Including Propellant Support Means Patents (Class 60/255)
  • Patent number: 5388399
    Abstract: An improved rocket motor and a method for its manufacture are characterized by the provision of a thermoplastic elastomer binder in the outer casing, the insulation layer, and the propellant. When the motor is heated to the melting point of the binder, the bondlines between the propellant and insulation and between the insulation and casing are simultaneously fused to form a unitary motor structure.
    Type: Grant
    Filed: March 11, 1992
    Date of Patent: February 14, 1995
    Assignee: Atlantic Research Corporation
    Inventors: Irving E. Figge, James D. Martin
  • Patent number: 5380570
    Abstract: Para-polyphenylene sulfide, a non-composite, ultrahigh-temperature-resist, thermoplastic resin, is employed for the manufacture of interceptor motor cases. The thermoplastic resin, para-polyphenylene sulfide, has a combination of properties which are of particular interest in the fabrication of interceptor rocket motor cases. Para-polyphenylene sulfide in ribbonized forth is wound directly onto the required mandrel and then fused into a solid mass. The fused, solid mass has the properties which enables it to serve as both insulator and motor case material. The manufacture of a combination insulated motor case is achieved by the following method: The equipment, first, involves the fabrication of a breakout mandrel by one of several methods. The para-polyphenylene sulfide is ribbonized by extrusion and wound down on the breakout mandrel to the required thickness and fused into a solid mass by heating to its melt temperature of about 285.degree. C.
    Type: Grant
    Filed: July 6, 1993
    Date of Patent: January 10, 1995
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: David C. Sayles
  • Patent number: 5352312
    Abstract: Rocket motor insulation compositions are provided. An important component of such insulation compositions is a thermoplastic liquid crystal polymer. Such a polymer provides an ablative insulation which has good performance characteristics during operation of the rocket motor. One such thermoplastic liquid crystal polymer is a wholly aromatic polyester known as VECTRA.RTM.. The insulation may also include fillers such as fibrous fillers and particulate fillers. Typical fibrous fillers include glass or carbon fibers. Typical particulate fillers include materials such as silica, alumina, powdered coal, and the like.
    Type: Grant
    Filed: August 6, 1992
    Date of Patent: October 4, 1994
    Assignee: Thiokol Corporation
    Inventor: David G. Guillot
  • Patent number: 5341638
    Abstract: A composite structure for rocket motors includes a longitudinal element of the composite structure, which is an assembly of segments of clamshell or barrel stave form. The element is held in place by a circumferential element, which is a composite overwrap of reinforcing fibers in a resin matrix. The matrix may be thermoplastic or thermosetting. The reinforcing fiber being high strength polyolefin thereby providing the rocket motor with insensitive munitions capability.
    Type: Grant
    Filed: March 9, 1992
    Date of Patent: August 30, 1994
    Assignee: Thiokol Corporation
    Inventors: Frederick W. Van Name, Michael A. Gerace, Victor Singer, Brendan M. Walsh
  • Patent number: 5339625
    Abstract: A hybrid rocket motor includes a solid propellant fuel grain component which incorporates fuel strengthening agents or mechanical retention devices. In one embodiment, the hybrid fuel formulation is a modified elastomeric polyurethane reaction product based on a liquid hydroxyl-terminated homopolymer of butadiene. A reinforcing agent is added which increases the tensile and tear strength of the grain by 50%. By so strengthening the grain, separation of the grain during the last portion of the burn is minimized. In a second exemplary embodiment, mechanical web stiffeners are provided in the form of a core configuration about which the fuel grain is cast. The web stiffeners are in the form of an open tetrahexagonal truss structure which mechanically traps and adheres to the fuel and becomes an integral part of the fuel grain geometry. In both embodiments, the integrity of the webs is maintained throughout the burn.
    Type: Grant
    Filed: December 4, 1992
    Date of Patent: August 23, 1994
    Assignee: American Rocket Company
    Inventors: Bevin C. McKinney, Roy J. Kniffen, Jr.
