Abstract: A high energy, high performance, ultrahigh-burning rate composite propell results when 2-azidoethyl acrylate is copolymerized with acrylic acid and is employed as the binder system for the composite propellant. The energetic binder when used in an amount of about 4.25 weight percent of an azido-based propellant composition as compared to a ethyl acrylate binder system results in a specific impulse increase from about 264 (lb-s/lb) to about 275 (lb-s/lb), and a burning rate increase from about 13.7 ips to about 19.8 ips at 1000 psia, and a burning rate increase from about 21.6 ips to about 30.2 ips at 2000 psia. The other propellant ingredients comprise a high solids loading of ammonium perchlorate, aluminum flake and aluminum powder, a burning rate catalyst of carboranylmethyl propionate, graphite linters, the crosslinking and curing agent 4,5-epoxycyclohexylmethyl 4',5'-epoxycyclohexylcarboxylate (ERL-4221), tris-1,2,3[bis(1,2-difluoroamino)ethoxy]propane (TVOPA), and a processing aid of lecithin.

Abstract: Preformed metal/oxidant agglomerates for enhancement of propellant burning ate are prepared from a finely divided metal (aluminum, boron, titanium, etc.), ammonium perchlorate, and a small quantity of the same binder material that goes into the manufacture of the propellant, such as, hydroxyl-terminated polybutadiene crosslinked with a polyisocyanate. Additional ingredients can be incorporated into the agglomerates to bring about further enhancement of burning rate, such as, an ammonium perchlorate decomposition accelerator triphenylbismuthine, a carboranyl burning rate enhancer, iron oxide, etc. Agglomerates are prepared in a fluorinated and/or chlorinated hydrocarbon solvent in which the agglomerate formulation ingredients are insoluble. Any remaining solvent is then evaporated under reduced pressure and the agglomerates are subsequently cured. Optimum mesh size of the agglomerates is 300-500 micrometers.

Abstract: A sabot arrangement for launching a penetrator from an electromagnetic acerator and including a forward sabot that is made of a multiplicity of segments with the segments being made of electrical and thermal insulating material and a base sabot that includes a metal shell made of three integral parts with a cap of electrical and thermal insulating material for insulating the shell structure from the launch tube of an electomagnetic accelerator.

Abstract: A general purpose expandable adhesive comprised of a spiroortho ester synthesized from the lactone, 6-caprolactone, and the diglycidyl ethers of bisphenol A and 1,4-butanediol, Cab-o-Sil thickener/thixotrope, silica (325 mesh), and Unirez 2800, amidoamino curing agent, has superior tensile strength, superior bondability and with less void formation to aluminum, steel, wood, and cured concrete as compared with a general purpose adhesive which does not contain a spiroortho ester.

Abstract: An embedment system with controlled shrinkage for use with a composite-modified double-base propellant composition which is comprised of an embedment granule portion in percent by weight of nitrocellulose of about 23.0, nitroglycerine of about 8.8-13.8, triacetin of about 1.2, bisspiro orthocarbonate from about 2.5-5.0, resorcinol of about 1.5, 2-nitrodiphenylamine of about 1.0, ammonium perchlorate (10 micrometers) of about 48.5 and aluminum powder (20 micrometers) of about 10.0 and an embedment resin portion in percent by weight of bisphenol A-epichlorohydrin of about 50.0, epoxidized dimer acid of about 50.0, and a curative which is comprised of equal parts mixture of methylenedianiline, m-phenylenediamine, and i-propyl-m-phenylenediamine with an added accelerator of 2,4-dinitrophenol. This embedment system employs a specific bisspiro orthocarbonate, 3,9-bis(5'-norbornene-2'-yl)-1,5,7,11-tetraoxaspiro[5.

Abstract: Cure shrink-resistant missile motor cases are disclosed along with their method for construction. These cases comprise a matrix resin composition which includes a bisspiroortho carbonate as a fourth component, a curing agent of o-phenylenediamine boron trifluoride etherate as a third component, butanediol diglycidyl ether as a second component, and equal parts by weight of diglycidyl ether of bisphenol A and epoxidized dimer of oleic acid as a second component and additionally, they comprise, in combination therewith, a high strength fiber reinforcement material selected from the group consisting of fibers of glass, graphite, and poly-p-ethylene terephthalamide (Kevlar). The specific bisspiroortho carbonate which achieves an expansion of the matrix resin on polymerization or curing is 3,9-bis(5'-norbornene-2'-yl)-1,5,7,11-tetraoxaspiro [5.5]undecane.

