Class / Patent application number | Description | Number of patent applications / Date published |
060253000 | Solid propellant | 38 |
20090139205 | Pourable centerport inhibitor for solid propellant rocket motors - A pourable opaque centerport for solid propellant rocket motors and method for applying the same are disclosed. The pourable centerport inhibitor for solid propellant rocket motors has a curing system that includes a prepolymer and a curing agent. The prepolymer and the curing agent are combined to form a pourable polymeric binder that cures into an amorphous solid. The pourable centerport inhibitor also includes an opaque agent. The pourable centerport inhibitor may also include a plasticizer. The plasticizer, the prepolymer, and the curing agent are preferably the same type that is in the solid propellant with which it will be used in conjunction. | 06-04-2009 |
20100024388 | Flow-Restricting Filter, Solid Propellant Gas Generator and Propulsion System Comprising the Same - The present invention discloses a flow-restricting filter capable of restricting intentionally the flow of the combustion gas from a solid propellant gas generator to an external member (for example, the nozzle) to rise up combustion pressure resulting in increasing a burning rate of the solid propellant and in reducing a burning area of the solid propellant and the overall size of the gas generator. The flow-restricting filter according to the present invention comprises a hollow member having a plurality of through holes formed thereon; and a flow-blocking plate provided at one end of the hollow member to form a space having one closed end and another opened end in the hollow member. | 02-04-2010 |
20100083634 | SOLID FUEL ROCKET, SOLID ROCKET FUEL AND METHOD - A rocket engine for manned or unmanned space flight and atmospheric flight uses an elongated fuel structure that is external to the combustion chamber and that is fed into the combustion chamber during operation of the rocket. The elongated fuel structure includes propellant elements and may include coolant elements and gas generating elements as well. The elongated fuel structure of one embodiment is a ribbon. The ribbon is fed between two opposed wheels of the fuel pump, which seal the engine from escaping gases while permitting the elongated fuel structure to be drawn into the engine. The opposed wheels may serve to activate the gas generating elements, so that gas pressure generated thereby drives the propellant elements into the combustion chamber of the rocket engine. The activation of the gas generating elements also provides coolant to the engine from the coolant elements, in one embodiment. | 04-08-2010 |
20100175367 | PROPELLANT DEVICE OF ENHANCED PERFORMANCE - The present invention relates to the field of propellant devices and more particularly to the propellant devices used in weapon systems and munitions. The invention has the two advantages of minimizing the risk associated with accidental attack to which propellant devices may be exposed thanks to the filling of the central channel commonly provided along the core of the cylindrical explosive charge and of greatly increasing the effectiveness of these propellant charges by the use of explosive materials having a very high burn rate. | 07-15-2010 |
20100251694 | Solid composite propellants and methods of making propellants - Solid composite propellants are provided that include a matrix comprising an energetic oxidizer and a binder. A multi-layered reactive thin film is provided in the matrix. The reactive thin film includes metal and inorganic oxidizer. Methods of making the solid composite propellants are also provided. | 10-07-2010 |
20100251695 | ROCKET ENGINE FOR USE WITH AERODYNAMIC FUEL RIBBON, AND FUEL RIBBON FOR ROCKET AND METHOD - A rocket engine for manned or unmanned space flight and atmospheric flight uses an elongated fuel structure that is external to the combustion chamber and that is fed into the combustion chamber during operation of the rocket. The elongated fuel structure includes propellant elements and may include coolant elements as well. The elongated fuel structure of one embodiment is a ribbon and a wide ribbon may be formed of plural side-by-side ribbon sections. The wide ribbon is cut into separate ribbon sections and is fed between two opposed pinion gears of a fuel injector. The fuel injector has multiple pairs of opposed pinion gears forming multiple stages of the injector, which seal the engine from escaping gases while permitting the elongated fuel structure to be drawn into the engine. The injector has a cutting wheel at the outlet to cut open the coolant and propellant bodies in the ribbon. The propellant ribbon has an outer slow burning layer and an inner fast burning layer. Gas pressure generated by burning the propellant in the combustion chamber of the rocket engine drives the engine. The coolant to the engine is provided from the coolant elements. | 10-07-2010 |