  • Patent number: 5309712
    Abstract: A rocket motor has a reloadable, reusable hollow casing which contains solid fuel, a nozzle and preferably a delay ignition cartridge and ejection charge. A nozzle gasket holds the nozzle in place at the exhaust end of the casing and a delay cartridge gasket holds the delay cartridge and ejection charge in place at the ejection charge end of the casing. The gaskets fit loosely against the casing and are deformable so that upon ignition they are pressed outward against removable flanges at each end of the casing to create a seal against the casing.
    Type: Grant
    Filed: May 3, 1991
    Date of Patent: May 10, 1994
    Inventor: Charles J. Mund, Jr.
  • Patent number: 5305601
    Abstract: A fiber/resin composite whose resin phase is formed by at least initial actinic radiation curing of a resin composition comprising an actinic radiation curable first resin component and a second resin component which is non-cured under curing conditions effective for the first resin component. The actinic radiation exposure of the fiber/resin composition effects curing of the first resin component to immobilize the composite and impart structural integrity thereto, whereby the composite may be handled, packaged, or further processed. Filament wound, braided, and pultruded articles are described, together with associated methods for forming such articles by filament winding, braiding and pultrusion. As a specific embodiment, a solid fuel rocket motor is disclosed comprising a solid fuel body in a filament wound fiber-resin composite casing formed by filament winding of the solid fuel body with resin-impregnated filament or rovings thereof.
    Type: Grant
    Filed: August 12, 1992
    Date of Patent: April 26, 1994
    Assignee: Loctite Corporation
    Inventors: Kieran F. Drain, Larry A. Nativi, Richard T. Thompson
  • Patent number: 5280706
    Abstract: A composite/metal hybrid rocket motor case made by rolling sheets of continuous, unidirectional fiber reinforcement pre-impregnated with an uncured, thermoset or thermoplastic resin about the mandrel using a tube rolling machine to form a liner having discontinuous layers of fiber reinforcement. The liner is inserted into a metal shell configured with elongated slots. A mold is placed around the shell with a bladder placed within the liner. The bladder within the mold is then pressurized to force the liner against the metal shell while the contents of the mold are heated. As the liner cures, it bonds to the shell. Fins, launch lugs, domes and bulkheads may be attached to the metal shell by known attachment methods.
    Type: Grant
    Filed: June 25, 1992
    Date of Patent: January 25, 1994
    Assignee: Thiokol Corporation
    Inventor: James A. Yorgason
  • Patent number: 5227208
    Abstract: A method is disclosed for forming an integrally wound joint structure with filament wound composite structure at an adjacent end of the integrally wound joint structure and having means for attaching said integrally wound joint structure to another structure provided at other end of said joint structure. The joint structure includes filament winding over a joint tube or joint solid with appropriately sized and spaced grooves running circumferentially around the outer surface of the joint structure. A curable resin is employed in filament winding to complete an assembly which is placed in a conventional oven and allowed to cure.
    Type: Grant
    Filed: June 10, 1992
    Date of Patent: July 13, 1993
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: Lawrence C. Thongs, Jr.
  • Patent number: 5220783
    Abstract: A process of forming an igniter in an aft-end assembly for a solid rocket motor, the assembly having an internal cavity and comprising at least one element selected from the group consisting of a nozzle, a blast tube and an exit cone, which process comprises positioning an ignition package comprising pyrotechnic material and an initiator in the assembly cavity and causing a polymer foam to expand and cure in the assembly cavity and around the ignition package, so as to embed and secure the ignition package, form an aft closure, and for the igniter as an integral portion of the assembly.
    Type: Grant
    Filed: September 20, 1991
    Date of Patent: June 22, 1993
    Assignee: Hercules Incorporated
    Inventors: Charles C. Cherry, Raymond E. Wiechering
  • Patent number: 5212946
    Abstract: A modular reusable rocket motor combined with reusable, disposable, and expendable assemblies to provide customized operational characteristics for a rocket launched therewith.
