of the burning rate of the propellant. Representative of the geminal compounds are the compounds identified as SYEP and SYPO and further identified by the following structural formulas and chemical nomenclatures:SYEPF(NO.sub.2).sub.2 C.CH.sub.2.O.CH.sub.2.C(NF.sub.2).sub.2.CH.sub.2.O.CH.sub.2.C(NO.sub.2).su b.

Abstract: Mechanical enhancement of the burning rate of solid propellants is achieved y the incorporation of limited percentages of heat-expandable beads into the solid propellant matrix. When the flame front reaches an individual bead, the bead which contains an expanding or blowing agent (e.g., pentane, 4,4'-oxybis(benzenesulfonyl hydrazide) (Celogen OT), etc., expands to several times its volume and ruptures. Bead expansion or rupture causes a disruption of the propellant's surface, and the flame can penetrate into the propellant. This penetration results in a major increase in burning rate.

Abstract: A method of extinguishing burning rocket or missile solid propellant employs a device including an explosive charge which is submerged in an extinguishant agent contained in container positioned near the rocket or missile solid propellant being tested or stored. An electrically initiated detonator or heat initiated detonator initiates the explosive charge which causes the extinguishant agent to be explosively driven or propelled horizontally, almost in a solid mass, to the sites of burning propellant to achieve extinguishment within milliseconds. The composition of a preferred extinguishant agent is ethylene glycol of about 55 weight percent, water of about 25 weight percent, and foaming agent of about 20 weight percent.

Abstract: A diisocyanate crosslinking agent having a minimum chain length of methylene groups from 25 to 45 which has a coiling-uncoiling ability in a cured solid propellant composition (under stress and relaxing of stress) as a result of the chain length and configuration imparts superior structural strength to the solid propellant composition. A preferred species is 1,37-heptatriacontane diisocyanate, OCN--(CH.sub.2).sub.37 --NCO, which is employed as an effective crosslinking agent in hydroxyl-terminated polybutadiene propellants.

Abstract: A fire protective blanket is fabricated by sealing and forming between two heets of plastic material a pocket or quilt design of fire extinguishing chemical in powder form which is contained in the formed pockets and selected from potassium hydrogen carbonate, sodium hydrogen carbonate, and the reaction product of potassium hydrogen carbonate and urea. A thickness from about 2 millimeters to about 5 millimeters has been found adequate for the plastic sheet material selected from poly-p-ethylene terephthalamide (Kevlar) or polyethylene. The sealed pocket or patch quilt design is to ensure against the powder from becoming nonuniformly distributed throughout the blanket and to ensure that no settling of the chemical takes place as well. The action mechanism, which can extinguish gasoline fires in millisecond time frames, is due to the rupture of the pockets containing the fire extinguishing chemicals when the gasoline is ignited.

Abstract: Disclosed is a method for ejecting an interceptor missile from the silo in hich it is stored. The method employs an ultrahigh-burning rate (e.g., burning rate 10-20 inches per second) booster solid propellant grain in combination with a fuse or a combination of fuses having a burning rate (e.g. 25 to 100 inches per second) or a rate which is well above that of the ultrahigh-burning rate booster solid propellant grain. The fuses are designed to a predetermined exterior contour which is the same as the exterior contour of the mandrel which would normally be used to provide the contour to the internal perforation of the booster propellant grain. The method include positioning the fuses longitudinally in the booster motor instead of the normally used mandrel, and then casting the propellant around the fuse or a combination of fuses and curing the propellant to yield a booster solid propellant grain.

Abstract: A method of achieving an ultrahigh-burning rate composite solid propellant hrough the embedment of the solid explosive diazodinitrophenol (e.g., 2-diazo-4,6-dinitrophenol) having predetermined shapes and dimensions of cubes or pellets. Cubes having dimension from about 1/16 inch to about 3/32 inches on each side and pellets having dimensions from about 1/16 inch to about 3/32 inch diameters are employed in weight percent ranging from about 1 to about 5 with an uncured composite solid propellant composition in a weight percent range from about 95 to about 99. After being uniformly blended in the uncured state, the propellant and solid explosive are cured to a solid grain which has an increase in burning rate with about a 4.5 weight percent concentration of diazodinitrophenol of about 4.5 composite solid propellant composition with 0% diazodinitrophenol burned at 0.6 inches per second.

Abstract: Aluminum-coated ammonium perchlorate is prepared in an apparatus consisting f a four-opening reaction flask (which serves as a vacuum chamber). The reaction flask is fitted with an electrically-heated tungsten helix coil (for vaporizing the aluminum), a mercury diffusion pump, a mechanical vacuum pump, a dry ice-acetone-cooled trap, and a McLeod pressure-measurement gage. The heater electrodes are submitted through two of the openings; reduced pressure operation is maintained through the third opening, and the aluminum is fed through the fourth opening. The reaction flask is operated at approximately 10 Torr. A magnetic stirrer permits the ammonium perchlorate to be vaporized onto the surface of the ammonium perchlorate after the melted aluminum on the tungsten helix coil is subsequently vaporized from the tungsten helix coil.

Abstract: An encapsulated signal illuminant flare composition is comprised of powde magnesium from about 45 to about 60 weight percent, of powdered sodium nitrate from about 32 to about 49 weight percent, and of capsular adhesives containing about 91 weight liquid materials contained within capsules having cell walls of equal parts Arabic gum and gelatin of about 9 weight percent to yield a binder from about 6 to about 12 weight percent. The composition ingredients are blended in a dry mixer to achieve a homogeneously, blended signal illuminant flare composition. The blended signal illuminant flare composition is incrementally fed into a flare press for compacting into cartridges in two increments at about 14,000 psi pressure which ruptures the capsular adhesives by hydraulic forces to achieve polymer mixing and the surrounding of the powder ingredients with the binder ingredients to form a very homogenous signal illuminant flare composition mass.