Abstract: A selected polybromocompound, when added in an amount from about 1.0 to at 3.0 weight percent to a controllable solid propellant composition, is effective as a reignition suppressant without having detrimental effects on the ballistic properties of the propellant. The mechanism for accomplishing these desired results consists of sweeping away the combustible exhaust products from the propellant's extinguished surface by the non-combustible decomposition gases of a polybromocompound which is selected from diammonium tetrabromophthalate, tetrabromophthalimide, and N-substituted tetrabromophthalimide.

Abstract: An organometallic polymeric resin is used to impregnate glass filaments (or oron, graphite, carbon, etc.) which are employed in the fabrication of composite motor cases and inert components of a solid propulsion system. The resulting motor case or inert component has the ability of regulating the amount of damage that a nuclear blast would inflict on the solid propulsion system to a level which is below the threshold damage value and the system remains operable. The metal of the organometallic polymeric resin is integral with the resin molecule. The preferred metal is tin which is effective in imparting an ability to stop or slow the passage of photon energy because of its capacity to absorb such energy.

Abstract: Burning rate promoter (e.g. n-butylferrocene, n-hexylcarborane) is incorpted into resonance rods that are used to eliminate combustion instability of solid propellant. As the solid propellant burning progresses the resonance rods undergo ablation, and as ablation takes place, subsurface quantities of the burning rate promoter are exposed and continuously released into the combustion zone to catalyze the combustion process. This invention also employs porous resonance rods which contain the burning rate promoter and a selected material for suppressing combustion instability as infiltrants.

Abstract: A mixed, intramolecular perchlorate salt, having a carboranyl moiety and ferrocenyl moieties, is used as a partial replacement for ammonium perchlorate to achieve ultrahigh burning rates for propellants. The perchlorate salt when incorporated into a propellant composition contributes to the oxidizer function, and in addition, since both boron and iron are present, two mechanisms for burning rate catalysis are exploited. The described compound, carboranyldiferrocenylmethyl perchlorate, obviates the need for incorporating the burning rate catalysts separately.

Abstract: Tetracene, H.sub.2 N.C(:NH).NH.NH.N:N.C(:NH).NH.NH.NO (C.sub.2 H.sub.8 N..10 O), that is pelletized by dead pressing at 10,000-30,000 psia is employed as a preferred gas generant for near-neutral combustion products. The chemical, tetracene, is almost completely nitrogen-containing, and has only negligible amounts of carbon or oxygen which results in producing dominant combustion products of nitrogen. Tetracene is employed as a gas generant in a method which produces near-neutral combustion products that are compatible with a variety of oxidizers (e.g., IRFNA, ClF.sub.3, ClF.sub.5, etc.) and a variety of fuels (e.g., UDMH, MHF, etc.). Contact of the combustion products with the oxidizers or fuels does not interfere with their normal functioning.

Abstract: A rocket motor case liner material that is the reaction product of tung oil ith phenolic resins with an added filler selected from tricalcium phosphate, boric acid, or powdered asbestos. When cured the product yields a liner material with a highly wrinkled interior surface having a greatly increased surface area for bond formation with propellant to permit improved propellant-to-liner bond because of mechanical adhesion.

Abstract: A solid propellant composition that employs methyltricarboranylmethyl perorate as a replacement for some of the ammonium perchlorate and for all of the carboranyl plasticizer achieves both improved burning rate and improved mechanical properties. In addition to methyltricarboranylmethyl perchlorate, the propellant of this invention comprises a diisocyanate crosslinking agent, hydroxyl-terminated polybutadiene binder, an interfacial bonding agent and aluminum metal fuel.

Abstract: Methyltricarboranylmethyl perchlorate is disclosed along with its synthesis nd its use in a solid composite propellant. Three carboranyl groups and a perchlorate group are contained in the intramolecular perchlorate salt, methyltricarboranylmethyl perchlorate, which is used as a partial replacement for ammonium perchlorate and as a replacement for liquid carborane catalyst-plasticizer compounds to achieve ultrahigh burning rates for propellants. The perchlorate salt when incorporated into a propellant composition contributes to the oxidizer function, and in addition, since three carboranyl groups are present in each molecule of the salt, the burning rate catalysis function is accomplished without having to incorporate separate burning rate catalysts.

Abstract: A means for reducing or eliminating the erosive burning which takes place ring the burning phase of solid propelled rocket motors which have a large length-to-diameter ratio and/or slow-burning propellants is disclosed. The means comprises incorporating into the solid propellant, in limited percentages (0.1-1.0%), a silicate selected from talc, kaolinite, kaolin, muscovite mica, and feldspar. The silicate additive is effective for composite or double-base solid propellant compositions. The solid composite propellant compositions can vary widely in formulation ingredients to include numerous ballistic modifiers; however, the general formulation for a composite propellant contains in addition to the silicate, a high solids loading of an inorganic oxidizer such as ammonium perchlorate, a polybutadiene binder with curatives and crosslinking agents, and optional metal fuel, preferably aluminum. The polybutadiene can have carboxyl- or hydroxyl-terminal groups.

