Abstract: Composite polar bosses applied in rocket motor cases have very desirable characteristics. The lead time for a boss can be reduced from 6-12 months to 2-3 months. Weight savings for the boss are about 20-40%. A composite polar boss which attaches closures to solid fueled rocket motor cases is disclosed. This polar boss is a carbonized fabrication which sits within a circumferential indentation within the motor case, and has a threaded inner circumference which permits the closure to be attached thereto. The materials of the boss are selected to permit a service temperature of 350 degrees F.

Abstract: A solid grain block is housed in a casing with interposition of a heat protection layer and defines a combustion chamber, and a separation zone is formed between the solid grain and the heat protection layer of the rocket motor bottom structure by means of a skin detached from said layer and adhering to the solid grain, at least one of the two parts constituted by the detached skin and the heat-protection layer of the rocket motor bottom structure being provided with projections or teeth to ensure a minimum spacing of the detached skin with respect to said layer and to give easy access to the gases into the separation zone.

Abstract: A method of making solid rocket propellant that facilitates tailoring of a variable burn rate. The method comprises molding binder and fuel and/or oxidizer to produce, for example, a molded strip of solid rocket propellant material. The molded solid rocket propellant material is formed into a desired shape by, for example, filament winding. In a preferred aspect, the solid rocket propellant is cured prior to being encased in a rocket motor casing. This improves rocket propellant to rocket engine casing bonding. Yet another aspect of this invention is a method of making solid rocket propellant comprising forming binder and oxidizer into separate strips and combining the binder and oxidizer strips to form solid rocket propellant material.

Abstract: Thermoplastic elastomer particulates, oxidizer particulates, fuel particulates, plasticizers and other propellant formulation ingredients are mixed to produce a dry blend. The dry blend is tightly packed into a rocket motor casing or mold. The dry blend is then heated in place, beginning at the bottom and continuing upward, to fuse the thermoplastic elastomer. During fusion, vacuum and mechanical compaction pressure are used to eliminate interstices. Upon cooling, a solid propellant grain is produced.

Abstract: A high acceleration high performance solid rocket motor grain such as for a ballistic defense missile or rocket assisted projectile comprises a propellant material which includes a highly plasticized binder so that the grain has a solids ratio equal to at least about 95 percent. In order that the grain with such a solids ratio may have adequate strength and withstand high acceleration forces, a reticulated structure is embedded therein. A method of constructing a rocket motor having such a grain is also disclosed.

Abstract: An elongated flexible bag is fitted inside templates that have aligned openings therein corresponding in shape to that desired for a solid rocket motor propellant bore. With the bottom sealed, the bag is filled with a multiplicity of solid pieces each having a cross section substantially less than that of the bag. When filled, suction is applied to the bag by a vacuum needle to exhaust air therefrom until the bag is very tight on the solid pieces contained therein. The vacuum needle is then withdrawn, the hole made thereby is sealed, and the templates are removed from the bag. After use in loading a solid rocket motor with propellant, the bag is cut open, the solid pieces are removed, and the bag is peeled out of the bore in the propellant.

Abstract: A process for preparing a porous propellant grain which comprises blending at least two combustible materials to form a homogeneous mixture, adding a predetermined amount of a liquid dispersant to said mixture to form a slurry, and flash drying the slurry in order to form a porous, single grain propellant having a greatly increased burning surface. A single grain propellant is produced having a flat, torroidal shape with a central cylindrical core and honeycombed with a plurality of porous channels extending entirely through the grain to increase the burning surface thereof.

Abstract: A reinforced split-flap hinge for supporting the unpressurized propellant grain of a rocket motor in a high acceleration environment includes a circular piece of material and an afterwardly spaced first annular piece of material bonded to the convex forward surface of the propellant grain, the material of the circular piece of material and the first annular piece of material being chopped fibers of insulating material in a rubber matrix, with a second annular piece of material bonded to the surface of the circular concave piece of material, the convex forward surface of the propellant grain, and the surface of the first annular piece of material, a third U-shaped annular piece of material having first and second skirts extending aft with a first skirt bonded to the surface of the second annular piece of material, the second and third annular pieces of material being made of fabric reinforced polyisoprene, and a fourth annular piece of insulating material made of powder filled polyisoprene positioned between t

Abstract: A solid propellant grain which comprises an homogeneous mass of propellant material including an oxidant. A variable burn rate is provided by embedding a reticulated structure in a portion only of the propellant mass. The reticulated structure may be coated with a high thermal conductivity material to provide an increased burning rate. The coat of material is selected to preferably provide improved bonding to the propellant mass.