20100281850 | Buried radial flow stereolithographic rocket motor - A hybrid rocket motor is manufactured by photopolymerizing the solid fuel grain in a stereolithography method, wherein fuel grains in a plastic matrix are deposited in layers for building a solid fuel rocket body in three dimensions for improved performance and for a compact design, the hybrid rocket motor including buried radial channels for defining a desired burn profile including the oxidizer to fuel burn ratio. | 11-11-2010 |
20110041475 | ELASTOMER STRUCTURES, ROCKET MOTORS INCLUDING ELASTOMER STRUCTURES AND METHODS OF FORMING STRUCTURES FROM LAYERED VISCOELASTIC MATERIALS - Methods of forming structures from layered viscoelastic materials are disclosed. In some embodiments, such methods may include covering at least a portion of a first viscoelastic material layer disposed on a substrate with a portion of at least a second viscoelastic material layer and containing a quantity of gas within a space defined between a portion of the substrate, a portion of the first viscoelastic material layer and a portion of the second viscoelastic material layer. The methods may further include forming at least one discrete fluid path between the defined space containing the quantity of gas and the vacuum, and removing at least a portion of the quantity of gas from the defined space through the at least one discrete fluid path. Additionally, elastomer structures comprising at least one void defined therein, the at least one void exhibiting at least a partial vacuum, are disclosed. | 02-24-2011 |
20110192136 | SOLID-PROPELLANT MOTOR - A solid-propellant motor includes an outer casing and a combustion chamber which is disposed within the outer casing. In order to simplify the attachment of fittings, the combustion chamber is in the form of a separate component, which is separate from the outer casing. | 08-11-2011 |
20110314791 | METHOD FOR COMBUSTION SYSTEM - A method of fabricating a combustion system includes cold depositing a starting material onto a substrate as a solid metal fuel to produce a combustion structure. | 12-29-2011 |
20120006001 | SOLID PROPELLANT ROCKET MOTORS EMPLOYING TUNGSTEN ALLOY BURST DISCS AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a solid propellant rocket motor are provided. In one embodiment, the solid propellant rocket motor includes a pressure vessel having a cavity therein, a solid propellant disposed within the cavity, a nozzle fluidly coupled to the cavity, and a tungsten alloy burst disc positioned proximate the nozzle. The tungsten alloy burst disc is configured to block gas flow through the nozzle when the tungsten alloy burst disc is intact and to fragment at a predetermined burst pressure. Embodiments of a method are further provided for manufacturing a burst disc. In one embodiment, the method comprises the step of forming a burst disc from a tungsten alloy. Embodiments of a burst disc are still further provided. In one embodiment, the burst disc includes an outer annular portion, and a central portion comprising a tungsten alloy. | 01-12-2012 |
20120042629 | Method And Plant For The Production Of A Casing For A Solid-Propellant Engine, And Casing Made According To Said Method - A casing of a solid-propellant engine comprising a core and a layer of elastomeric material, set as coating for at least part of the core to provide a thermal protection of the core itself is obtained by: inserting the core in a forming mould so as to make within the mould two annular chambers separated from one another by the core; forming a strand of elastomeric material; obtaining a defined portion of elastomeric material by cutting the strand transversely to size in an external environment; and injecting the cut portion of elastomeric material simultaneously within both of the annular chambers. | 02-23-2012 |
20120079807 | METHOD FOR PRODUCING SOLID COMPOSITE ALUMINIZED PROPELLANTS, AND SOLID COMPOSITE ALUMINIZED PROPELLANTS - The main subjects of the present invention are:
| 04-05-2012 |
20140109551 | SOLID CHEMICAL ROCKET PROPULSION SYSTEM - A solid chemical rocket propulsion system includes a solid fuel and a solid oxidizer that is physically separated from the solid fuel and is not mixed with solid fuel while the rocket is initially at rest. | 04-24-2014 |
20140109552 | In-Flight Attitude Control and Direct Thrust Flight Control System of a Vehicle and Craft Comprising Such a System - A system for in-flight attitude control and side-force steering includes a thruster body and a plurality of valves capable of generating side thrusts put into communication with the thruster body. The valves are arranged in two sets of valves spaced apart from each other towards the front and towards the rear of the thruster body in substantially symmetrical manner relative to the center of gravity of the vehicle situated on a longitudinal axis (A) of the vehicle. Each set comprises a first pair of valves generating thrust in opposite directions along axes that are not in alignment and are parallel to a first axis, and a second pair of valves generating thrust in opposite directions along axes that are not aligned and are parallel to a second axis. The first and second axes are distinct and perpendicular to the longitudinal axis of the vehicle. | 04-24-2014 |
