Famous Patents
3M employee and church chorister Art Fry needed something to temporarily mark pages in his hymnal. He was in luck because his colleague, Spencer Silver, accidentally developed a glue that was too weak for other purposes. After initially discouraging consumer response, Post-it Notes became a hit in 1979.
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| Number | Title | Issue Date |
| 8056319 | Combined cycle missile engine system An insensitive combined cycle missile propulsion system includes a solid fuel contained within a first section of the missile, a liquid oxidizer contained within a second section of the missile and a solid oxidizer contained within a third section of said missile. A... | 11/15/2011 |
| 7849670 | Propulsion system with integrated rocket accelerator The present invention relates to a propulsion system for a vehicle. The propulsion system has an airframe integrated hydrocarbon fueled airbreathing engine, such as a ramjet or a scramjet. The propulsion system further has at least one rocket positioned so as to use... | 12/14/2010 |
| 7621116 | Gas turbine engine system An engine system comprises a first transfer positive displacement, volumetric device, at least one second positive displacement, volumetric device, and a transmission in engagement with two adjacent volumetric devices. The transmission has a ratio designed to cause ... | 11/24/2009 |
| 7509796 | Pintle-controlled propulsion system with external dynamic seal A propulsion system with a pintle for variable thrust is constructed such that the pintle contains a shaft at its fore end which passes through an opening in the thrust chamber wall and extends into a boss on the outside surface of the thrust chamber. A dynamic seal... | 03/31/2009 |
| 7484353 | Rocket motor case using plank sections and methods of manufacturing A rocket motor case includes a plurality of plank sections which provide a structural key for locking metal and/or composite end enclosures in place as part of the motor case. The plank sections are sized longitudinally to form venting spaces in the motor case sidew... | 02/03/2009 |
| 7412831 | Integral cooling system for rotary engine A rotary combustion engine (12) with a self-cooling system comprises a heat exchanging interface for discharging excess heat from the rotary combustion engine (12), and a direct drive fan (44) integrated on the rotary engine output shaft (26 | 08/19/2008 |
| 7351458 | Plastics bags and methods of making the same A plastics bag has at least one seal (34, 36) extending parallel to the mouth of the bag to close the sides. Preferably, a reclosable zipper seal (36) is provided below a top seal (34). A novel tag is provided, secured to the zipper seal (36 | 04/01/2008 |
| 7334392 | Counter-rotating gas turbine engine and method of assembling same A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft... | 02/26/2008 |
| 7328571 | Semi-axisymmetric scramjet flowpath with conformal nozzle In accordance with a first aspect of the present invention, an aircraft having a scramjet engine is provided. The scramjet engine includes a flowpath which varies in three dimensions. In accordance with a second aspect of the present invention, a method for launchin... | 02/12/2008 |
| 7316855 | Fuel cell assembly for portable electronic device and interface, control, and regulator circuit for fuel cell powered electronic device A fuel cell assembly including a membrane electrode assembly, an anode plate, a cathode plate, a removable fuel cartridge, and a fuel delivery system. The assembly includes an anode, a cathode, and a polymer electrolyte membrane having a fuel side and an oxygen side... | 01/08/2008 |
| 7269951 | Throat retention apparatus for hot gas applications A nozzle for use in a hot gas valve is provided that includes a housing, an insert, and a throat retainer. The housing is constructed of an insulating material and has a flow path formed therein. The flow path has a throat section. The insert is made of material cap... | 09/18/2007 |
| 7254936 | Simple solid propellant rocket engine and super-staged rocket A solid propellant rocket engine includes: a propellant formed into a predetermined shape having a combustion cavity and capable of deflagrating into hot, high-pressure gas upon ignition; and a nozzle configured and positioned to expand the hot, high-pressure gas in... | 08/14/2007 |