    Type: Grant
    Filed: May 20, 1991
    Date of Patent: May 25, 1993
    Assignee: Industrial Solid Propulsion
    Inventors: Paul C. Hans, Gary C. Rosenfield, Daniel H. Meyer
  • Patent number: 5151145
    Abstract: A liner for a rocket motor case or other filament wound vessel includes a relatively thin casing. Reinforcements are formed integrally with the interior of the casing whereby the liner can be used as a mandrel for filament winding or applying composite material to the rocket motor case or other vessel. Interfacing is formed integrally with the interior of the casing for positioning and restraining propellant, hardware or other components within the liner.
    Type: Grant
    Filed: January 2, 1990
    Date of Patent: September 29, 1992
    Inventor: Alvin R. Cederberg
  • Patent number: 5127223
    Abstract: A linerless rocket motor is provided by the bonding of a reticulated support structure, which is embedded in an homogenous mass of propellant material including an oxidant, to the inner wall of the rocket motor case. An inexpensive, safe, and easy to manufacture igniter is comprised of an homogeneous mass of propellant material including an oxidant and a reticulated support structure embedded therein. A light weight, high crush strength, and high strain capability sliver for a rocket motor comprises a block of inert material and a reticulated support structure of carbon, graphite, or a non-combustible material embedded therein. A rocket motor is prevented from accidental propulsion during a fire by attaching a propellant block to the outer side of the rocket motor base. The propellant block burns and produces heat during the fire to weaken the motor case so that pressure resulting from burning of propellant in the rocket motor will burst a hole in the rocket motor case to relive the pressure.
    Type: Grant
    Filed: August 7, 1989
    Date of Patent: July 7, 1992
    Assignee: Thiokol Corporation
    Inventors: James O. Hightower, Jr., Tomio Sato
  • Patent number: 5085725
    Abstract: The trimer of 1,6-hexanediisocyanate, which has the chemical name in acconce with (International Union of Pure and Applied Chemistry) (IUPAC) nomenclature of 7-aza-8-oxo-7[1-isocyanato-6-oxohexyl]pentadecanediisocyanate, is employed in a method of chemical bonding of solid propellant grains to the internal insulation of an interceptor motor. Both the propellant composition and the insulation are chemically reactive with the trimmer identified hereinabove. The method comprises providing a solid propellant rocket motor case having the internal insulation installed therein. Following degreasing of the insulation outer surface, the trimer identified hereinabove is spray coated onto the insulation, and the solid propellant composition is placed onto the trimer. A chemical bond is formed between the propellant and the trimer and the insulation to achieve the chemical bonding of an isocyanate curable solid propellant composition to the internal insulation.
    Type: Grant
    Filed: August 6, 1990
    Date of Patent: February 4, 1992
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: David C. Sayles
  • Patent number: 5060470
    Abstract: A rocket motor or other gas generator the case of which is ventable at a predetermined temperature substantially greater than the ambient temperature range for storage and operation thereof and substantially less than the auto-ignition temperature of gas generant material contained therein so as to prevent catastrophic propulsion or burst in case of fire. The venting is provided by memory metal members which are interleaved between plies of matrix-impregnated fibrous material in the case and which have a transformation temperature which is substantially higher than the ambient temperature range and substantially lower than the auto-ignition temperature and characterized by a change in shape when heated to a temperature above the transformation temperature.
    Type: Grant
    Filed: May 22, 1990
    Date of Patent: October 29, 1991
    Assignee: Thiokol Corporation
    Inventor: Frederick W. VanName
  • Patent number: 5044154
    Abstract: A rocket motor having case segments which are attached together. A retaining member extends circumferentially thereabout to maintain attachment of the segments together. The retaining member is characterized by sensitivity to a predetermined temperature greater than ambient temperature and less than the ignition temperature of propellant material in the rocket motor to lose strength whereby the retaining member is released and the rocket motor may safely be rendered non-propulsive during a hazard such as a fuel fire or slow cook-off.