20140130480 | STRAIN MEASUREMENT DEVICE, A SOLID ROCKET MOTOR INCLUDING SAME, AND RELATED METHODS - A strain measurement device includes a reference material, and a displacement sensor configured to detect relative changes in distance between the sensor and the reference material. At least one of the displacement sensor and the reference material is coupled with a pre-cured elastomeric material. The displacement sensor generates a data signal to a processor that is configured to determine a strain of another elastomeric material based at least in part on the data signal received from the sensor. A displacement sensor and a reference material may be positioned within an elastomeric material within a casing of a solid rocket motor for determining strain experienced by the elastomeric material, such as the propellant of the solid rocket motor. A method includes installing a sensor of an elastomeric material. Another method includes determining strain of an elastomeric material of a solid rocket motor. | 05-15-2014 |
20140260184 | PRECURSOR FORMULATIONS FOR A LINER, A ROCKET MOTOR INCLUDING THE LINER, AND RELATED METHODS - A precursor formulation of a liner comprising a polymer and at least two curatives. One of the at least two curatives comprises a more reactive curative and the other of the at least two curatives comprises a less reactive curative. The more reactive curative is formulated to crosslink the polymer. A method of lining a rocket motor is also disclosed, as is a rocket motor including the liner. | 09-18-2014 |
20140260185 | PRECURSOR FORMULATIONS FOR AN ENERGETIC COMPOSITION INCLUDING HIGH SURFACE AREA AMORPHOUS CARBON BLACK - A precursor formulation of an energetic composition with improved electrostatic charge dissipation, including an amorphous carbon black having a specific surface area of at least about 1,200 m | 09-18-2014 |
20150291483 | PROPELLANT WITH EXTENDED STORAGE LIFE - A propellant includes a binder system that has a polybutadiene component, a polytetrahydrofuran component, and an anti-oxidant component. In an example, the propellant includes a solid oxidizer, a solid fuel, and a binder system that holds the solid oxidizer and the solid fuel together. The binder system includes a polybutadiene component, a hydrocarbon diluent component of a higher level of saturation than the polybutadiene component, and an anti-oxidant component. | 10-15-2015 |
20150361923 | Rocket Motors and Their Use - Apparatus, methods and computer programs are provided. In one example, an apparatus is a rocket motor, comprising: a casing having a length dimension, a width dimension and a depth dimension, wherein the length dimension is greater than the width dimension and greater than the depth dimension; and propellant, located inside the casing, arranged to generate a force in a direction that is substantially perpendicular to the length dimension of the casing. | 12-17-2015 |
060254000 | Including means to terminate or regulate motive fluid production | 5 |
20080216462 | SOLID PROPELLANT BURN RATE, PROPELLANT GAS FLOW RATE, AND PROPELLANT GAS PRESSURE PULSE GENERATION CONTROL SYSTEM AND METHOD - Systems and methods of controlling solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and propellant gas flow rate, rely on pulse width modulation of a control valve duty cycle. A control valve that is movable between a closed position and a full-open position is disposed downstream of, and in fluid communication with, a solid propellant gas generator. The solid propellant in the solid propellant gas generator is ignited, to thereby generate propellant gas. The control valve is moved between the closed position and the full-open position at an operating frequency and with a valve duty cycle. The valve duty cycle is the ratio of a time the control valve is in the full-open position to a time it takes the valve to complete one movement cycle at the operating frequency. The valve duty cycle is controlled to attain a desired solid propellant burn rate, propellant gas pressure, propellant gas pressure pulse shape, and/or propellant gas flow rate. | 09-11-2008 |
20090211227 | Hydroxyl Amine Based Staged Combustion Hybrid Rocket Motor - A new rocket motor assembly configuration is disclosed. Amine based oxidizer is decomposed in the presence of a metallic catalyst to generate an oxygen rich hot gas stream. The hot gas stream is used to trigger a Magnesium based solid fuel in the combustion chamber. The thrust of the rocket motor may be regulated at multiple points. This design thus offers an IM compliant, thrust-adjustable rocket motor that is of a low hazard classification without compromising its performance. | 08-27-2009 |