| 7216474 | Integrated air inlet system for multi-propulsion aircraft engines An air inlet duct for an air-breathing combined-cycle aircraft engines is internally divided into separate channels for low-speed and high-speed components of the engine, and contains one or more movable panels that are fully contained within the duct and pivotal be... | 05/15/2007 |
| 7200987 | Off-axis pulse detonation configuration for gas turbine engine The present invention is a gas turbine engine system containing a compressor stage, a pulse detonation stage, and a turbine stage. During operation of the engine system, compressed flow from the compressor stage is directed to at least one off-axis pulse detonation ... | 04/10/2007 |
| 7200538 | Methods and apparatus for modeling gas turbine engines A method enables modeling of a gas turbine engine that includes a pulse detonation system. The method includes providing a pulse detonation modeling system, predicting characteristics of the engine using the pulse detonation modeling system, and predicting character... | 04/03/2007 |
| 7168236 | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which th... | 01/30/2007 |
| 7137255 | Compact swirl augmented afterburners for gas turbine engines An afterburner apparatus that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel and an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which th... | 11/21/2006 |
| 7107756 | Turbofan arrangement A bypass turbofan engine comprises a first propulsion system and a second propulsion system. The first propulsion system comprises a first fan rotor, a core engine, a first low pressure turbine and a first fan shaft drivingly connecting the first turbine and the fir... | 09/19/2006 |
| 7055306 | Combined stage single shaft turbofan engine A turbofan engine includes a combined stage rotor mounted for common rotation with a shaft, a compressor stage, and a turbine stage. Each of the plurality of fan blades of the combined stage rotor are contiguous with a respective compressor blade. The combined stage... | 06/06/2006 |
| 7047724 | Combustion ignition Distributed initiation (e.g., multipoint or continuous) is utilized to obtain constant volume-like combustion performance in a pulse combustion device in the absence of detonation. A number of such devices may be utilized as turbine engine combustors. ... | 05/23/2006 |
| 7000377 | Super-staged and continuously staged rocket A super-staged rocket includes at least approximately 50 rocket engines, where the engines are distributed according to at least one of: at least five multi-engine stages connected in series, each stage including at least ten engines connected in parallel; and at le... | 02/21/2006 |
| 6968695 | Compact lightweight ramjet engines incorporating swirl augmented combustion with improved performance A ramjet powered device that utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an oxidant flow into a turbulent, three-dimensional flowfield into which th... | 11/29/2005 |
| 6964154 | Axisymmetric, throttleable non-gimballed rocket engine A rocket engine assembly is provided for a vertically launched rocket vehicle. A rocket engine housing of the assembly includes two or more combustion chambers each including an outlet end defining a sonic throat area. A propellant supply for the combustion chambers... | 11/15/2005 |
| 6952917 | Dual liquid engine and rocket using the same The engine for a rocket is suitable for using for an educational program. The engine uses a liquid phase propellant having a predetermined boiling point and a heating substance having a temperature higher than the boiling point. The engine has an inner wall having a... | 10/11/2005 |
| 6926232 | Variable cycle propulsion system with compressed air tapping for a supersonic airplane A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having at least one compressor and capable of generating thrust for supersonic flight speeds, and at least one auxiliary propulsion assembly separate from said en... | 08/09/2005 |
| 6918243 | Bi-propellant injector with flame-holding zone igniter A bi-propellant injector (66) includes a first injector element (68) and a second injector element (70) injecting a first propellant (69) and a second propellant (71), respectively, into a combustion chamber (53). A flame-ho... | 07/19/2005 |
| 6915626 | Blanking-plug system for blanking off an orifice of a pipe, particularly for blanking off an orifice of a duct for introducing air into the combustion chamber of a ramjet A blanking-plug system for blanking off an orifice of a pipe, particularly for blanking off an orifice of a duct for introducing air into the combustion chamber of a ramjet. The blanking-plug system (16) comprises at least one blanking plug (15)... | 07/12/2005 |