    Type: Grant
    Filed: November 27, 1989
    Date of Patent: September 3, 1991
    Assignee: Thiokol Corporation
    Inventors: R. Hill English, Jr., Hermann L. Miskelly, Jr.
  • Patent number: 5038561
    Abstract: A thermal insulator for a rocket motor body comprises a member adapted to be fitted as a sleeve on the outer surface of the body the member comprising a composite of cork having on its outer surface a layer of fibre reinforced polymeric material wherein a substantial proportion of the fibre reinforcement comprises fibres of low-conducting material.
    Type: Grant
    Filed: August 28, 1989
    Date of Patent: August 13, 1991
    Assignee: Royal Ordnance plc
    Inventor: Michael J. Chase
  • Patent number: 5032201
    Abstract: Sectors of tubes are adhesively fixed around a prefabricated propellant, the sectors being juxtaposed edge to edge to constitute a cylindrical tube, and a winding is formed around the tube at least in circumferential direction. The front and rear walls which are equipped with a seating and a tuyere, can be joined to the tubular structure formed by the tube sectors, by adhesive means on the inside of that structure, or as a variant, by means of a helical winding formed simultaneously on the wall and on the tubular structure.
    Type: Grant
    Filed: April 28, 1989
    Date of Patent: July 16, 1991
    Assignee: Societe Anonyme: Societe Europeenne de Propulsion
    Inventor: Dino Crapiz
  • Patent number: 4999997
    Abstract: A radial pulse rocket motor having a nozzle at the aft end includes longitudinally spaced hollow boost and sustain propellant grains in the combustion chamber thereof with an elongated tubular thermal barrier covering substantially the whole of the interior surface of the sustain grain to enable the production of separate boost and sustain pulses. At the forward end of the motor, mounted within a reentrant motor bulkhead position, is a multiple pulse arm-fire device which, when commanded, produces an igniting signal that is transmitted to a boost igniter for igniting the boost grain and a subsequent igniting signal that is transmitted to a sustain igniter for igniting the sustain grain. The sustain igniter is positioned in surrounding relation to the motor forward bulkhead reentrant portion, the multiple pulse arm-fire device, and the forward end of the tubular barrier, and comprises a consumable, molded, polyurethane case having two interlocking tubes with a thin 0.10 inch (2.5 mm.
    Type: Grant
    Filed: November 18, 1985
    Date of Patent: March 19, 1991
    Assignee: Thiokol Corporation
    Inventors: Roger A. Grosgebauer, C. Max White
  • Patent number: 4878431
    Abstract: Non-asbestos elastomeric insulating materials for rocket motors are disclosed. The insulating materials are low in density (between about 0.035 and 0.050 lb./cubic inch) and comprise crosslinked elastomeric polymers (100 parts by weight of a crosslinkable elastomeric polymer that is substantially saturated and about 5-50 parts by weight of a crosslinkable, substantially unsaturated, elastomeric polymer) in which are dispersed between about 10 and 100 (preferably 15-75) parts by weight of a char forming organic fiber selected from polyaramide pulps, between 1 and 15 parts by weight of a peroxide crosslinker, and between about 0 and 150 parts by weight organic and/or inorganic particulate. The insulating materials issue little smoke, have notable erosion resistance and can be tailored to have thermal, mechanical and other properties of desired character. Ingredients such as supplemental elastomers, oils and lubricants enhance the processability and green properties such as tack of the insulating materials.
    Type: Grant
    Filed: February 21, 1986
    Date of Patent: November 7, 1989
    Assignee: Hercules Incorporated
    Inventor: Liles G. Herring
  • Patent number: 4866930
    Abstract: A thin membrane of high strength but ductile material is placed over a perforated structural support, thus allowing high pressure on the membrane side of the support to separate one chamber from another. Upon application of pressure through the perforated structural supporting structure, the membrane will collapse allowing communication between chambers. The arrangement has utility in rocket motors and gas generators where discrete impulse segments are desired to be available on command, and may be fabricated in concentric or tandem (series) volumes.