Abstract: The utilization of metal hydride and an acidic reagent for the accelerating of masses, and propulsion devices for applying such materials. The materials are of a saline complex metal hydride and acidic reagent which is sprayed onto the metal hydride which is offered in a lumpy consistency, for the pulse-like generation of expanding reaction gas bubbles in a constructive or dynamically, yieldably dammed chamber. Also provided is a propulsion device for the application of the above materials, with a support for a saline complex metal hydride of a lumpy consistency in a yieldably dammed expansion chamber in which an injection nozzle for the reagent is directed towards a surface portion of the metal hydride.

Abstract: A propellant configuration for a solid propellant rocket motor, comprising a generally cylindrical housing containing a generally cylindrical main grain having a central cavity, and an igniter assembly supported in the central cavity and having means therein for bringing about combustion. At the time of actuation of the igniter assembly, hot gases are directed along flutes formed in the interior of the main grain, to cause burning thereof to take place. Advantageously, the propellant utilized in the main grain is the same as utilized in the igniter assembly, with the burn surface area of the igniter grain being in a pre-established relationship to the burn surface area of the fluted main propellant grain, such that the igniter grain will be totally consumed at the time that the flutes of the main propellant are consumed.

Abstract: An air-breathing solid fuel rocket motor containing a solid fuel ramjet gn having a plurality of concentric layers of solid fuel which provide a means of controlling the thrust of the motor.

Abstract: An end-burning grain structural arrangement for a solid rocket propellant is formed by two parallel inhibited grain components formed into an "S" shaped cross section. The components form a fully case bonded system and the two components are separated from each other along the "S" which provides stress relief.

Abstract: The invention relates to a general method of producing progressively burning deterrent-coated powder, more particularly propellant powder for weapons having barrels. According to the method a film-forming, preferably polymerizable deterrent substance is fed to the powder loosely or dispersed in a liquid phase which is thereafter driven off. The invention also relates to a method of giving a deterrent coating to granular powder or powder cut up in to short pieces (so-called tubular powder) in a fluidized bed. Finally, the invention relates to a special deterrent substance in the form of a water-dispersable polyurethane built up on an aliphatic isocyanate and a caprolacton polyester.

Abstract: The invention relates to a process for preparing a body of a rocket propulsion unit comprising a rubber wall forming a chamber which contains a propergol and an outer wall forming reinforcement, characterized in that the following steps are carried out:the rubber chamber is coated with an adhesive agent,the whole is baked at a temperature higher than about 100.degree. C.,the propergol is introduced into the chamber,the outer wall is made by depositing impregnated fibers around the chamber and polymerization at a temperature lower than about 100.degree. C.

Abstract: A mechanical bond between a solid rocket propellant composition and a substrate such as insulation material is provided by a quantity of molded member portions integral with the substrate and protruding from a substrate surface into the cured propellant composition whereby a linerless rocket motor may be provided. A method of effecting such a bond is also disclosed.

Abstract: A method and design are disclosed for the introduction of ammonia gas into he rocket motor gas environment wherein the ammonia gas functions to suppress the flash signature.The firing and pressurization of a sealed container having suppressant vents results in the rupturing of one or more seals for the container containing clathrate means from which adsorbed liquid or gaseus ammonia is boiled out and discharged and mixed with combustion gases prior to being discharged through the exhaust nozzle of a rocket motor.The design for the container for containing clathrate means include as part of one embodiment a toroidal shaped container for installing within the rocket motor exhaust nozzle wherein the container functions as the throat of the exhaust nozzle of the rocket motor. Other embodiments feature the clathrate means in a sealed container which additionally houses the ignitor means.

Abstract: An adjustable restraint assembly connectable between a dome portion of a solid propellant rocket motor casing and a rigid base or support, for use during the curing of a propellant in the casing. The assembly includes an upper attach bracket connectable to the dome portion, a lower attach bracket connectable to a rigid base, upper and lower flanges connected to the upper and lower brackets, respectively, and an adjustable threaded turnbuckle-like member connected between the flanges. The assembly is used to establish a maximum net downward deflection of the dome portion upon maximum pressurization of the uncured propellant in the motor casing and is thereafter adjusted at various times during the curing process to reduce and ultimately eliminate the deflection in increments to thereby improve the bond between the grains of the cured propellant and the casing in the region of the forward dome.

