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"Flight by machines heavier than air is unpractical and insignificant, if not utterly impossible."
Simon Newcomb, astronomer ; Said in 1902, less than two years before the first flight at Kitty Hawk
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| Number | Title | Issue Date |
| 7980058 | Air compression type engine for aviation The present invention relates to an air compression type engine for aviation. The conventional aircraft engine is complicated in structure, consumes expensive aero fuel, and produces extremely loud noise during operation. Therefore, the present invention employs a t... | 07/19/2011 |
| 7707820 | Control and/or drive device for a flying body Control and/or drive device for a flying body for ejecting hot gas streams of a combusted fuel combination of at least a first and second component. Device includes a first hollow chamber body structured and arranged to contain first component, a second hollow chamb... | 05/04/2010 |
| 7665294 | Exhaust nozzle assembly Apparatus including an exhaust nozzle assembly having a translatable structure operable to open and close a flow diverting port in an exhaust duct. The translatable structure includes a forward region partly defining a converging nozzle region. The translatable stru... | 02/23/2010 |
| 7631486 | Thrust orienting nozzle The present invention relates to a thrust orienting nozzle, shaped in such a way as to divide a principal propulsion gas flow coming from at least one gas generator into a first flow and a second flow for an ejection in a first half-nozzle and in a second half-nozzl... | 12/15/2009 |
| 7628006 | Thrust termination device for solid rocket motor Disclosed is an abrupt opening apparatus of a pressurized chamber in an intended procedure to accomplish thrust termination for a stage separation of the solid rocket motor. It can open trust termination ports with simple mechanical structure to thereby terminate th... | 12/08/2009 |
| 7610747 | 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 direct... | 11/03/2009 |
| 7578121 | 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... | 08/25/2009 |
| 7364115 | System and method for controlling engine RPM of a ducted fan aircraft An aircraft including a ducted fan and an engine for driving the ducted fan includes a plurality of vanes movably mounted to the aircraft at a substantially rectangular exhaust end of the aircraft. Each of the plurality of vanes is substantially rectangular or squar... | 04/29/2008 |
| 7281367 | Steerable, intermittently operable rocket propulsion system A propulsion system including an extinguishable rocket motor and an incorporated maneuver control system. The rocket motor may be of the solid fuel type. One or more proportional axial thrust valves in communication with a pressure vessel or motor case containing a ... | 10/16/2007 |
| 7188802 | Convertible aircraft provided with two tilt fans on either side of the fuselage, and with a non-tilting fan inserted in the fuselage The present invention relates to a convertible aircraft provided with first and second tilt fans disposed on either side of the fuselage a little forward of the center of gravity of the convertible aircraft. In addition, the convertible aircraft includes, in remarka... | 03/13/2007 |
| 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 |
| 7124981 | Thrust reverser utilizing integrated structural bypass duct A thrust reverser having an engine cowl, a nacelle, a blocker door, a nacelle door and a cascade vane. The engine cowl has a hollow body that shrouds a jet engine and which includes a cowl opening. The nacelle surrounds the engine cowl and includes a nacelle opening... | 10/24/2006 |
| 7107757 | Aircraft provided with thrust reversers Some but not all engines of an aircraft are provided with thrust reversers. A safety device disables, at least from the position corresponding to idling, the action of the throttles corresponding to the engines devoid of thrust reversers when the thrust reversers ar... | 09/19/2006 |
| 7102113 | Three-axis attitude control propulsion device and flying object comprising the same A three-axis attitude control propulsion device and a flying object like a rocket including the device are provided in which combustion gas for attitude control can be efficiently used. A three-axis attitude control propulsion device 4, having six nozzles has... | 09/05/2006 |
| 7069717 | Hybrid propulsion system Disclosed is a propulsion system for a spacecraft. The propulsion system includes a supply of oxidizer and at least one nozzle. A conduit fluidly couples the supply of oxidizer and the nozzle. The conduit provides a pathway for oxidizer to flow in a downstream direc... | 07/04/2006 |
| 7051512 | Fluidic diverter valve with a variable valve-bore clearance A fluidic diverter valve includes valve element freely disposed within a valve bore. The valve bore has a cross sectional area that varies. As a result, the clearance between the valve element and an inner surface of the valve bore also varies. This variation in cro... | 05/30/2006 |
| 7018590 | Reverse flow catalytic muffler A catalytic muffler having a housing with a first chamber and a second chamber fluidly communicating through a catalyst bed interspersed there between. A first baffle assembly in the first chamber extends between the catalyst bed and the housing. An inlet passage ex... | 03/28/2006 |
| 7007454 | Locking system on a cascade thrust reverser The invention provides a locking system on a cascade thrust reverser for a bypass turbojet, the reverser (20) comprising guide means (60) for the movable parts (50), and the guide means (60) comprising rails (64) attached to the mo... | 03/07/2006 |
| 6973773 | Propellant supply device A propellant supply device (10) is provided for a vehicle (11) having a main propulsion motor (12) and having an attitude control system (11) including a plurality of thrusters (14A, 14B, 14C, . . . , 14F). The... | 12/13/2005 |
| 6968701 | Engine integrated auxiliary power unit The present invention relates to an engine integrated auxiliary power unit. The engine comprises a high pressure spool which includes a high pressure compressor connected to a high pressure turbine and a low pressure spool which includes a low pressure compressor co... | 11/29/2005 |
