With Thrust Direction Modifying Means Patents (Class 60/228)
  • Patent number: 10920714
    Abstract: A hybrid rocket engine is described that achieves stable, highly efficient hybrid combustion by having a core flow of fuel-rich gas generator gases, with the flow being surrounded with an annular injection of oxidizer. The fuel-rich gas serves to vaporize and decompose the oxidizer, such as nitrous oxide, and prepare it for effective, stable combustion. In one embodiment, this is done at the head-end of a combustion chamber. The combustion products can then be expanded through a nozzle to create thrust. The engine can be an upper stage engine that can include modular thrust chambers and an integrated aerospike nozzle. The thrust chambers can be arranged in an array that rings the top of the aerospike nozzle.
    Type: Grant
    Filed: March 14, 2014
    Date of Patent: February 16, 2021
    Assignee: EXQUADRUM, INC.
    Inventors: Kevin E. Mahaffy, Byron Henning, Korey Robert Kline, Philip Pelfrey, Eric Schmidt, Elias Wilson
  • Patent number: 10724476
    Abstract: An assembly is provided for an aircraft propulsion system with an axial centerline. The assembly includes a translating sleeve, a sleeve actuator and a locking apparatus. The sleeve actuator is connected to the translating sleeve. The sleeve actuator is configured to move the translating sleeve along the axial centerline between a stowed position and a deployed position. The locking apparatus includes a lock and a lock actuator. The lock comprises a locking element. The lock actuator is configured to move the locking element between a locked position and an unlocked position. The locking element is configured to lock the translating sleeve in the stowed position when the locking element is in the locked position. A first portion of the locking apparatus axially overlaps the sleeve actuator along the axial centerline. A second portion of the locking apparatus does not axially overlap the sleeve actuator along the axial centerline.
    Type: Grant
    Filed: March 27, 2017
    Date of Patent: July 28, 2020
    Assignee: Rohr, Inc.
    Inventors: Timothy Gormley, Imad D. Ghandour
  • Patent number: 10724477
    Abstract: A lock system for a component of a thrust reverser actuation system (“TRAS”), comprising a lock member translatable between a locked position, in which the lock member prevents movement of the thrust reverser component to deploy the thrust reverser actuation system, and an unlocked position, in which the lock member allows movement of the thrust reverser component to deploy the thrust reverser actuation system. The actuator may further comprise a screw shaft and a nut translatable along the screw shaft and operatively connected to the lock member. Rotational movement of one of the screw shaft and the nut causes the nut to translate along the screw shaft and, in turn, the lock member to move between its locked position and its unlocked position.
    Type: Grant
    Filed: May 9, 2018
    Date of Patent: July 28, 2020
    Assignee: GOODRICH ACTUATION SYSTEMS LIMITED
    Inventors: Andrew Hawksworth, James Holding
  • Patent number: 10316796
    Abstract: The invention relates to a combustion gas discharge nozzle for a rocket engine including a stationary part and a moving part extending from the stationary part, the moving part made using flaps positioned downstream from the stationary part and forming an extension of the nozzle, the nozzle including a sealing device extending between the fixed part and the moving part in the form of a flexible membrane withstanding a local temperature of the combustion gases at the nozzle outlet and connecting the end of the stationary part to a border of the flaps or petals forming the moving part, the flexible membrane forming an annular tubing, the sealing device being provided with a duct for injecting gas at the flexible membrane between the stationary part and the moving part extending the nozzle.
    Type: Grant
    Filed: July 23, 2014
    Date of Patent: June 11, 2019
    Assignee: AIRBUS SAFRAN LAUNCHERS SAS
    Inventor: Jean-Philippe Dutheil
  • Publication number: 20150113946
    Abstract: A flow vectoring turbofan engine employs a fixed geometry fan sleeve and core cowl forming a nozzle incorporating an asymmetric convergent/divergent (con-di) and/or curvature section which varies angularly from a midplane for reduced pressure in a first operating condition to induce flow turning and axially symmetric equal pressure in a second operating condition for substantially axial flow.