Abstract: A solid propellant acts in a chamber to propel a member such as a rocket, the chamber being closed to the atmosphere. The propellant provides high density-impulses and, when combusted, produces end products which do not have any deleterious effects. The propellant preferably includes a binder having hydrocarbon linkages and a lead compound oxidizer formed from an inorganic lead oxidizer salt. This oxidizer has dense characteristics and stable properties at ambient temperatures and through a particular range of temperatures above ambient. The propellant also includes a fuel additive, preferably a metal such as aluminum, having properties of being oxidized by the oxidizer and of reducing the lead. The fuel additive has a percentage by weight relative to the lead compound oxidizer to reduce the lead to lead oxide. The fuel additive is preferably included in the propellant in the range to approximately twenty percent (20%) by weight and is preferably in a fragmentary form.

Abstract: A roll calendered sheet propellant features thin sheets of solid propellant which have been consolidated by the calendering operation. After calendering, the sheet propellant is roll-printed or "coined" with a pattern, which forms propellant flakes after ignition in a gun/cannon system. The printed pattern consists of a designed flake geometry, for example, of contiguous diamond or square shapes providing flame communicating paths therebetween. The formation of propellant flakes depends upon a characteristic of propellants, specifically that they burn faster in zones of high residual stress. By varying the design of the roll printer, the printed pattern, in a two-sided printed sheet configuration, may include a cut in the pattern of the order of 15 to 40% of the propellant sheet uncut web depth. After roll printing, the propellant may be cut to length and rolled for insertion into a shell or cartridge case.

Abstract: A method of bonding propellant to a rocket motor casing using the nitrene insertion reaction is disclosed.

Abstract: A thin frangible cork barrier conforming to the contour of the burning surface of individual solid propellant grains in a multiple grain rocket motor prevents premature ignition of the protected grain by the heat of combustion of previously ignited adjacent grains and is expelled through the rocket motor nozzle upon ignition of the protected grain. In a second embodiment, the thermal protection afforded by the frangible cork barrier is augmented by bonding to a thermally-protective elastomer layer which is in turn bonded to the propellant grain burning surface. By virtue of the composition and structure of the embodiments, thermal protection is afforded. Upon ignition of a protected grain the thermal barrier breaks up so as to pass readily through the throat of a small motor nozzle.

Abstract: End burning gas generators for use either as propulsion systems or means for generating large volume of gases for various purposes such as the generation of the fuel for a ducted rocket engine, the rapid inflation of air bags for personal protection or recovery of submersed items or the expulsion of projectiles from subsurface launch tubes are currently widely utilized. End burning gas generator grains are ignited at one end of a generally cylindrical charge mounted within a combustion chamber which is fixed with a suitable exhaust means. For many of the applications described above, it is desirable that the gas generator burn in a uniform manner such that a constant volume of gas is generated per unit of time so that the chamber pressure and the mass flow rate of gas remain constant.

Abstract: A solid rocket motor is provided which comprises a rocket case and a centrally ported propellant grain comprising a main portion and a nozzle portion, wherein the main portion is a shaped and cured first propellant and wherein the nozzle portion comprises a shaped and cured second propellant composition having a lower burn rate than the first composition and having a plurality of aromatic amide fibers dispersed therethrough.

Abstract: A method of determining tensile bond strength and lap shear strength betw a liner/insulation material and a propellant composition which is cured to portions of the liner/insulation material.The liner/insulation material is bonded to a propellant composition in a dogbone configuration by positioning a predetermined size of the liner/insulation material in a groove that is constructed in a mold in a transverse direction for a tensile bond strength specimen whereby the propellant is bonded to each side of the exposed liner/insulation material. The lap shear specimen is formed in a mold wherein a predetermined size of the liner/insulation material is longitudinally positioned in a groove that is constructed in a mold.

Abstract: A curvilinear solid propellant gas generator which includes a housing that as a diameter or width that is larger than the length of the gas generator and with a curvilinear solid propellant grain mounted therein to provide a long burning time propellant with a short length housing.

Abstract: A rocket propellant or rocket motor is provided with an insulating layer ween the fuel proper and the inner wall of the housing forming the combustion chamber. The insulating layer is made of a foamed synthetic material. The foaming insulating material is introduced into the housing under pressure after the solid fuel body has been centered in the housing with a spacing between the inner housing wall and the fuel body the front face of which is covered with a synthetic material film for the subsequent removal of the layer of foamed insulating material from the front face of the fuel body. In an alternative method the inner surface of the combustion chamber wall may be coated with a layer of foamed insulating material prior to the introduction of the fuel into the combustion chamber, said layer of foamed insulating material forming a tubular member.

