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| Number | Title | Issue Date |
| 8186145 | Rocket nozzles for unconventional vehicles Improved rocket nozzle designs for vehicles with nozzles embedded in or protruding from surfaces remote from the desired thrust axis. The nozzle configurations are for rocket vehicles where the nozzles are not located at the optimal thrust axis of the vehicle. Two e... | 05/29/2012 |
| 8020367 | Nozzle with yaw vectoring vane An exhaust vane disposed in a divergent section of an aircraft gas turbine engine exhaust nozzle is sideways pivotable about a vane pivot axis. The nozzle vane pivot axis may be centrally located at an unvectored nozzle throat. Transversely spaced apart upper and lo... | 09/20/2011 |
| 7975466 | Exhaust nozzle for thrust vectoring An exhaust nozzle (10) for a gas turbine engine is described for vectoring a flow of exhaust gases issuing therefrom at an angle to a centre line (8) of the engine. The exhaust nozzle (10) comprises a plurality of radially outer flaps (25... | 07/12/2011 |
| 7836681 | Mechanism for a vectoring exhaust nozzle A nozzle device defines a passageway including an outlet to discharge working fluid to produce thrust. This device includes a vectoring mechanism having three or more vanes pivotally mounted across the passageway and a linkage pivotally coupling the vanes together. ... | 11/23/2010 |
| 7716912 | 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... | 05/18/2010 |
| 7581381 | Ducted air power plant A ducted air power plant, comprising a motor driven fan (7) situated in a duct (4), the fan (7) having an air intake side and in operation providing a high pressure air stream in the duct, and the fan being located adjacent air splitter mechanis... | 09/01/2009 |
| 7555893 | Aircraft propulsion system To provide an aircraft propulsion system which can secure the optimum thrust and thrust vector for flight conditions, as well as the optimum sectional area for the engine, and which is highly compatible with the environment. An electrical generator is coupled... | 07/07/2009 |
| 7509797 | Thrust vectoring missile turbojet A turbojet engine includes a core engine, an afterburner, and a converging-diverging exhaust nozzle in serial flow communication. A thrust vectoring system is joined between a compressor and the nozzle. A controller is operatively joined to the thrust vectoring syst... | 03/31/2009 |
| 7481038 | Yaw vectoring for exhaust nozzle An exhaust nozzle assembly provides fluidic thrust vectoring of the primary stream to enhance aircraft maneuverability. The exhaust nozzle assembly includes a cooling air passage that supplies cooling air to a plurality of cooling holes that generate an insulating l... | 01/27/2009 |
| 7434762 | Retractable thrust vector control vane system and method A retractable thrust vector control system (10) for a rocket motor (26) that can generate an exhaust plume comprises at least one control vane (12) connectable to an attitude control assembly (20) that rotates the vane (12) about a... | 10/14/2008 |
| 7406821 | Adapter device for a rocket engine nozzle having a movable diverging portion An adapter device for controlling a rocket engine nozzle under conditions of external pressure that can lead to the jet separating inside the nozzle, the nozzle being fitted with a diverging portion that is movably mounted relative to a stationary portion of the noz... | 08/05/2008 |
| 7313910 | Jet vane thrust vector control system Disclosed is a jet vane thrust vector control (JV-TVC) system. A general system has many problems in design techniques considering actual operation environments, and does not have reliability in component assembly design. The JV-TVC system improves thrust vector con... | 01/01/2008 |
| 7225622 | Turbine engine nozzle A turbine engine nozzle assembly has an upstream flap and a downstream flap pivotally coupled thereto for relative rotation about a hinge axis. An actuator linkage is coupled to the downstream flap along a forward portion thereof for actuating the upstream flaps and... | 06/05/2007 |
| 7174718 | Device for controlling propulsive jet mixing for aircraft jet engines A device for controlling propulsive gas mixing at an outlet of an aircraft jet engine, wherein propulsive jets are composed of a hot primary jet exiting from a nozzle of the jet engine and a secondary flux flowing between an external wall of the nozzle and an intern... | 02/13/2007 |
| 7134271 | Thrust vectoring aft FLADE engine An aft FLADE gas turbine engine including a fan section drivenly connected to a low pressure turbine section followed by an aft FLADE turbine having at least one row of aft FLADE fan blades radially extending across a FLADE duct circumscribing the aft FLADE turbine,... | 11/14/2006 |
| 7104337 | Electrostatic fire control and extinguishing device A fire's electrostatic field is used to directly control and extinguish a fire. A flame is, in and of itself, a virtual electrode. The inventive electro-static fire control and extinguishing device uses at least one common electrode and allows the fire's own electro... | 09/12/2006 |
| 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 |
| 6948307 | Rocket engine nozzle that is steerable by means of a moving diverging portion on a cardan mount The nozzle comprises a moving diverging portion (20) and a static portion (16) secured to the rear end wall of the combustion chamber (12) of the engine. A cardan mount jointed link device connects the moving diverging portion of the nozzle to t... | 09/27/2005 |
| 6745570 | Methods and apparatus for sealing gas turbine engine nozzles using a flap system A method for assembling a flap system for a gas turbine engine exhaust nozzle including a plurality of backbone assemblies facilitates extending a useful life of the exhaust nozzle. The method includes providing a flap basesheet having a width defined between a pair... | 06/08/2004 |
| 6681560 | Nozzle throat area control apparatus and method Control apparatus for a nozzle for a rocket or other vehicle having a combustion chamber with a propellant therein in communication with the nozzle, the nozzle having a throat and a pair of bores extending into the throat The bores may be in opposed or an... | 01/27/2004 |