Abstract: Disclosed is a method of microwave drying of ammonium perchlorate grinding pheres. A preferred embodiment of the method employs a tunnel oven in combination with a microwave generator having an appropriate power supply. The tunnel oven receives microwave energy through transmission ducts in communication with a channeling device to distribute microwave energy over the grinding spheres to be dried. A preheated air supply facilitates moisture removal from the tunnel oven after the moisture adhered or occluded to the grinding spheres' surfaces is evaporated from the grinding spheres as a result of molecular vibrations of the water molecules after they absorb the microwave energy. A predetermined microwave frequency range and a predetermined drying time are employed to more efficiently remove adhered or occluded moisture from carbide grinding spheres as compared to conventional convection drying.

Abstract: Ethanol is recovered from fermentation products by a countercurrent extraction process which employs diethyl ether as the extraction solvent to form a diethyl ether-ethanol mixture. The ethanol is salted out by adding calcium chloride to the mixture, and the diethyl ether layer is separated and recycled. The calcium chloride in ethanol solution is removed by adding sodium carbonate to form the solids calcium carbonate and sodium chloride which are removed by filtration. The ethanol is recovered as the filtrate.

Abstract: Unconfined detonation by a single-event process is achieved by simultaneous ispersion of both fuel and the initiating chemical catalyst into the atmosphere. The fuel is selected from a volatile liquid (lower molecular weight, alkanes, epoxyalkanes, etc.), aluminum, boron, etc. or mixtures thereof. The initiating chemical catalyst is selected from n-hexylcarborane, carboranylmethyl propionate, ferrocene, n-butylferrocene etc. The fuel and initiating chemical catalyst are dispersed simultaneously to form a cloud after the catalyst is premixed with the fuel and housed in a container prior to dispersion. The dispersed catalyst catalyzes the reaction between fuel and atmosphere oxygen to produce the explosive oxidation of the fuel-air mixture.Additional enhancers for detonability such as a bis(difluoroamino) compound (TVOPA) and/or ultrafinely-ground ammonium perchlorate are included in the fuel-catalyst mixture when the unconfined detonation is to be achieved in an oxygen-deficient atmosphere.

Abstract: An improved embedment system is disclosed which is comprised of an embedm granule portion in percent by weight of nitrocellulose of about 23.0, nitroglycerine of about 15.0, resorcinol of about 1.5, 2-nitrodiphenylamine of about 1.0, ammonium perchlorate (10 micrometers) of about 45.5, and aluminum powder (20 micrometers) of about 14.0 and an embedment resin portion in percent by weight of bisphenol A-epichlorohydrin of about 44, epoxidized dimer acid of about 20, and a curative which is the condensation product of 2 moles of 1,2-bis(maleimido)ethane and one mole of triaminotriazine of about 36.0. This embedment system has superior characteristics of a high peel strength and greater resistance to penetration by or absorption of carboranylmethyl propionate or casting solvent absorption.

Abstract: Disclosed is a method for increasing the burning rate of solid propellants hich contain metal staples and/or metal flakes, etc., through the use of an electrical field effect created by the application of direct-current to a propellant grain placed between direct-current electrodes. This method also provides a means of correcting for anisotropy of burning rate in propellants which contain metal staples, metal flakes, etc., where non-random orientation may occur at the motor wall and mandrel surface.

Abstract: Disclosed is an improved method and the thermolysis equipment setup for certing tetraethylammonium tetrahydridoborane to bis(tetraethylammonium) decahydrodecaborane by a thermolysis reaction which increases the yield in the range between about 22% to 64%, and, perhaps higher. The heat transfer control is maintained by employing triethylamine borane in the reaction mixture between about 175.degree. C. and 186.degree. C. for a reaction time from about 1 hour to about 2.5 hours. The disclosed thermolysis procedure is successful in dissipating a major portion of the exothermic heat. The control of the generated heat serves to minimize the formation of the byproduct bis(tetraethylammonium) dodecahydrododecaborane while increasing the yield of the desired product, bis(tetraethylammonium) decahydrodecaborane.

Abstract: Means for generating an inert enveloping gas for surrounding the exhaust me of a rocket motor are disclosed along with how the enveloping gas serves to prevent the adverse interaction between the rocket motor exhaust plume and the on-board sensors when the rocket motor is operating in exoatmospheric environments. Means for generating an inert enveloping gas utilizes a combination of a T-tube rocket motor and a donut of a chemical which is a gas generant selected from hydrazine bisborane, covalent azides, tetracene, or fluorocarbon-nitroamine.