| 6907724 | Combined cycle engines incorporating swirl augmented combustion for reduced volume and weight and improved performance A combined-cycle engine having at least one core engine and at least one ramjet engine. The ramjet utilizes a novel swirl generator for rapidly and efficiently atomizing, vaporizing, as necessary, and mixing a fuel into an oxidant. The swirl generator converts an ox... | 06/21/2005 |
| 6857261 | Multi-mode pulsed detonation propulsion system A multi-mode propulsion system for potential application to hypersonic and aerospace planes. The system can employ various propulsion modes at various points in time, with the propulsion system employed at a given point in time being selected according to the veloci... | 02/22/2005 |
| 6845606 | Variable cycle propulsion system with gas tapping for a supersonic airplane, and a method of operation A variable cycle propulsion system for a supersonic airplane, the system comprising at least one engine having means for producing exhaust gas and a gas exhaust nozzle for generating thrust for supersonic flight speeds, and at least one separate auxiliary propulsion... | 01/25/2005 |
| 6808145 | Dual-mode airbreathing propulsion system The present invention includes a method for a dual-mode propulsion system. During the first mode of operation, intake air is liquefied through a cooling heat exchanger and condenser using a combination of stored liquid hydrogen (LH2) and stored liquid nit... | 10/26/2004 |
| 6782693 | Case burning rocket with drive system for combustion chamber and nozzle A case-burning rocket booster includes a combustible case containing a solid rocket fuel, a combustion chamber adjustably coupled to the case for burning the case and the solid rocket fuel, a nozzle connected to the combustion chamber for expelling the burned case a... | 08/31/2004 |
| 6477829 | Combined cycle pulse combustion/gas turbine engine A combined cycle pulse combustion/gas turbine engine has a gas turbine engine used in conjunction with a plurality of pulse combustion engines. In one embodiment, the gas turbine engine includes a housing, a bypass fan, a central engine core, and a diffus... | 11/12/2002 |
| 6378292 | MEMS microthruster array A microelectrical mechanical system (MEMS) microthruster array is disclosed. The MEMS microthruster array of the present invention can be used for maintaining inter satellite distance in small satellites. One microthruster array includes numerous microthr... | 04/30/2002 |
| 6293091 | Axisymmetrical annular plug propulsion system for integrated rocket/ramjet or rocket/scramjet The invention is an airframe which includes a vehicle (12) having a solid propellant rocket engine (14) and a ramjet or scramjet engine (16); a thrust plug (18) extending from an end (20) of the vehicle which directs combustion gases (23 and 64) produced ... | 09/25/2001 |
| 5873240 | Pulsed detonation rocket engine A pulse detonation rocket engine, having at least two detonation chambers. The rocket propelled vehicle includes at least one fuel delivery system in fluid communication with each of the at least two detonation chambers, and at least one oxidant delivery ... | 02/23/1999 |
| 5823469 | Missile launching and orientation system This invention concerns a missile launching system, and particularly a missile launching and orientation system. It can be used to modernize missiles with an inclined launch at an angle by transforming them into missiles controlled for circular defense, a... | 10/20/1998 |
| 5787703 | Combined ramjet and rocket engine having rectilinear duct A combined ramjet and rocket engine, operates as a ramjet in atmosphere, and a rocket engine in space is provided with a rectilinear duct. The engine has interior of the rectilinear duct paired and hinged rectilinear baffles which move from one of the duc... | 08/04/1998 |
| 5402720 | Booster-missile self-aligning adapter A self-aligning adapter used for attaching a booster to a missile includes a hollow tapered receptacle positioned on the missile. A tapered member sized and shaped to fit into and mate with the receptacle is positioned on the booster. The tapered member f... | 04/04/1995 |
| 5383332 | Gas turbine engines A variable cycle gas turbine bypass engine includes a first fan 1 located at an inlet to the engine so as to provide air to a compressor 2 driven by a turbine 11 and to a bypass duct 13 surrounding the compressor housing. A second fan 5 located in the byp... | 01/24/1995 |
