Abstract: This invention relates to priming compositions for ammunitions containing manganese dioxide as oxidizer agent in the primer mix, and to the rimfire cartridge containing dinol, manganese dioxide, tetrazene and glass.

Abstract: Non-asbestos elastomeric insulation materials for rocket motors are disclosed. The insulation materials comprise 100 parts by weight of a crosslinked elastomer polymer and between about 10 and 100 (preferably 15-75) parts by weight of an organic fiber selected from cotton flock, Sisal and a combination of cotton flock and Sisal. The insulation materials have notable erosion resistance and can be tailored to have thermal, mechanical and other properties of desired character. The organic fiber advantageously functions as a char forming, low density filler. Other ingredients such as silica, phenolic resin, polybutadiene etc. are included to enhance the utility of the insulation materials.

Abstract: This invention relates to a water containing explosive cartridge, of which at least one end face is constituted of a star-shaped crimping closure including an inner lid, and a process for producing the same.

Abstract: A thermal protection device is intended for protecting structures submitted to high temperature and high speed ablative flow in the presence of high frequency vibrations and of the type comprising an armature containing a binder layer. The armature is a fringed meshing comprising a meshed portion submitted to ablative flow and fringes thereon directed to the structure surface to be protected with a predetermined orientation relative to the direction of said flow. Such a device is obtained for example by winding on a mandrel a fringed strip previously impregnated with a polymerizable resin which is polymerized after forming. The device can protect reactor conduits conveying high temperature corrosive gases.

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 single- or multiple-base powder charge for propellants is made up of at least one powder grain in the form of a shaped mass of powder having at least one internal cavity. The diameters of the internal cavities within the powder grains making up the charge are different and at least a portion thereof is smaller than the critical diameter that corresponds to the ignition pressure and that governs the penetration of the ignition flame into the internal cavities. With this arrangement at least a portion of the internal cavities is ignited with a retardation only by gas pressures that rise above the ignition pressure.

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 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 fuel rocket burn rate control apparatus wherein grain preheating energy is supplied to the grain region just ahead of the regressing burn face by optical conductors such as fiber optic filaments that are buried in the grain and dispersed across the grain cross section. The optical conductors receive optical energy from one of several types of electrical-to-optical energy transducers such as a semiconductor laser or an incandescent source; the optical conductors promote coning burn action at the burn face of the rocket and allow control of the burn rate by electrically modified optical signals.

Abstract: The invention is an improved solid propellant grain, wherein the solid prllant grain is structured to provide a programmed method and system for splitting the solid propellant grain at a programmed moment to provide an increase in the burning surface. The programmed-splitting of the solid propellant grain provides improved ballistic performance of guns, which yields a higher muzzle velocity for a given projectile without increasing the maximum pressure exerted on the gun chamber. The improvement consists of embodiments that are a plurality of slits of various configurations through the longitudinal length of each grain of solid propellant. The improvement includes a structure to delay end burning of the grains until the longitudinal exterior surface burns sufficiently to split the grain into a plurality of sections at a programmed moment when the increased burning surface is desired to occur.

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: Inserts for hollow charges, especially for armor-piercing projectiles, are formed with a monocrystalline, unitary structure by melting and directional solidification of a body of the insert material, e.g. copper, in which a shaping member has been provided.

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: 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: Non-asbestos elastomeric insulation materials for rocket motors are disclosed. The insulation materials comprise 100 parts by weight of a crosslinked elastomer polymer and between about 10 and 100 (preferably 15-75) parts by weight of an organic fiber selected from cotton flock, Sisal and a combination of cotton flock and Sisal. The insulation materials have notable erosion resistance and can be tailored to have thermal, mechanical and other properties of desired character. The organic fiber advantageously functions as a char forming, low density filler. Other ingredients such as silica, phenolic resin, polybutadiene etc. are included to enhance the utility of the insulation materials.

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: Described is a pyrotechnic charge as smoke- or combustion charge in the form of separate pressed objects arranged in a case, the improvement comprising the fact that the case (1) for the pressed objects (3) consists of plastic or light metal provided with preset breaking points (2). More specifically, the pyrotechnic charge contains a charge base containing smoke compounds in the form of pressed objects and also contains an igniting charge.

Abstract: Propellant charge, the combustion of which takes place according to at least two thrust modes, and which makes it possible to obtain at least one acceleration phase and one cruising phase of the self-propelled device equipped with this charge.The propellant charge is of the so-called "trumpet block" type with radial combustion from a central channel which has a star-shaped cross-section over a length equal to at least one third of the total length of this charge. In order to obtain at least one dual combustion mode using only a single charge of propellant, that part of the channel which is of star-shaped cross-section possesses at least one zone in which the star of the channel has at least four arms which determine at least two tooth-like sectors of propellant with a large sector angle (A) and at least two tooth-like sectors of propellant with a small sector angle (a), distributed symmetrically relative to the axis of the charge.

