Did You Know...
...that the Band-Aid Bandage was invented by a Johnson & Johnson employee whose wife had cut herself? Earl Dickson's wife was rather accident prone, so he set out to develop a bandage that she could apply without help. He placed a small piece of gauze in the center of a small piece of surgical tape, and what we know today as the Band Aid bandage was born!
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| Application No. | Application Title | Issue Date |
| 20120079807 | METHOD FOR PRODUCING SOLID COMPOSITE ALUMINIZED PROPELLANTS, AND SOLID COMPOSITE ALUMINIZED PROPELLANTS The main subjects of the present invention are:
| 04/05/2012 |
| 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 mo... | 02/23/2012 |
| 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 al... | 01/12/2012 |
| 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 |
| 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 |
| 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 mat... | 02/24/2011 |
| 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 co... | 11/11/2010 |
| 20100275576 | SYSTEM AND METHOD FOR MANEUVERING ROCKETS A dual control system for a solid propellant propelled exoatmospheric kill-vehicle is disclosed. The system includes a primary solid propellant propulsion mechanism for controlling the propulsion of the kill-vehicle during a first phase of rocket flight, and a secondary... | 11/04/2010 |
| 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 prope... | 10/07/2010 |
| 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 composit... | 10/07/2010 |
| 20100224731 | PROPULSION SYSTEM AND METHOD USING A COMBUSTION CHAMBER DISCHARGING A CONCENTRATED MASS A propulsion system and method are described configured to exert a force upon a vehicle. The system includes a concentrated mass which may be discharged from the vehicle by a propellant typically via an ejection tube. The system is optimized so that the discharged conce... | 09/09/2010 |
| 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 devic... | 07/15/2010 |
| 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 prope... | 04/08/2010 |
| 20100024385 | PULSED PLASMA THRUSTER AND METHOD OF OPERATION THEREOF A pulsed plasma thruster and method of operation are provided. The pulsed plasma thruster comprises solid propellant material. A main discharge source provides a pulsed discharge across the propellant material for ablating the propellant material to produce propellant p... | 02/04/2010 |
| 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 b... | 02/04/2010 |
| 20090229245 | END BURNING TYPE GAS GENERATOR An end burning type gas generator includes a hollow cylindrical combustor, a propellant which is densely charged in the combustor concentrically and in a plurality of layers without leaving a large void in an internal cross section and which has the same sectional area ... | 09/17/2009 |
| 20090229241 | HYBRID MISSILE PROPULSION SYSTEM WITH RECONFIGURABLE MULTINOZZLE GRID A propulsion system, such as for use in a missile, includes a multinozzle grid having a pair of plates that are separably mechanically coupled together. When coupled together in a first configuration, the plates provide multiple nozzles in a first nozzle configuration (... | 09/17/2009 |
| 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... | 06/04/2009 |
| 20090133405 | Combustible outgassing material lined altitude compensating rocket nozzle A fixed sized bell rocket nozzle is lined with a layer of combustible material that is ignited during launch ignition and burns to outgas into the rocket exhaust for spatially variably confining the exhaust and perfecting an effective variably sized altitude compensatin... | 05/28/2009 |
| 20080134924 | Controllable digital solid state cluster thrusters for rocket propulsion and gas generation A thruster stack assembly and method for manufacturing the same is provided. The thruster stack assembly includes a plurality of grain elements having a common core region (e.g., a channel or passageway), where each grain element comprises a volume of electrically ignit... | 06/12/2008 |
| 20070204593 | Propulsion thrust control system and method A propulsion thrust control system and method for controlling thrust in a rocket motor includes configuring valves of an energized rocket motor to an initial total valve area according to a total thrust command. The total thrust command is converted into a commanded pro... | 09/06/2007 |
| 20070193250 | Side thruster module A side thruster module, comprises: a cavity-type body skin extending in a longitudinal direction; a first thruster arranged in the body skin and extending in a longitudinal direction; and a conversion nozzle arranged in the body skin and extending in a radial direction ... | 08/23/2007 |
| 20070113537 | Thrust termination device for solid rocket motor Disclosed is a thrust termination device for a solid rocket motor, which terminates the net thrust by the reverse thrust of the rocket motor produced from the emission of the combustion gas in the reverse direction, when the stage separation signal is transferred at the... | 05/24/2007 |
| 20050188677 | Systems and methods for varying the thrust of rocket motors and engines while maintaining higher efficiency using moveable plug nozzles The thrust of a rocket motor can be varied while maintaining efficiency over a range of pressure ratios using a design that allows for changing the relative position of a plug and a combustion chamber exit. The plug or the chamber exit may be attached to an adaptive con... | 09/01/2005 |
| 20050034447 | Polyoxymethylene as structural support member and propellant A vehicle includes at least one polyoxymethylene structural support member. The polyoxymethylene structural support member includes a polyoxymethylene component that is a propellant that provides thrust to the vehicle upon pyrolysis or combustion of the polyoxymethylene... | 02/17/2005 |
| 20050028514 | Method of insulating a case of a solid propellant rocket motor This method permits manufacturing EPDM rocket motor insulation in which carbon fibers are dispersed and immobilized in the EPDM polymeric matrix but are not excessively fractured or fragmentized, i.e., broken into smaller fragments, when encountering degrees of shear ne... | 02/10/2005 |