    Type: Grant
    Filed: October 19, 1988
    Date of Patent: September 19, 1989
    Assignee: Morton Thiokol, Inc.
    Inventors: Michael Fling, William R. Puckett
  • Patent number: 4840025
    Abstract: A woven, silicon carbide fiber inner wall forms a combustor liner and a nozzle throat liner, and a woven silicon carbide fiber outer wall is spaced from the inner wall to form a fuel passageway. The silicon carbide fibers are woven to conduct heat from the combustor and nozzle throat to the fuel passageway and thereby provide heat for the endothermic pyrolysis of the fuel in a propulsion system having a rocket casing containing a combustor, propellant injectors, nozzle throat and nozzle. The fuel passageway is adjacent to and surrounds the combustor and nozzle throat, and fuel is endothermically pyrolyzed in the fuel passageway.
    Type: Grant
    Filed: April 15, 1988
    Date of Patent: June 20, 1989
    Assignee: General Electric Company
    Inventor: George A. Coffinberry
  • Patent number: 4836961
    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.
    Type: Grant
    Filed: January 2, 1987
    Date of Patent: June 6, 1989
    Assignee: Morton Thiokol, Inc.
    Inventors: Richard E. Morgan, Charles B. Dye
  • Patent number: 4829765
    Abstract: A segmented rocket motor case includes wedge members for forcing the case segments into position to remove free play at the joint thereof which may otherwise interfere with or upset the missile's guidance system and throw it off target. A lap joint member for such a joint includes a shoulder having a surface for attachment of a membrane seal assembly for a pulsed rocket motor. A through bulkhead initiator communicates from the forward segment via a fitting which extends through the membrane seal assembly with an igniter for the propellant grain within the aft segment to eliminate the necessity of running explosive transfer lines along the outside of the case from a safe and arm device and other controls at the head end of the rocket motor.
    Type: Grant
    Filed: December 27, 1985
    Date of Patent: May 16, 1989
    Assignee: Morton Thiokol, Inc.
    Inventors: Christopher W. Bolieau, Roger A. Grosgebauer
  • Patent number: 4823548
    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.
    Type: Grant
    Filed: September 6, 1988
    Date of Patent: April 25, 1989
    Assignee: Societe Europeenne de Propulsion
    Inventor: Jean Beboux
  • Patent number: 4821511
    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.
    Type: Grant
    Filed: October 31, 1986
    Date of Patent: April 18, 1989
    Assignee: United Technologies Corporation
    Inventors: Bernard R. Felix, Stephen E. Slosarik
  • Patent number: 4766726
    Abstract: A segmented rocket motor case includes wedge members for forcing the case segments into position to remove free play at the joint thereof which may otherwise interfere with or upset the missile's guidance system and throw it off target. A lap joint member for such a joint includes a shoulder having a surface for attachment of a membrane seal assembly for a pulsed rocket motor. A through bulkhead initiator communicates from the forward segment via a fitting which extends through the membrane seal assembly with an igniter for the propellant grain within the aft segment to eliminate the necessity of running explosive transfer lines along the outside of the case from a safe and arm device and other controls at the head end of the rocket motor.
    Type: Grant
    Filed: December 27, 1985
    Date of Patent: August 30, 1988
    Assignee: Morton Thiokol, Inc.
    Inventors: E. Wayne Tackett, Bradley W. Smith, Charles R. Voris
  • Patent number: 4756248
    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
    Type: Grant
    Filed: September 28, 1987
    Date of Patent: July 12, 1988
    Assignee: Morton Thiokol, Inc.
    Inventor: Tomio Sato
  • Patent number: 4711086
    Abstract: A rocket motor insulator of varied thickness with an integrated flap to rce propellant stresses.