| 6951317 | Vehicle, lightweight pneumatic pilot valve and related systems therefor A vehicle, such as a missile, with a pilot valve system controls the vehicle's thrust valves despite a hostile propellant gas environment. The pilot valve system can have one or more pilot valves. Using refractory elements, the pilot valve ball reciprocates between ... | 10/04/2005 |
| 6935098 | Turbomachine nozzle with noise reduction A nozzle comprising an inner barrel, a centerbody disposed inside the inner barrel so as to define a first channel for a primary flow, and an outer barrel surrounding the inner barrel so as to define a second annular channel for a secondary flow, the free end of the... | 08/30/2005 |
| 6918244 | Vertical takeoff and landing aircraft propulsion systems This patent concerns VTOL propulsion systems that develop a forward flow of air through the air intake duct(s), by the methods of a internal duct system, reversing the rotation of the fan, or a variable pitch (thrust reversing) fan. ... | 07/19/2005 |
| 6910328 | Vectorable variable area nozzle A vectorable variable area nozzle is formed by a pair of parallel sidewalls, a pair of opposed clamshell elements arranged between the sidewalls and each able to rotate about an axis perpendicular to the sidewalls and a pair of flaps each pivotally lined to the down... | 06/28/2005 |
| 6837038 | Variable cycle boost propulsor The present invention relates to a variable cycle boost propulsor system for use on an aircraft. The variable cycle boost propulsor system includes an engine, a turbine, a fan connected to the turbine, and a valve system for delivering the fluid output from the engi... | 01/04/2005 |
| 6820411 | Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion An apparatus for providing propulsive power 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 flo... | 11/23/2004 |
| 6591602 | Ejection seat rocket motors A rocket motor is disclosed that is suitable for use with an ejection seat. The rocket motor includes a combustion chamber, and has a plurality of spaced apart outlets arranged in fluid communication with the combustion chamber, to allow the passage of ex... | 07/15/2003 |
| 6502384 | Side thruster of flying object A side thruster of a flying object of the invention is provided with a solid gas generating agent, a nozzle arranged in a direction perpendicular to an axis of the flying object, a tube body for flowing the gas generated in accordance with a combustion of... | 01/07/2003 |
| 6393830 | Hybrid rocket propulsion system including array of hybrid or fluid attitude-control rocket engines This propulsion system of a rocket motor assembly includes an array of attitude-control rocket engines, one or more oxidizer-fluid sources, one or more ignition-fluid sources, and, optionally, one or more primary rocket engines. Each of the attitude-contr... | 05/28/2002 |
| 6352211 | Flow blocking exhaust nozzle An exhaust nozzle for an aircraft engine. The nozzle includes a mount for attaching the exhaust nozzle to a downstream end of the engine and first and second opposed upstream flaps moveably connected to the mount having inner surfaces defining an upstream... | 03/05/2002 |
| 6289669 | Lateral-thrust control arrangement for missiles with solid-fuel hot-gas generator A lateral-thrust control device for a four-quadrant final-phase guidance control of a missile having lateral-thrust nozzles (10) communicating with a solid-fuel gas generator (13). Each of the nozzles has a valve member (22, 38), whose open and closed sta... | 09/18/2001 |
| 6276125 | Pressure balanced poppet valve A valve is disclosed for regulating the flow of a pressurized working fluid through a nozzle having a nozzle throat. In a preferred embodiment of the invention, the valve comprises a valve body defining a valve bore, a pressure inlet and a nozzle plenum. ... | 08/21/2001 |
| 6178741 | Mems synthesized divert propulsion system A synthesized divert propulsion system adapted to be utilized in various vehicles, including kill vehicles, interceptors, rockets, missiles and the like. The system is fabricated using microelectromechanical system (MEMS) technology which eliminates compl... | 01/30/2001 |
| 6102329 | Flow diverter system for multiple streams for gas turbine engine A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine ... | 08/15/2000 |
| 5816042 | Flow diverter system for multiple streams for gas turbine engines A flow diverting mechanism for the twin duct offtakes or coannular offtake for a turbo fan engine powering aircraft with either thrust reversing or short takeoff and vertical landing or both capabilities includes a rotary drum mounted between the turbine ... | 10/06/1998 |
| 5782434 | Self-closing pivoting door thrust reverser with gear actuated panel A thrust reverser for a turbojet engine is disclosed having a thrust reverser door and a thrust reverser panel pivotally attached to a housing so as to pivot in opposite directions about the same pivot axis. An epicyclic gear mechanism interconnects the h... | 07/21/1998 |
| 5765367 | System for controlling a space vehicle by gating gas The control system comprises a plurality of nozzles pointing in different directions, a plurality of gas generators, and pipework connecting the gas generators to the nozzles via gates for allowing or preventing gas being ejected therethrough. Each gas ge... | 06/16/1998 |
| 5706649 | Multi axis thrust vectoring for turbo fan engines The present invention is a thrust reversing apparatus for diverting purely rearwardly directed air flowing through an engine nacelle to combined rearward-and-radially-outward flow, and then to a combination of various radially outward angles and forward f... | 01/13/1998 |
| 5339623 | Singly fueled multiple thrusters simultaneously energized by a common power supply A spacecraft has, in addition to redundant thrusters T3, T4 prime thrusters T1 or T2 arranged to be operated one at a time which are supplied with propellant 1 via valves V1 and V2. The thrusters are of the kind in which energy is transferred to the prope... | 08/23/1994 |