    Type: Application
    Filed: October 24, 2013
    Publication date: April 30, 2015
    Applicant: The Boeing Company
    Inventors: Robert H. Willie, David F. Cerra, Leonard J. Hebert
  • Publication number: 20150107224
    Abstract: A thrust reverser system deployable from a core cowl is provided. The thrust reverser system may comprise one or more doors that are configured to overlap to reduce leakage and increate reverse thrust while deployed. The doors may be configured to vanes that are configured to split and/or direct airflow.
    Type: Application
    Filed: October 17, 2013
    Publication date: April 23, 2015
    Applicant: ROHR, INC.
    Inventor: Michael Aten
  • Publication number: 20150052875
    Abstract: A blocker door actuation system for use in an aircraft thrust reverser is provided. The blocker door actuation system may comprise a rack, a gear, a gear housing, a screw shaft, and a link. The blocker door actuation system may be mounted to a translating sleeve in an aircraft nacelle. In response to the thrust reverser being activated and the translating sleeve moving aft, the blocker door actuation system may move the blocker door from a stowed position to a deployed position in a fan air duct.
    Type: Application
    Filed: August 23, 2013
    Publication date: February 26, 2015
    Applicant: ROHR, INC.
    Inventor: Sarah Lohman
  • Patent number: 8910464
    Abstract: A thrust-vectoring nozzle is disclosed that includes a cylindrical case and a flow director. The flow director includes a cylindrical ring having a dimension to fit within the cylindrical case. The cylindrical ring has an inner wall and an outer wall and a plurality of fixed vanes are coupled to the inner wall of the ring. The flow director is configured to rotate about first and second mutually perpendicular axes.
    Type: Grant
    Filed: April 26, 2011
    Date of Patent: December 16, 2014
    Assignee: Lockheed Martin Corporation
    Inventor: David Ambrose
  • Patent number: 8800259
    Abstract: In one embodiment, a nozzle of a gas turbine engine may be provided having a coanda injector and a fluidic injector which operate together to provide for a change in exhaust flow direction. The fluidic injector may be coincident with or downstream of the coanda injector and both may be used in high pressure ratio operations of the nozzle. The fluidic injector may be positioned opposite the coanda injector and, when activated, may provide for a region of separated flow on the same side of the nozzle as the fluidic injector. The coanda injector may provide additional momentum to an exhaust flow flowing through the nozzle and may encourage the flow to stay attached on the coanda injector side of the nozzle.
    Type: Grant
    Filed: September 22, 2008
    Date of Patent: August 12, 2014
    Assignee: Rolls-Royce North American Technologies, Inc.
    Inventors: Crawford F. Smith, III, Steve Bergeron
  • Patent number: 8763930
    Abstract: The present invention's nozzle is especially suitable for use in a shipboard air-discharge maneuverability device known as a “bow thruster.” As typically embodied, the inventive nozzle includes a nozzle wall and an arc-shaped vane. The nozzle wall has a circular nozzle inlet and an elliptical nozzle outlet, and is configured so that the geometric major axis of the nozzle outlet is horizontal. The arc-shaped vane: is upwardly bowed in the nozzle wall's transverse direction; joins the nozzle wall along its two horizontally opposite sides in the nozzle wall's longitudinal direction; extends most or all of the longitudinal distance between the nozzle inlet and the nozzle outlet; has a transversely intermediate section that, taken in the transverse direction, is generally uniform in thickness; has two transversely lateral sections that, taken in the transverse direction, gradually thicken toward the two respective joints of the arc-shaped vane with respect to the nozzle wall.