    Type: Grant
    Filed: October 24, 1986
    Date of Patent: December 8, 1987
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Darrell L. Offe, R. Gregory Martin
  • Patent number: 4689845
    Abstract: An impulse propulsion unit or pulse-generating impeller mechanism for the lateral acceleration of a projectile, including a hollow cylindrical member, having an outer shell surface which is passed through by nozzles which are peripherally offset relative to each other, and each of which connects into a propellant chamber in the interior of the hollow-cylindrical shell or casing. The propellant chamber is in the shape of an axially elongated section of the hollow wall of a cylinder in which the annular space between the cylindrical inner and outer walls is subdivided through the intermediary of radial separating walls into peripherally neighboring chamber.
    Type: Grant
    Filed: May 21, 1986
    Date of Patent: September 1, 1987
    Assignee: DIEHL GmbH & Co.
    Inventor: Lothar Stessen
  • Patent number: 4654097
    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.
    Type: Grant
    Filed: November 21, 1984
    Date of Patent: March 31, 1987
    Assignee: Societe Europeenne de Propulsion
    Inventor: Dominique Sauvage
  • Patent number: 4577542
    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.
    Type: Grant
    Filed: March 7, 1984
    Date of Patent: March 25, 1986
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: Peter F. O'Driscoll
  • Patent number: 4495764
    Abstract: An integrated three-component insulation wall assembly which can be used by itself as an insulation wall assembly, or which can be incorporated into a solid rocket motor case that is made of material fabricated using conventional layup construction methods, or which can provide the contour stability necessary to allow its functioning as a mandrel for filament-winding a solid rocket motor case, and which can be spliced and reinforced across the splice. The insulation wall assembly comprises, in an integrated condition, an inner wall component (i.e., a flame side wall component) which is laminated from woven reinforcements in an ablative matrix, a middle wall component of non-metallic honeycomb core material, and an outer wall (i.e., a pressure side wall component). The inner wall component provides a fire barrier; the middle wall component provides thermal insulation; and the outer wall component provides structural stability.
    Type: Grant
    Filed: May 26, 1983
    Date of Patent: January 29, 1985
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventor: Clayton C. Gnagy
  • Patent number: 4345427
    Abstract: A solid propellant rocket motor of gas generator of the type having retractable filaments embedded in the propellant for the purpose of controlling the overall thrust or mass flow output is combined with a channeled separator located between the propellant and its casing with the channels open to the combustion chamber. This results in distribution of combustion chamber pressure and temperatures over the exterior of the propellant grain so that distortion of the grain will not occur sufficiently to cause binding or sticking of the filament in their holes in the propellant nor will the holes be enlarged to cause uncontrolled burning between the filament and the hole.
    Type: Grant
    Filed: October 26, 1979
    Date of Patent: August 24, 1982
    Assignee: Thiokol Corporation
    Inventor: Roger H. Whitesides, Jr.
  • Patent number: 4314509
    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.
    Type: Grant
    Filed: December 20, 1979
    Date of Patent: February 9, 1982
    Assignee: Societe Nationale des Poudres et Explosifs
    Inventor: Francis A. Dalet
  • Patent number: 4275657
    Abstract: A pyrotechnic charge for generating gases, for example for the propulsion of an engine, comprising elongate strands of propellant fixed, such as by adhesive or mechanical fastening devices, to at least one band of flexible material which is wound into a spiral having several turns so that each strand of propellant is positioned radially between adjacent turns of the band and lies in an axial plane. The flexible band has an inhibiting effect on the combustion characteristics of the strands of propellant.