Abstract: A method is disclosed for curing a nitrogen-fluorine propellant in an eleomagnetic alternating field. The propellant is cast into thin walled-titanium tubes of predetermined size and with a graphite-epoxy overwrap. When the propellant-filled tubes are exposed to electromagnetic radiation, the propellant is cured to a grain in about 30 minutes as compared to about 5 days required for thermal curing at 135.degree.F. The disclosed method of curing is achieved because of the permeability of the overwrapped tubes to microwaves. The grain cured by the disclosed method acquires the desired mechanical properties, particulary, a greater uniformity, as indicated by a higher Shore hardness value, within a considerably shorter time period. The greater uniformity of mechanical properties throughout the propellant grain is particularly essential for this application because of the small quantity of propellant and the thrust repeatability necessary from one micromotor to another in the Maneuver Motor Array.

Abstract: A means for reducing or eliminating the erosive burning which takes place ring the burning phase of solid propelled rocket motors which have a large length-to-diameter ratio and/or slow-burning propellants is disclosed. The means comprises incorporating into the solid propellant, in limited percentages (0.1-1.0%), a silicate selected from talc, kaolinite, kaolin, muscovite mica, and feldspar. The silicate additive is effective for composite or double-base solid propellant compositions. The solid composite propellant compositions can vary widely in formulation ingredients to include numerous ballistic modifiers; however, the general formulation for a composite propellant contains in addition to the silicate, a high solids loading of an inorganic oxidizer such as ammonium perchlorate, a polybutadiene binder with curatives and crosslinking agents, and optional metal fuel, preferably aluminum. The polybutadiene can have carboxyl- or hydroxyl-terminal groups.

Abstract: Formamidinesulfinic acid (thiourea dioxide) is employed as an additive to ert motor components of solid-propelled rocket motors to eliminate afterburning which is defined as the combustion of gases (produced by the pyrolysis of the inert motor components) with the air ingested into the rocket motor due to the free convective circulation after motor burnout.

Abstract: A tetrabromo compound, e.g., tetrabromophthalic anhydride (TBPA) and tetromophthalimide (TBPI), their salts and derivatives, when employed as additives to the inert components when these inert components are being compounded or as crosslinking agents for these inert components, impart fire-retardancy characteristics to these inert components (liner, insulation, slivers, etc.) which undergo afterburning (combustion of the gases which are produced by the pyrolysis of the inert components with the air ingested into the rocket motor due to the free convective circulation after motor burnout).

Abstract: Polybutadiene-iron carbonyl complexes are useful as the binder-catalyst for ast-burning rate propellants which are additionally comprised of ammonium perchlorate, aluminum powder, curative-cross-linking agent, and additive (e.g., wetting agents, grinding aids, etc.). The complexes, which are regarded as copolymers of uncomplexed polybutadiene and tricarbonyl(diene)-iron units [C.sub.8 H.sub.12 Fe(CO).sub.3 ].sub.x (where x is one or multiples of one), can be utilized as a high burning rate additive or as a plasticizer for carboxylated polybutadiene binder materials, such as, polybutadiene acrylic acid, polybutadiene acrylic acid-acrylonitrile, carboxyl-terminated polybutadiene, and hydroxy- or epoxy-terminated polybutadiene. The various binder materials, such as those set forth above, can be reacted with the polycarbonyl-iron directly to yield a prepolymer which can be used as the binder-catalyst for propellants containing, an oxidizer, metal fuel, curative-cross-linking agent, and additives.

Abstract: The use of certain chemical constituents, such as hexanitrostilbene, triaotrinitrobenzene, picric acid and the ammonium salt of picric acid, which can be incorporated into propellant compositions which have high pressure exponents to reduce them to acceptable values. The propellant compositions generally include a binder, a curing agent, oxidizer ingredients, and other additives which depend upon the specific structure of a particular propellant formulation.

Abstract: Bis(trinitroethyl)nitroamine, O.sub.2 N.N[ CH.sub.2 .C(NO.sub.2).sub.3 ]..2, (BTNEN), is used as an oxidizer in smokeless propellants. BTNEN can be used as a replacement for cyclotetramethylene tetranitramine (HMX) or cyclotetramethylene trinitramine, (RDX) in smokeless propellant compositions. Ready ignitability is ensured when BTNEN is used in hybrid grains. A higher performance results when BTNEN is substituted for HMX or RDX in a propellant formulation. The propellant composition employing BTNEN as oxidizer has lower tendency to afterburning since it is a more effective oxidizer and as a result thereof, there are few combustibles in the exhaust products.

Abstract: This invention disclosure relates to the incorporation of a high nitrogenntaining compound selected from tetrazole and bitetrazole in the form of a doughnut forward of the nozzle throat or in the form of a toroidal ring attached to the aft end of the nozzle exit cone. Both have been demonstrated as an effective means of reducing the quantity of water in the exhaust plume to an acceptable level which does not impart adverse effects on sensors or cause a reactive effect on the graphite constituents of the rocket nozzle. The compound, bitetrazole or tetrazole, can also be incorporated into the solid propellant where it will function similarly as a means or mechanism for water removal from the exhaust plume. Because of its contribution to the propellant's performance through the generation of near-incompressible gases, N.sub.2, H.sub.2 and CO, it is a desirable propellant ingredient.

Abstract: The incorporation of tris(difluoroamino)-methoxyethyl ammonium perchlorate n small percentages in conventional composite solid propellant compositions to achieve a marked increase in burning rates.

Abstract: Propellant compositions using bis[N-(trinitroethyl)nitramino]ethane as an oxidizer for smokeless propellants that additionally contain binder ingredients, crosslinking agent and other additives as desired.