    Type: Grant
    Filed: March 9, 2011
    Date of Patent: July 1, 2014
    Assignee: The United States of America as represented by the Secretary of the Navy
    Inventors: Yu-Tai Lee, Paul A. Coffin
  • Publication number: 20140137539
    Abstract: A detonation thrust-producing device includes an explosive located in a recess in an external surface of a body. Detonation of the explosive expels material out of the recess, providing thrust to the body in an opposite direction. A mass, such as a metal disk, may be placed blocking or covering the external opening. The body may be a part of a vehicle, such as an airborne projectile. The thrust-producing device may include multiple detonation motors arrayed around the body, capable of being individually or multiply detonated. Such thrust-producing devices may be used for attitude adjustment, steering, or other control of the flight of the projectile or other air vehicle. The detonation thrust-producing devices have the advantage of a faster-response time than propellant-based devices, and do not need the nozzles that are used with many propellant-based devices.
    Type: Application
    Filed: November 19, 2012
    Publication date: May 22, 2014
    Applicant: RAYTHEON COMPANY
    Inventor: RAYTHEON COMPANY
  • Patent number: 8727284
    Abstract: An electromechanical actuation system (10) for a space vehicle includes a propellant source (18) and at least one turbine (14) operably connected to the propellant source (18) and rotatable by a flow of propellant (16) therefrom. At least one electrical generator (20) is operably connected to the at least one turbine (14) and is configured to convert rotation of the turbine (14) into electrical energy. At least one electromechanical actuator (12) is operably connected to the at least one electrical generator (20) such that electrical energy from the at least one electrical generator (20) drives operation of the at least one electromechanical actuator (12). A method of operating a turbine powered electromechanical actuator (12) for a space vehicle includes rotating the at least one turbine (14) via a flow of propellant (16) therethrough.
    Type: Grant
    Filed: January 22, 2010
    Date of Patent: May 20, 2014
    Assignee: Hamilton Sundstrand Corporation
    Inventor: David G. Hill
  • Patent number: 8707675
    Abstract: A hot-gas thruster is actuated using a relatively small electric motor. The hot-gas thruster includes a pressure assisted pilot shaft to keep electric power demand to only a few hundred watts peak and only tens of watts on average, while exhibiting relatively fast response times.
    Type: Grant
    Filed: January 20, 2011
    Date of Patent: April 29, 2014
    Assignee: Honeywell International Inc.
    Inventors: Steve Abel, Raymond R. Tseng
  • Publication number: 20140060004
    Abstract: The exhaust system is located on each nacelle of a tiltrotor aircraft. The exhaust system includes a vector nozzle that is selectively rotatable in relation to each nacelle in order to achieve certain performance objectives. The vector nozzle can be oriented to provide maximum flight performance, reduce infrared (IR) signature, or even to reduce/prevent ground heating.
    Type: Application
    Filed: August 13, 2012
    Publication date: March 6, 2014
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Thomas M. Mast, Keith C. Pedersen, David L. Miller, Steven Ray Ivans
  • Patent number: 8583294
    Abstract: A dual redundant actuation control system for controlling a plurality of actuators for positioning a plurality of moveable aircraft components. The actuation control system includes a component controller. The component controller includes two component control channels. Each of the plurality of actuators is electrically connected to each of the two component control channels such that either of the two component control channels may control any or all of the plurality of actuators.
    Type: Grant
    Filed: April 11, 2011
    Date of Patent: November 12, 2013
    Assignee: Hamilton Sundstrand Corporation
    Inventors: William E. Villano, Kevin Gibbons, Teddy L. Jones, Francis W. Recck
  • Patent number: 8539751
    Abstract: 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 propellant mass flow discharge rate. A varying total valve area is computed from an error between the commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. The valves are reconfigured according to a distribution of the varying total valve area. The propulsion system includes a pressure vessel with valves and a controller for regulating the valve area according to a propellant mass flow discharge rate from the pressure vessel.
    Type: Grant
    Filed: April 14, 2010
    Date of Patent: September 24, 2013
    Assignee: Alliant Techsystems Inc.