    Type: Grant
    Filed: December 12, 1977
    Date of Patent: June 30, 1981
    Assignee: Societe Nationale des Poudres et Explosifs
    Inventor: Francis A. Dallet
  • Patent number: 4187676
    Abstract: A rocket assisted projectile is equipped with a bi-metallic disk which ches shape to compensate for propellant grain growth or shrinkage with change in ambient temperature for maintaining the propellant in a predetermined position within the combustion chamber of the rocket. The disk is located in the combustion chamber forward of the propellant grain and bears against the chamber forward wall and the forward end of the grain. The effective thickness of the disk increases with reduced temperature so that the grain is maintained in solid contact with the base of the projectile to prevent excessive energy absorption upon firing of the projectile.
    Type: Grant
    Filed: March 13, 1978
    Date of Patent: February 12, 1980
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Scott M. O'Neil, Howard H. Payne
  • Patent number: 4120153
    Abstract: 1. In combination with a vessel forming a rocket motor combustion chamber, a rubber-base liner firmly adhering to the interior chamber wall, said rubber-base liner containing between about 2.5 and 30 percent by weight of an inorganic metal salt selected from the group consisting of zinc chromate, barium chromate, zinc phosphate, lead phosphate, potassium phosphate, and mixtures thereof, and a propellant charge substantially filling the lined portion of the chamber, said propellant charge firmly adhering to said liner.
    Type: Grant
    Filed: May 21, 1964
    Date of Patent: October 17, 1978
    Assignee: Olin Corporation
    Inventor: Otto G. Schaffling
  • Patent number: 4118928
    Abstract: A solid propellant grain is held within a rocket motor case in a substantially stress-free manner. The grain is not bonded to the case itself but is bonded to a sleeve which has lateral protrusions or convolutions on its exterior which fit loosely and unattached into similar convolutions in a sleeve bonded to the interior of the case. The sleeve bonded to the propellant is made of a polymer having substantiallythe same elastomeric qualities as the propellant itself so that stresses are not created in the propellant at the bond. Physical shock or distortion of the propellant and thermal expansion or contraction of it create changes in dimension which are absorbed principally by the clearance gap between the convoluted surfaces of the sleeves and therefore substantially no cracking stresses are produced in the propellant itself.
    Type: Grant
    Filed: July 12, 1973
    Date of Patent: October 10, 1978
    Assignee: Thiokol Corporation
    Inventor: Bobby J. Lyles
  • Patent number: 4085584
    Abstract: A barrier system for use in preventing the pre-ignition of second pulse rocket grains in a dual pulse rocket motor. The system includes two double layers of rubber material positioned between the first and second pulse grains with an igniter assembly adjacent to the second grain.
    Type: Grant
    Filed: November 5, 1976
    Date of Patent: April 25, 1978
    Assignee: The United States of America as represented by the Secretary of the Air Force
    Inventors: Roy A. Jones, Marshall W. Mabry
  • Patent number: 3991565
    Abstract: A method of inhibiting combustion of some of the surfaces of a solid propellant charge for or in a rocket motor comprising bonding to said surfaces an elastomeric compound resistant to permeation by combustible components of the charge, and bonding a combustion inhibiting cellulosic derivative to the elastomeric compound, the cellulosic derivative being spaced from said surfaces by the elastomeric compound. The invention also relates to a rocket motor provided with a solid propellant charge inhibited in accordance with the method.
    Type: Grant
    Filed: March 12, 1969
    Date of Patent: November 16, 1976
    Assignee: Imperial Metal Industries (Kynoch) Limited
    Inventors: Stuart Gordon, Geoffrey Ian Evans, Philip Graham Jones
  • Patent number: 3990369
    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.
    Type: Grant
    Filed: March 31, 1975
    Date of Patent: November 9, 1976
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: David C. Sayles
  • Patent number: 3967444
    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.
    Type: Grant
    Filed: September 30, 1974
    Date of Patent: July 6, 1976
    Assignee: The United States of America as represented by the Secretary of the Army
    Inventor: David C. Sayles
  • Patent number: 3965676
    Abstract: 1. In combination with a vessel forming a rocket motor combustion chamber, a rubber-base liner having one surface firmly adhering to the chamber, the opposite surface of said rubber-base liner having a plurality of discrete powder grains partially embedded therein, each of said powder grains having a portion extending from said opposite surface of said rubber-base liner, and a propellant charge substantially filling the lined portion of said chamber, said propellant charge firmly adhering to said liner and enveloping each of said extending portions of said powder grains.