| 6631314 | Propellant utilization system A propellant utilization system for a space vehicle having at least a first thrust source and a second thrust source. The propellant utilization system utilizes a common set of algorithms to generate mixture ratios for each thrust source as each thrust so... | 10/07/2003 |
| 6598385 | Two stage gas pilot valve controlling gas flow to a reaction jet nozzle A multi-stage pilot valve is disclosed for selectively supplying a working fluid to and venting from a reaction jet main stage actuation chamber. In a preferred embodiment of the invention, the pilot valve comprises a solenoid actuated ball and socket fla... | 07/29/2003 |
| 6532730 | Slip joint duct system for a rocket fuel duct Various joints within a duct assembly to allow relative movement between portions of a fluid system which are interconnected by this duct assembly are disclosed. This duct assembly is particularly suited for interconnecting a rocket fuel tank and rocket e... | 03/18/2003 |
| 6520450 | V/STOL aircraft An aircraft having a powerplant with an aft-directed main propulsion outlet means for providing forward thrust, and further including duct means having an inlet for receiving at least a proportion of the efflux from said main propulsion outlet and extendi... | 02/18/2003 |
| 6315239 | Variable coupling arrangement for an integrated missile steering system An integrated system for missile steering, which uses both jet reaction control (JRC) and aerofin control systems, is provided with a variable coupling mechanism for adjusting the relative responsiveness of the two systems in accordance with the pressuriz... | 11/13/2001 |
| 6192671 | Cross bar centering mechanism for slave petals in covergent divergent nozzles with variable geometry Divergent petal arrangement for convergent-divergent nozzles with thrust vectoring capability through changes in the divergent section geometry, in which the position of each slave divergent petals 4 is determined by a centering mechanism 31, made up by t... | 02/27/2001 |
| 6170253 | Cascade structure arrangement for a gas turbine engine A gas turbine engine is provided with a translatable cowl and a cascade structure which is nested within the translatable portion of the cowl. The cascade structure comprises a pair of C ducts which are exposed upon translation of a portion of the cowl. T... | 01/09/2001 |
| 6134873 | Method of operating a combustion turbine power plant at full power at high ambient temperature or at low air density using supplemental compressed air A method is provided to ensure that a combustion turbine power generation system may operate at maximum allowable power at elevated ambient temperature and/or at low air density. The method includes providing at least one combustion turbine assembly inclu... | 10/24/2000 |
| 6105364 | Vstovl engines A turbofan engine is provided with a conventional air by-pass duct communicating with a plenum chamber downstream of the engine core, vectoring nozzles upstream of the by-pass duct, and a non-vectoring nozzle and a jet-pipe exhausting from the plenum cham... | 08/22/2000 |
| 6105901 | Thrust vectoring system A thrust directing mechanism to vector thrust and control discharge throat area with a number of vanes mounted across the passage. The mechanism includes a control link pivotally coupled to each of the vanes. The control link is selectively movable to cor... | 08/22/2000 |
| 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 |
| 6042053 | Automatic restow system for aircraft thrust reverser An actuation activation system for an aircraft engine thrust reverser system is provided including an improved locking actuator (29), a sleeve sensor mechanism, and auto-restow control logic. The locking actuator (29) includes a lever (57) corresponding t... | 03/28/2000 |
| 5903432 | Computer package with a polygonal shaped motherboard An electronic assembly that includes a plurality of electronic substrates that are plugged into a polygonal shaped motherboard. The polygonal shape of the motherboard minimizes the electrical path between electronic substrates while providing enough space... | 05/11/1999 |
| 5752381 | Method and apparatus for vectoring thrust employing electrodes generating voltages greater than the dielectric breakdown voltage A method and apparatus are provided for controlling rocket and/or jet engine thrust by producing a strong electric, magnetic or electro-magnetic field, and applying the field to deflect the thrust stream as it exits from the engine until the desired thrus... | 05/19/1998 |
| 5598701 | Frangible connection for a thrust reverser for a ducted fan gas turbine A ducted fan gas turbine engine is provided with a thrust reverser which comprises doors which deflect the fan exchaust efflux. Each door is pivotably attached at its downstream end to a common support member by a frangible coupling. In the event of an un... | 02/04/1997 |
| 5485959 | Axisymmetric vectoring exhaust nozzle thermal shield A thrust vectoring axisymmetric vectoring exhaust nozzle having universally pivoting divergent flaps is provided with a surrounding thermal shield of overlapping outer flaps and seals generally disposed in an aftwards converging conical arrangement and ha... | 01/23/1996 |
| 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 |
| 5329763 | Thrust vectoring variable geometry exhaust nozzle for gas turbines A thrust vectoring variable geometry exhaust nozzle for gas turbines, which includes a convergent section (2) followed, in the direction of the flow, by a divergent section (3), both formed by master (4 and 5) and slave petals (41 and 42), whose convergen... | 07/19/1994 |
| 5245823 | External flap vectoring mechanism An external flap vectoring mechanism on an axisymmetric gas turbine exhaust nozzle, the external flap vectoring mechanism comprising a plurality of external flaps, each such flap having first and second flaps, the first flap pivotably connected to a sync ... | 09/21/1993 |
| 5239815 | Sync-ring assembly for a gas turbine engine exhaust nozzle A sync-ring assembly for use on a axisymmetric gas turbine exhaust nozzle, the sync-ring having a semi-spherical outward surface received within and slidably contacting the cylindrical inner surface of a liner. The sync-ring runs along guide tracks mounte... | 08/31/1993 |