    Inventors: Cary Lee Cover, Sean Scott Stroud, Michael Joseph Piovoso, Timothy James Kelly
  • Patent number: 8468796
    Abstract: A by-pass turbojet including a thrust reverser is disclosed. The thrust reverse includes a deflector device which deflects all or part of the primary stream gas in such a manner that the deflected primary stream gas encounters the secondary stream, thereby reducing the injection speed of the secondary stream in an aft direction, and thus generating the thrust-reversal effect. The secondary stream escapes from the aft end of the nacelle. In the thrust-reversal position, the deflector device is inscribed radially substantially within the section of the primary nozzle cowl at the aft end of the nacelle. Such a thrust reverser is particularly simple in design, inexpensive, and makes it possible to avoid having moving parts present on the outside portion of the nacelle, thus simplifying the design of the turbojet.
    Type: Grant
    Filed: April 10, 2008
    Date of Patent: June 25, 2013
    Assignee: SNECMA
    Inventors: Yves Emprin, Jeremy Edmond Fert, Jean-Pierre Valentin Wesolowski
  • Patent number: 8371104
    Abstract: A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be integrated into a nozzle deck or side walls without the need for engine bleed to supply fluid injectors. An external fluidic vectoring system uses injectors or plasma devices located aft of the nozzle exit to vector the exhaust plume with no external moving parts. Elements of both mechanical and fluidic systems may be combined for a given application.
    Type: Grant
    Filed: October 10, 2008
    Date of Patent: February 12, 2013
    Assignee: Lockheed Martin Corporation
    Inventors: David M. Wells, Brent N. McCallum, Kerry B. Ginn, Stewart A. Jenkins
  • Patent number: 8245495
    Abstract: 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. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage.
    Type: Grant
    Filed: November 22, 2010
    Date of Patent: August 21, 2012
    Assignee: Rolls-Royce Corporation
    Inventors: Kenneth M. Pesyna, Jeffrey P. Henkle
  • Publication number: 20120186223
    Abstract: A hot-gas thruster is actuated using a relatively small electric motor. The hot-gas thruster includes a pressure assisted pilot shaft to keep electric power demand to only a few hundred watts peak and only tens of watts on average, while exhibiting relatively fast response times.
    Type: Application
    Filed: January 20, 2011
    Publication date: July 26, 2012
    Applicant: HONEYWELL INTERNATIONAL INC.
    Inventors: Steve Abel, Raymond R. Tseng
  • Patent number: 8215096
    Abstract: An outlet device for a jet engine comprises a number of fixed ducts, each with a gas intake and a gas outlet for conducting a gas from the jet engine, at least two of the outlets of said gas ducts open in different directions, and a gas distribution arrangement is arranged at the gas intakes for selective distribution of the gas to the ducts.
    Type: Grant
    Filed: October 20, 2005
    Date of Patent: July 10, 2012
    Assignee: Volvo Aero Corporation
    Inventors: Anders Lundbladh, Melker Härefors, Richard Avellán
  • Publication number: 20120167550
    Abstract: One embodiment of the present invention is a unique thrust augmented gas turbine engine. Other embodiments include apparatuses, systems, devices, hardware, methods, and combinations for thrust augmented gas turbine engines. Further embodiments, forms, features, aspects, benefits, and advantages of the present application will become apparent from the description and figures provided herewith.
    Type: Application
    Filed: December 27, 2011
    Publication date: July 5, 2012
    Inventors: Victor Lewis Oechsle, Andrew James Elfert, Daniel Kent Vetters, Bradley Eugene Auker
  • Patent number: 8205821
    Abstract: A method for exhausting gas from an aircraft engine assembly is provided. The method includes coupling a first exhaust duct in fluid communication only to a first engine. The first exhaust duct includes a primary outlet and a secondary outlet. The method further includes coupling a second exhaust duct in fluid communication only to a second engine. The second exhaust duct includes a primary outlet and a secondary outlet. The method also includes aligning a portion of the first engine secondary outlet concentrically within a portion of the second engine secondary outlet.
    Type: Grant
    Filed: December 13, 2006
    Date of Patent: June 26, 2012
    Assignee: General Electric Company
    Inventor: Robert Andrew Peck
  • Patent number: 8186145
    Abstract: 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 examples include nozzles located on the forward end of the vehicle (also called tractor nozzles) and attitude control nozzles located on the periphery of the vehicle. More particularly, the disclosed nozzle shapes enhance the axial thrusts and/or maneuver torques on the vehicle. These unconventional nozzle shapes improve vehicle performance.