20110167794 | Multi-Functional Pulse-Divided Rocket - A multi-pulse rocket is equipped with a thermally insulating barrier that serves as a rupture disk or a movable plug or plate separating staged propellant grains. When a rupture disk it used, the disk can be equipped with a pyrotechnic actuator to weaken the disk upon command, enabling the propellant grain on the fore side of the disk to burst the disk at a relatively low pressure when ignition of the propellant grain is needed for additional thrust. Rupturing of the disk can also be controlled by attitude maneuvering ports on the fore side of the barrier whose open or closed conditions are controlled by independently operable closures. When a movable plug is used, the plug is movable between a closed position separating rocket chamber into subchambers isolating the propellant grains from each other and an open position allowing the flow of combustion gas between the two subchambers to achieve additional axial thrust. In all cases, the barrier when intact serves to contain both propellant grains regardless of whether one or both is ignited. The propellant grain on the fore side of the barrier can thus be used for either axial thrust augmentation or for attitude maneuvering. | 07-14-2011 |
20110167795 | NANOTHERMITE THRUSTERS WITH A NANOTHERMITE PROPELLANT - In various embodiments, the present disclosure provides a thruster that utilizes a nanothermite material as a propellant. The thruster generally includes a body having at least one sidewall and a bottom wall that define a propellant chamber having a closed repulsion end and an opposing open exhaust end. The thruster additionally includes a nanothermite propellant configured within the propellant chamber to have a selected density that dictates a reaction propagation rate of the nanothermite propellant such that the reaction propagation rate will have a selected one of two distinctly different force-time profiles. | 07-14-2011 |
20140338306 | Device for Burning Off Propellants Or Explosive Substances - The invention relates to a device for burning off propellants or explosive substances, which has an activation temperature that lies below the spontaneous ignition temperature of the propellant or explosive substance. The device ( | 11-20-2014 |
060255000 | Including propellant support means | 6 |
20090205313 | Fast Response Solid Fuel Rocket Motor - There is disclosed a solid fuel rocket motor which may include a grain disposed within a case. Prior to ignition, a burnable surface of the grain may be defined, at least in part, by a non-circular center perforation. The interior surface of the case may conform to the expected shape of the burnable surface of the grain at a predetermined time after ignition. | 08-20-2009 |
20090235640 | Pellet Loaded Attitude Control Rocket Motor - There is disclosed a solid fuel rocket motor which may include a case and a nozzle coupled to the case. A plurality of fuel pellets may be disposed within the case. An igniter may be disposed to ignite at least a portion of the fuel pellets. A pellet retainer may be positioned within the case to retain the plurality of fuel pellets within the case. The pellet retainer may be perforated to allow exhaust gases to flow from the ignited fuel pellets to the nozzle while preventing unburned fuel pellets from being expelled through the nozzle | 09-24-2009 |
20120060468 | ADDITIVE MANUFACTURED PROPULSION SYSTEM - Propulsion systems and method for making a propulsion system include additively manufacturing a casing body into a single-piece structure having no bonded or bolted joints. The casing body defines a combustion chamber therein and is at least partially composed of a material useful as a solid rocket fuel and capable of being consumed during combustion. Other embodiments are also described. | 03-15-2012 |
20120117941 | FLIGHT VEHICLES INCLUDING ELECTRICALLY-INTERCONNECTIVE SUPPORT STRUCTURES AND METHODS FOR THE MANUFACTURE THEREOF - Embodiments of a flight vehicle are provided, as are embodiments of a method for manufacturing a flight vehicle. In one embodiment, the flight vehicle includes a solid-propellant rocket motor, control circuitry, and an electrically-interconnective support structure. The electrically-interconnective support structure includes a load-bearing frame and a plurality of electrical conductors embedded within the load-bearing frame. The solid-propellant rocket motor is mounted to the load-bearing frame, and the plurality of electrical conductors embedded within the frame electrically couples the solid-propellant rocket motor to the control circuitry. | 05-17-2012 |
20130031888 | Systems, Methods, and Apparatus for Providing a Multi-Fuel Hybrid Rocket Motor - Certain embodiments of the invention may include systems, methods, and apparatus for providing a multi-fuel hybrid rocket motor. According to an example embodiment of the invention, a method is provided for producing a multi-fuel hybrid motor. The method can include forming a body, where the body includes one or more intake ports; one or more exit nozzles; one or more channels connecting the one or more intake ports with the one or more exit nozzles; and a plurality of cavities comprising segment walls in communication with the one or more channels. The method also includes depositing a propellant fuel within the plurality of cavities, wherein at least a portion of the propellant fuel is exposed to the one or more channels and wherein the propellant fuel has a higher burn consumption rate than the segment walls. | 02-07-2013 |