Abstract: Disclosed is a method for the prevention of the formation of ammonia as a product in the reaction of hydrazine and a halogen oxidizer used in a liquid-propelled rocket engine and in chemical laser pumping systems. The method employs vanadium pentafluoride as an additive up to about 1% to the halogen oxidizer to thereby shift the equilibrium of the reaction between the hydrazine and the halogen oxidizer so that no ammonia is produced.

Abstract: Disclosed is a method of converting non-hypergolic, liquid, rocket propellants into hypergolic propellants. The method to accomplish the conversion relates to the use of ammonium metavanadate as an additive to the liquid oxidant, such as, red fuming nitric acid (RFNA). The RFNA with additive is hypergolic with the usual fuels with which RFNA has been employed where a separate ignition system is normally required. RFNA with additive is also hypergolic with fuels which have been non-hypergolic and which have not been so used in the past with RFNA. These additional fuel blends include a fuel material selected from turpentine, aniline, triethylamine, furfuryl alcohol or blends of these fuel materials.

Abstract: A highly effective liner-barrier is disclosed for use with carborane-conting ultrahigh burning rate propellants. The liner-barrier includes a resinous matrix selected from an epoxy, polysulfide, and a near neutral phenolic resinous liner-barrier composition, and a leafing aluminum flake incorporated therein. When this liner-barrier is applied to the surface of a rocket motor case, or insulation when used, the leafing aluminum flake floats to a region near the surface of the resin. The liner-barrier is cured to yield a leafing aluminum flake sub-surface layer which markedly reduces the permeability of the liner-barrier by the carboranyl burning rate catalysts which results from the migration or diffusion of the carborane from the propellant. The ultrahigh burning rate propellant is compatible with and forms a secure bond to the liner-barrier. These requirements of compatibility and forming a secure bond are essential for the field of use.

Abstract: A solid propellant grain is converted from a non-conductive filled elasto into a highly-conductive filled elastomer by introducing an effective amount of an alkali metal tungstate or the analogous ammonium salt which, in addition to imparting electrical conductance characteristics, also functions as an oxidizer in the propellant composition. When sodium tungstates, known as tungsten bronzes, or the analogous ammonium salt, are used to replace from 1 to 3 parts of the ammonium perchlorate oxidizer in the propellant formulation, it changes the grain to a highly-conductive grain, and, thereby, permits measuring the continuity of the propellant grain by means of electrical conductance measurements.

Abstract: Disclosed is a method of providing an ingition system for substantially sltaneously and uniformily igniting all the internal burning surfaces of a large propellant grain of the internal burning grain type that is employed in an upper stage advanced missile interceptor. The propellant grain to be ignited is also of the type which requires support for reinforcing the grain during high acceleration loads especially before the interceptor stage motor is pressurized. The means for igniting the large propellant grain is comprised of high-velocity deflagration compositions which are derived from cesium dodecahydrodecaborane and which are extruded or formed in a variety of shapes. These shaped high-velocity deflagration compositions are then bonded to a consumable casting mandrel, or to a grain support tube which also serves as a casting mandrel.

Abstract: Disclosed is a method of synthesis and the compound synthesized B.sub.10 ub.12 [(CH.sub.3).sub.2 S].sub.2. The method employs the starting compound (R.sub.4 N).sub.2 B.sub.10 H.sub.10, as a source of the ten-boron ion (e.g., B.sub.10 H.sub.10.sup.-2), in which the starting compound, wherein R equals an alkyl with the formula C.sub.n H.sub.2n+1 and wherein n equals 2, 3, or 4, is converted to Li.sub.2 B.sub.10 H.sub.10 by ion-exchange. The Li.sub.2 B.sub.10 H.sub.10 is reacted with HCl in (CH.sub.3).sub.2 S solution to produce the compound B.sub.10 H.sub.12 [(CH.sub.3).sub.2 S].sub.2, a precursor compound for synthesizing carboranyl burning rate accelerators. The precursor compound is reacted with propargyl propionate if the interest is to synthesize carboranylmethyl propionate; 1-octyne to synthesize n-hexylcarborane; or propargyl ethyl sulfide or propargyl propyl sulfide to synthesize carboranylmethyl ethyl sulfide or carboranylmethyl propyl sulfide, respectively.

Abstract: Improved method of manufacturing composite rocket motor cases and laminated tructures is disclosed which includes a layered procedure wherein a high percentage of a highly flexibilized, low-modulus epoxy blend of a resin composition is employed in the matrix of the innermost layer section with a subsequent, gradual addition of a toughened (or hard) high-modulus resin to the filament impregnating bath during the filament winding process to achieve a higher-modulus resin composition in the intervening layers with the highest modulus resin composition being in the outermost layer section to achieve a gradation in mechanical properties to mechanical behavior.