    Type: Grant
    Filed: February 26, 2008
    Date of Patent: May 29, 2012
    Assignee: Aerojet-General Corporation
    Inventor: Melvin J. Bulman
  • Publication number: 20120031071
    Abstract: The invention relates to a system for controlling a plurality of actuators (15) that can displace a mobile panel (13, 17) pertaining to a nacelle (1) of an aircraft, said system comprising at least two motors (16) that can drive the actuators (15). The system also comprises two separate control units (33, 35), each unit being configured in such a way as to control and feed at least one motor that is not fed or controlled by the other control unit. The invention also relates to a nacelle comprising such a system.
    Type: Application
    Filed: April 6, 2010
    Publication date: February 9, 2012
    Applicants: HISPANO SUIZA, AIRCELLE
    Inventors: Hakim Maalioune, Vincent Le-Coq, Pierre Moradell-Casellas, Djemouai Hadjidj, Guillermo Garcia Soto
  • Patent number: 8091335
    Abstract: A swept fan ramp for a pivot door thrust reverser includes a cylindrical unit with an elliptical flared portion, a side portion, and a rectangular flared portion. The elliptical flared portion is operable to reduce drag on airflow in a reverse direction and is coupled to the top center and bottom center of the circumference of the cylindrical unit. The side portion is operable to reduce side spillage airflow and is coupled to the central left side and central right side of the aft circumference of the cylindrical unit. The rectangular flared portion is operable to promote separation of airflow into an upper airflow path and a lower airflow path, is coupled with the aft circumference of the cylindrical unit, and is connected to the elliptical flared portion and the side portion.
    Type: Grant
    Filed: February 14, 2008
    Date of Patent: January 10, 2012
    Assignee: Spirit AeroSystems, Inc.
    Inventor: Joe E. Sternberger
  • Patent number: 8065868
    Abstract: A non-invasive system, method, and apparatus for control input prediction and state verification of an aircraft's fluidic vectoring exhaust is disclosed. The control system derives a desired vector state, then predicts and sets the fluidic injection input required to produce the desired vector state. A vectored state verification routine is used to determine the resulting vector state for feedback to the control system.
    Type: Grant
    Filed: December 22, 2006
    Date of Patent: November 29, 2011
    Assignee: Lockheed Martin Corporation
    Inventors: Rob S. Burgun, Kerry B. Ginn, Daniel N. Miller
  • Patent number: 8020367
    Abstract: 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 lower tips of the exhaust vane may be incorporated to sealingly engage a nozzle outer wall along upper and lower surfaces of the outer wall of the nozzle. The exhaust vane has flat or contoured vane sidewalls and contoured vane sidewalls may be concave. The exhaust vane may have transversely biased apart upper and lower vane sections extending transversely inwardly from the upper and lower tips of the exhaust vane respectively. The exhaust vane may be articulated having upstream and downstream sections separately sideways pivotable about the vane pivot axis and a second pivot axis downstream of and parallel to the vane pivot axis respectively.
    Type: Grant
    Filed: March 16, 2007
    Date of Patent: September 20, 2011
    Assignee: General Electric Company
    Inventors: Michael Jay Toffan, James Lee Salmon, Ronald Clement Hollett, Arthur McCardle
  • Patent number: 7980058
    Abstract: 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 turbo-charged air compressor to generate high temperature and high pressure gas in the pressure chamber, and uses the reaction thrust force generated by ejecting the compressed air through the nozzle to make the aircraft vertically take off/land, suspend in the air and fly forwardly. Benefited from the simple structure, the manufacture cost of the aircraft engine can be dramatically decreased. Vertically raising and landing the aircraft can be achieved by changing the ejection directed of the compressed air in the pressure chamber. The commonly used gasoline or diesel, which is cost saving and capable of combusting with a high combustion value, can be used instead of the expensive aviation kerosene. Further, the generated noise is quite small.
