Abstract: A solid propellant grain for a gas generator such as a missile canister erection actuator. The grain provides a sustain phase followed by a boost phase which may then be followed by another sustain phase. The aft portion of the grain may have the configuration of an end burner to provide the initial sustain phase. The middle portion contains a longitudinally extending cavity in which is disposed a plug for supporting the grain during the initial sustain phase against collapse or cracking. A gap is provided between the plug and the wall of the cavity to provide effective propellant burnign surface area along the cavity wall for the boost phase. The cavity and plug, which terminate at the aft portion, may extend longitudinally through the forward portion of the grain.

Abstract: A method of and apparatus for casting uncured solid propellant in solid propellant rocket motors includes a casting bayonet having annular slits formed in the exit end thereof that improve the fluidity and self-leveling behavior of the uncured propellant. Both of these effects eliminate or reduce the trapping of air in the cast propellant, thus providing a better product.

Abstract: A curable liner for a solid propellent rocket motor includes a radiopaque material uniformly blended therein to provide a sufficient density difference between the propellant and insulator to enhance non-destructive X-ray evaluation of the liner propellant interface. Up to 10% powdered tungsten is added to a liner component mixture prior to incorporation in a rocket motor. Utilizing this radiopaque material in the liner mixture allows detection of previously undetectable voids, disbands or flaws at the liner propellant interface, thereby reducing the potential for failure of the rocket motor during operation.

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 The vacuum needle is then withdrawn, the hole made thereby is sealed, and the templates are removed from the bag.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: 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 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: 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: 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: 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 method of making an elastomer lined composite vessel or portion of such vessel is disclosed. The method comprises causing a thin, tacky ribbon comprising an elastomer (preferably curable) to continuously so encircle a center rotational axis of a mandrel as to adjacently position and tack together integral segments of the ribbon substantially circumferentially relative to this center rotational axis thereby forming a layer of the elastomer about the mandrel; applying a shell comprising filaments and thermosettable resin to the layer of elastomer; curing the thermosettable resin (preferably in stages if the elastomer is curable with a later stage including cure of the elastomer) to provide the vessel or portion of the vessel.

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: A closed urethane cylindrical case includes a mounting base or foot which runs parallel to the axis of the case and is bonded to the surface of the propellant grain of a full head-end-web rocket motor. Contained within the case are one or more spaced tube initiators and concentrically positioned discs or webs of high energy propellant. Flaming gases resulting from actuation of the tube initiators and consequent burning of the propellant wafers are projected over the surface of the rocket motor propellant from a plurality of nozzle ports that are provided in the cylindrical case, in the quadrants thereof adjacent the surface of the rocket motor propellant. Cylindrical case length and the number of tube initiators and propellant wafers including their spacing can be selected as required to achieve a desired mass flow rate.

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 consumable sealed plastic cup containing ignition pellets is assembled into end cap at the forward end of a solid fuel rocket motor with sufficient clearance to allow leak test gas to bypass it and thereby expose the port seals of the through bulkhead initiators for leak checking.

Abstract: An igniter for high-performance rocket motors having a full, head-end web of propellant in the forward end of the motor comprises a closed, rigid pressure vessel having walls which are formed of a consumable filament structure. The igniter includes a hollow cylindrical solid propellant having a high surface grain area which operates at high pressure and is removably attached to a liner that is provided in a cavity in the aft end of the propellant. The liner is machinable with the motor propellant grain thereby facilitating propellant grain cutback if required by a change in mission of the motor. The thrust produced by the igniter neither applies stresses to the motor propellant nor exerts any forces tending to eject it from the cavity.

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: 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: 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.