    Type: Grant
    Filed: October 2, 1961
    Date of Patent: June 29, 1976
    Assignee: Olin Corporation
    Inventor: Otto G. Schaffling
  • Patent number: 3962865
    Abstract: A rocket motor construction wherein a convolutely wound propellent strip forms a fuel grain disposed within the rocket motor casing. The fuel grain consists essentially of double base propellent having a plateau or mesa burn characteristic and is shaped to provide a plurality of rearwardly extending blades connected to a convolutely wound margin of the strip. The blades cooperate with each other and with the rocket motor casing to define flow channels between angularly adjacent blades and between adjacent convolutions thereby providing flow channels for combustion product.
    Type: Grant
    Filed: November 16, 1973
    Date of Patent: June 15, 1976
    Assignee: MB Associates
    Inventor: Alan I. McCone, Jr.
  • Patent number: 3961476
    Abstract: A rocket motor is described in which a thin layer of metallic foil or the ke is used between a silicone rubber insulator and an isocyanate cured, hydroxy terminated polybutadiene bound propellant grain to prevent migration of isocyanate into the silicone rubber liner.
    Type: Grant
    Filed: September 11, 1975
    Date of Patent: June 8, 1976
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Bernard Wasserman, Allen T. Robinson
  • Patent number: 3961581
    Abstract: The igniter of the generator is constituted by a deformable plate of solid ropergol bound and fixed on a wooden or metal sleeve mandrel. The plate has open striae parallel to the axis of the support and oriented radially inwards or outwards. The device is useful as an initiator for a solid propergol rocket motor.
    Type: Grant
    Filed: April 30, 1975
    Date of Patent: June 8, 1976
    Assignee: Office National d'Etudes et de Recherches Aerospatiales (O.N.E.R.A.)
    Inventors: Pierre Larue, Pierre Beaumont
  • Patent number: 3958417
    Abstract: A method of suppressing unstable burning in a solid propellant rocket motor comprising combusting a silicone elastomer with burning of the solid propellant to produce a continuous stream of small silica particles which suppress instability.
    Type: Grant
    Filed: November 14, 1967
    Date of Patent: May 25, 1976
    Assignee: Imperial Metal Industries (Kynoch) Limited
    Inventors: Stuart Gordon, Geoffrey Ian Evans, Philip Graham Jones, Stephen William Bell
  • Patent number: 3952506
    Abstract: A solid propellant grain for a rocket is encased in and bonded to an elastomeric insulation sheath. Stresses that would occur between the propellant grain and the rocket case as a result of differential expansion and contraction if the grain were bonded to the case are eliminated by an expandible bearing sleeve that is bonded to the elastomeric sheath. The bearing sleeve is made of noncombustible material and comprises a series of overlapping segments that permit longitudinal motion of the propellant grain relative to the rocket case. The segments may be formed either by separate hoops or by a tape that is wound in a helical pattern on the elastomeric sheath. Since the segments of the sleeve overlap, the rocket case is always protected from hot gases. Hence, the sleeve also functions as a part of the insulation for the rocket case.
    Type: Grant
    Filed: November 7, 1973
    Date of Patent: April 27, 1976
    Assignee: Thiokol Corporation
    Inventor: Albert W. Macbeth
  • Patent number: H1082
    Abstract: A ballistic missile main-stage solid-propellant rocket motor; including a propellant grain configuration tailored to provide required missile ballistic performance, having a center bore, major and minor rear fin slots, and a silver eliminator bore enlargement; utilizing a forward pressure equalizing flap; and designed to accommodate severe operating conditions.
    Type: Grant
    Filed: January 3, 1991
    Date of Patent: August 4, 1992
    Inventor: James W. Andrew