Abstract: Positive rocket motor pressure hull venting in the case of deck fires is vided by placement of thermite masses at spaced locations on the interior of the hull. Small cylindrical masses as well as strip formed masses are employed. The thermite mass includes a small amount of structurally formed aluminum as well as the conventional powdered aluminum.

Abstract: An improved booster construction having a metallic covering with a plural of apertures therein encases a booster charge which, in turn, is encased in a nonmetallic cup having a low temperature melting characteristic permitting the booster charge to expand during thermal cook-off to prevent reaching critical temperature pressure relationships.

Abstract: A gas generating propellant charge which is made by piling explosive powder sheets having a plurality of projections on at least one surface thereof so as to make contact them with each other is excellent in firing characteristics, and the explosive powders in the gas generating propellant charge can be burnt in a short time, thereby generating a large amount of gas.

Abstract: A propellant grain for improved ballistic performance of guns, the grain prising a cylinder of generally hexagonal cross-section being provided with a plurality of perforations, preferably 37, passing therethrough. The perforations are disposed such that the interstitial distance between adjacent perforations is substantially equal and the extrastitial distance between peripheral perforations and the surface of the outer wall is substantially equal to the aforesaid interstitial distance. The novel shape of the solid propellant grain improves ignition and burning characteristics such that higher average pressures are maintained during projectile acceleration without increasing the maximum pressure within the gun barrel.

Abstract: Longitudinal stresses in the explosive grain of a rapidly accelerated high xplosive projectile are absorbed in longitudinal reinforcement members and are transferred therefrom to the casing of the projectile. Transmission of the acceleration load from the grain to the longitudinal reinforcement members may be by friction, adhesive bonding or by area mismatch. A stress decoupling layer in the aft end of the projectile may be employed for matrix stress decoupling.

Abstract: A method of producing pressed rocket propellant with good flash suppression and a high burning velocity, i.e. containing optimal quantities of flash reducing agent and catalysts. The meethod is characterized by the entire quantity of flash reducing agent required in order to achieve the result desired being mixed into a separate quantity of propellant while the entire quantity of catalysts required in order to achieve the result desired is mixed into the remaining quantity of propellant, after which these propellants containing either flash reducing agent or catalysts are converted into an appropriate form and mixed in layers or in its entirety and thereafter pressed into the form desired. In the body of propellant obtained, the flash reducing agent and catalysts will be separated, and will not interfere with each other's function.

Abstract: The invention relates generally to a small model rocket motor. The motor includes a plastic composite propellant, and plastic ablative nozzle, and provides means for producing thrust, a time delay, and a charge to activate external devices of desirable design.

Abstract: An effective method to recover the catalyst material, ferrocene or its deatives, from high burn rate propellants comprises the method which uses compressed gas in the form of a near critical liquid to extract, remove, and recover the specific catalyst material directly from rocket motors or from chunks of cut propellant.The method comprises introducing compressed carbon dioxide into a pressure vessel containing the propellant from which the catalyst material is to be recovered. The carbon dioxide as a near critical liquid (NCL) is circulated within the pressure vessel where extraction of ferrocene or its derivatives directly from the propellant takes place. The NCL with extractibles is transported to a warming and recovery zone where the extractibles are recovered after the carbon dioxide is volatilized and returned for recycling, compressing, and further extracting after being adjusted to a near critical liquid.Analytical data indicates that from 99.

Abstract: A double base propellant grain inhibitor is comprised of a hydroxyl-termied polybutadiene polymer having from 2 to about 3 hydroxyl groups per average molecule and an approximate molecular weight of 2800 to 3600, an inert filler, a cross-linking agent, a thickening agent, an antioxidant, a curative, and a catalyst. When properly applied to the surface of a propellant grain, the inhibitor bond does not weaken with age and the inhibitor produces planar, no-cone grain burning having a constant chamber pressure during the burning of the propellant grain. A 1,4-butylene oxide-type polyether barrier layer consisting of a poly-1,4-butylene oxide diisocyanate with an approximate molecular weight of 850 to 1000, a diol curative, a triol cross-linker, and antioxidant and a cure catalyst can be added between the propellant grain and inhibitor to reduce propellant plasticizer migration.