    Type: Grant
    Filed: April 19, 2006
    Date of Patent: July 19, 2011
    Inventor: Stanley Chang
  • Patent number: 7975466
    Abstract: 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) and radially inner flaps (26) which are circumferentially disposed around the engine. The radially outer flaps (25) and radially inner flaps (26) alternately overlap each other to define a path through which the exhaust gases flow. The radially outer flaps (25) can be moved asymmetrically about the engine centre line (8). The radially inner flaps (26) are maintained in sealing contact with the outer flaps (25) by the flow of exhaust gases passing therethrough. The radially inner flaps (26) are divided into a number of triangular sections (29) which renders the flaps (26) torsionally flexible so that they can twist along their lengths to maintain sealing contact with adjacent radially outer flaps (25) when the outer flaps (25) are moved asymmetrically.
    Type: Grant
    Filed: December 26, 1991
    Date of Patent: July 12, 2011
    Assignee: Rolls-Royce plc
    Inventor: Leonard John Rodgers
  • Publication number: 20100313544
    Abstract: A propulsion system includes a canted multinozzle plate, which has a multitude of small nozzles angled (not perpendicular) to major surfaces of the multinozzle grid plate. The multinozzle plate may be a cylindrical section or plate, and the multitude of nozzles may be substantially axisymmetric about the cylindrical plate. The propulsion system includes a pressurized gas source which may be placed either forward or aft of the multinozzle grid plate. The propulsion system may have a conical insert, an internal flow separator cone, to aid in changing directions of flow from the pressurized gas source, to divert the flow through the multiple nozzles.
    Type: Application
    Filed: November 6, 2006
    Publication date: December 16, 2010
    Inventors: Daniel Chasman, Stephen D. Haight
  • Patent number: 7836681
    Abstract: 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. This linkage includes a first arm fixed to a first one of the vanes to pivot therewith about a first pivot axis, a second arm and a third arm fixed to a second one of the vanes to pivot therewith about a second pivot axis, and a fourth arm fixed to a third one of the vanes to pivot therewith about a third pivot axis. A first connecting link pivotally couples the first arm and the second arm together, and a second connecting link pivotally couples the third arm and the fourth arm together. The relative angular positioning of the arms with respect to the corresponding pivot axes and/or the arm links can be varied to define different vectoring schedules with the mechanism linkage.
    Type: Grant
    Filed: June 13, 2006
    Date of Patent: November 23, 2010
    Assignee: Rolls-Royce Corporation
    Inventors: Kenneth M. Pesyna, Jeffrey P. Henkle
  • Patent number: 7835828
    Abstract: Method for the computer-assisted determination of an optimum-fuel control of nozzles according to a control instruction b=Ax. A defined matrix transformation of starting constraints for the mass flow of the nozzles and of the minimization criterion thereby takes place in a computer-assisted manner, a data processing representation of a geometric description of the matrix-transformed starting constraints, a computer-assisted determination of limiting point sets of the geometric description of the starting constraints through a computer-assisted geometric search procedure in the vector space and the application of the matrix-transformed minimization criterion to the points of the limiting point sets.
    Type: Grant
    Filed: June 9, 2008
    Date of Patent: November 16, 2010
    Assignee: Astrium GmbH
    Inventor: Peter Zentgraf
  • Publication number: 20100212288
    Abstract: A first trailing edge portion of a scarfed jet engine exhaust nozzle aft of a second trailing edge portion relative to a central axis of an associated exhaust duct causes an automatic nozzle-pressure-ratio responsive transverse deflection of the associated exhaust flow away from the first trailing edge portion. When offset from both the center of gravity (CG) and the central longitudinal axis of an aircraft, at a relatively low nozzle pressure ratio, e.g. during takeoff, the thrust vector from the exhaust flow acts relatively close to the CG, whereas at a relatively high nozzle pressure ratio, e.g. during relatively high-speed cruise, the scarfed exhaust nozzle deflects the exhaust flow so that the resulting thrust vector is relatively parallel to the path of the aircraft. With the final portion of the exhaust duct skewed, the primary axis of the jet engine can be relatively parallel to the path of the aircraft.