20130042596 | Systems and Methods for Fabricating Hybrid Rocket Fuel Motor Fuel Grains - Embodiments of the invention relate to systems and methods for fabricating hybrid rocket motor fuel grains. In one embodiment, a method for fabricating a rocket motor fuel grain can be provided. The method can include providing a platform operable to support a rocket motor fuel grain during fabrication. The method can also include disposing at least one fuel material onto the platform to form a material layer. Further, the method can include successively disposing additional fuel material onto the material layer in small amounts, wherein the rocket motor fuel grain is formed on the platform. | 02-21-2013 |
060256000 | Including ignition means | 7 |
20090139206 | Dual-mode chemical-electric thrusters for spacecraft - Spacecraft thrusters capable of dual-mode operation, and a method of applying s propulsion to a spacecraft using a dual-mode thruster are provided. In one embodiment, the thrusters of the current invention can operate as a chemical motor to provide high thrust and low propellant exhaust velocity to achieve fast maneuverability, or as an electric propulsion thruster to provide low thrust and high exhaust velocity to perform maneuvers with a minimal amount of propellant. | 06-04-2009 |
20100011742 | Rocket Motor Containing Multiple Pellet Cells - A rocket motor may include a case, a plurality of pellet cells disposed within the case, an igniter disposed to ignite at least one of the pellet cells, and a nozzle coupled to the case. Each pellet cell may contain a corresponding plurality of propellant pellets. | 01-21-2010 |
20100307131 | Cartridge-Loaded Rocket Motor with Castellated Grain Segments - A solid fuel rocket motor, a castellated propellant cartridge and a method of controlling a pressure differential in a cartridge-loaded rocket motor are disclosed. The rocket motor may include a housing having an inside surface, a plurality of propellant cartridges disposed within the housing, an igniter disposed to ignite propellant material within the propellant cartridges, and a nozzle disposed to exhaust combustion gases out of the housing. At least some of the propellant cartridges may be castellated propellant cartridges. | 12-09-2010 |
20130019587 | THRUSTER DEVICES AND METHODS OF MAKING THRUSTER DEVICES FOR USE WITH THRUST VECTOR CONTROL SYSTEMS - Thruster devices for use with a lateral thrust module and/or a flight body are adapted to achieve short action times with relatively slow burning propellant materials. Such thruster devices include a combustion chamber with a plurality of propellant grains disposed therein. At least some of the plurality of propellant grains are formed into a selected shape. Methods of making thruster devices include forming a housing comprising a first longitudinal end and an opposing second longitudinal end. The housing is formed to define a combustion chamber. A plurality of propellant grains are disposed in the combustion chamber of the housing, where each propellant grain comprises a selected shape. An igniter is coupled to the housing, which igniter is adapted to initiate a combustion of the plurality of propellant grains during deployment of the thruster device. | 01-24-2013 |
20130111874 | Pulse Rocket Motor - A pulse rocket motor has a hollow cylinder-like first grain situated in a rear section of a pressure vessel; a first igniter for igniting the first grain; a hollow cylinder-like second grain situated in a front section of the pressure vessel; a second igniter for igniting the second grain; and a dividing sheet member that covers the second grain within the pressure vessel. The dividing sheet member includes a dividing sheet expanding at least along the inner circumferential surface of the second grain and holders formed integrally with the dividing sheet at both ends of the dividing sheet by cure adhesion and attached to the pressure vessel. The dividing sheet includes a brittle portion that expands along the inner circumferential surface of the second grain through a rear end face of the second grain and is more brittle than other portions. | 05-09-2013 |
20130118147 | TWO-PULSE ROCKET MOTOR - In the two-pulse rocket motor in accordance with the present invention, the second propellant is set outside of the first propellant in a motor case, and the inner surface of the first propellant is exposed throughout the almost entire length in the axial direction of the motor case. Therefore, the initial burning area can be secured without deteriorating the performance. Also, by providing a weak part by bonding the barrier membranes or shaping slits on the barrier membrane, the breaking portion of barrier membrane and the behavior of barrier membrane after breakage can be controlled. Further, by setting an igniter charge having higher ignitability and a higher burning rate than the second propellant between the inner surface of the second propellant and the inner barrier membrane, the detachment of barrier membrane and the ignition of the second propellant can be assisted. | 05-16-2013 |
20140137542 | CONTROLLED PYROTECHNIC TRAIN - A controlled pyrotechnic train implementing a MEMS chip portion for use as an igniter of a charge. The pyrotechnic train includes an initiator; a blocker configured to block the train; a deflector of the blocker; and an output charge. The blocker is displaceable by the action of the deflector. | 05-22-2014 |