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: The burning rate of a composite solid propellant comprising ammonium perchlorate and a fuel binder such as polysulfide, polyurethane or polybutadiene can remarkably be increased by the addition of a small amount of FeOOH. Considering the mechanical properties of the propellant, the maximum amount of FeOOH is preferably limited to 7 Wt % of the toatal of the fuel binder and ammonium perchlorate. It is possible to jointly use FeOOH and Fe.sub.2 O.sub.3 on condition that the weight ratio of FeOOH to Fe.sub.2 O.sub.3 is at least 10:90 and that the total weight of FeOOH and Fe.sub.2 O.sub.3 is in the range from 0.9 to 7% of the total weight of the fuel binder and ammonium perchlorate.

Abstract: An unlined Munroe Effect device for breaching structures in urban terrain. he device is constructed as an unlined, linear, shaped explosive charge which directs an explosive jet into the structure. The shaped charge is formed with a honeycombed substrate of metal in which the substrate interstices are filled with and the substrate is covered by an explosive material. The substrate is embedded in the explosive material. The explosive material and substrate, prior to curing of the explosive material, are formed into an unlined, semi-cylindrical shape to create the explosive jet or Munroe Effect. The device is initiated or detonated with a booster charge.

Abstract: A semi-automatic, semi-continuous method is provided for the manufacture of cast explosive boosters. The method makes us of a mold assembly which is transported through filling, cooling and disassembly stations in a substantially continuous manner with little or no manual intervention. The method is adaptable to the manufacture of sheath/core or multiple layer boosters employing two explosives of different sensitivities. The method results in reduced operating costs and improved safety.

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: An end-burning grain of a solid gas-generating composition which may be a propellant for use in rocket motors, in which an elongate metal heat conductor is embedded to increase mass burning rate by the effect of heat transferred from the hot combustion gas to the unburned gas-generating composition through the heat conductor. The improvement resides in that the heat conductor is constituted of a plurality of relatively thin wires which are loosely twisted together. This heat conductor can produce greater extent of increase in the burning rate and has a mechanical strength sufficient for embedding in a practical grain.

Abstract: A mechanical method of case bonding a solid propellant to a rocket motor e wherein a coating of a liner material is first applied to the internal surface of a rocket motor case. While the liner material is uncured a mechanical structural material selected from wire grid, wire hooks, rubber spikes, steel wool, metal grid, polyamide material, or polypropylene material is embedded in the liner material but allowed to protrude above the liner material. The liner material is allowed to cure, and an uncured propellant composition is cast against the cured liner and allowed to flow around the protruding mechanical structural material. On curing, the propellant composition attaches itself to both the liner and the mechanical structural material. The combination of the liner material, the mechanical reinforcing material, and the propellant composition provides a mechanical reinforcement in the propellant which is held in place with improved tensile adhesion against the rocket motor case wall.

Abstract: A method and improved propellant composition for eliminating secondary mue flash in small and large caliber weapons without the increased smoke production or inhibiting burning characteristics through the step of incorporating a novel microencapsulated organic coolant additive into a conventional propellant composition wherein the microencapsulated coolant will survive the propellant flame zone intact so as to decompose down barrel to cool the bases exiting the weapon barrel. The preferred organic coolant is oxamide microencapsulated within a gelatin wall material and coated with Bakelite.TM..

Abstract: Pyrotechnic charge, with a short combustion time, comprising inclined plates of propellant and deflectors, and a propulsion system using a charge of this type.The pyrotechnic charge is intended especially for use in a propulsion system for acceleration, and it comprises a set of plates of solid propellant, which plates are arranged approximately parallel to one another and provide at least one longitudinal channel for discharging the combustion gases in the direction of the nozzle of the propulsion system. In order to achieve a very high flow rate of gas without causing breakage of the plates of propellant, the plates of propellant (6) are inclined towards the longitudinal channel, and the charge comprises deflectors (5) which are arranged approximately parallel to the plates of propellant and which possess, in a longitudinal cross-section of the charge, a length which is equal to or greater than the length of the plates of propellant.

Abstract: A flexible, adjustable refractory filler (1) is disclosed for filling gaps between ceramic tiles (10, 11) forming the heat shield of a space shuttle vehicle, to protect its aluminum skin (20) during atmospheric re-entry. The easily installed and replaced filler (1) consists essentially of a strip of ceramic cloth (3) coated, at least along both its longitudinal edges (4, 5), with a room temperature vulcanizable silicone rubber compound with a high emittance colored pigment. The filler may have one or more layers (2, 3), as the gap width requires. Preferred materials are basket-weave aluminoborosilicate cloth, and a rubber compounded with silicon tetraboride as the emittance agent and finely divided borosilicate glass containing about 7.5% B.sub.2 O.sub.3 as high temperature binder. The filler cloth strip or tape is cut to proper width and length, inserted into the gap, and fastened with previously applied drops of silicone rubber adhesive.