    Type: Application
    Filed: August 20, 2009
    Publication date: August 26, 2010
    Applicant: WILLIAMS INTERNATIONAL CO., L.L.C.
    Inventors: Mark L. SUCHEZKY, Lisa M. SIMPKINS
  • Patent number: 7770379
    Abstract: The present invention provides an actuating apparatus for moving relatively rotatable components. In one embodiment the apparatus comprises: a bearing (30) including first (34) and second (36) relatively rotatable bearing elements for mounting respective first (18) and second (12) rotatable components for relative rotation about a common axis; a pneumatic or hydraulic actuator having a pair of co-acting parts (44, 54), including a first part (54) fixed with respect to the said first rotatable element and a second part (44) fixed with respect to the said second rotatable element; and, means (110) for energising and/or de-energising said actuator means to effect movement of the said co-acting parts and thereby relative rotation of the said first and second bearing elements about the said bearing axis.
    Type: Grant
    Filed: September 15, 2006
    Date of Patent: August 10, 2010
    Assignee: Rolls-Royce PLC
    Inventor: Michael C. Roberts
  • Patent number: 7716912
    Abstract: 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 propellant mass flow discharge rate. A varying total valve area is computed from an error between the commanded propellant mass flow discharge rate and a calculated propellant mass flow discharge rate. The valves are reconfigured according to a distribution of the varying total valve area. The propulsion system includes a pressure vessel with valves and a controller for regulating the valve area according to a propellant mass flow discharge rate from the pressure vessel.
    Type: Grant
    Filed: March 2, 2006
    Date of Patent: May 18, 2010
    Assignee: Alliant Techsystems Inc.
    Inventors: Cary Lee Cover, Sean Scott Stroud, Michael Joseph Piovoso, Timothy James Kelly
  • Publication number: 20100089031
    Abstract: A vectoring nozzle with external actuation generates thrust vectoring by applying mechanical or fluidic actuation, or both, on the nozzle deck, external sidewalls, and/or air vehicle aft body to produce changes in the aft body flowfield and/or exhaust plume. An external mechanical sidewall may be integrated into a nozzle deck or side walls without the need for engine bleed to supply fluid injectors. An external fluidic vectoring system uses injectors or plasma devices located aft of the nozzle exit to vector the exhaust plume with no external moving parts. Elements of both mechanical and fluidic systems may be combined for a given application.
    Type: Application
    Filed: October 10, 2008
    Publication date: April 15, 2010
    Applicant: LOCKHEED MARTIN CORPORATION
    Inventors: David M. Wells, Brent N. McCallum, Kerry B. Ginn, Stewart A. Jenkins
  • Publication number: 20090320445
    Abstract: According to the invention, under braking of an aircraft (AC) with reverse thrust, that (those) engine(s) (Mc) of said aircraft (AC) the associated control lever (4c) of which is (are) not in a reverse thrust position (I) is (are) set to low idle speed.
    Type: Application
    Filed: June 26, 2009
    Publication date: December 31, 2009
    Applicant: AIRBUS France
    Inventor: Alain Dupre
  • Publication number: 20090282806
    Abstract: An engine assembly includes a gas-turbine engine having a tailcone portion and a bypass duct, a rocket engine combustion assembly located at the tailcone portion of the gas-turbine engine, and a movable nozzle segment subassembly that is selectively engageable with the gas-turbine engine bypass duct in an open position and with the rocket engine combustion assembly in a closed position.
    Type: Application
    Filed: February 15, 2006
    Publication date: November 19, 2009
    Applicant: United Technologies Corporation
    Inventor: Eric Jahnsen
  • Patent number: 7599768
    Abstract: Method for the computer-assisted determination of an optimum-fuel control of nozzles according to a control instruction b=Ax. A defined matrix transformation of starting constraints for the mass flow of the nozzles and of the minimization criterion thereby takes place in a computer-assisted manner, a data processing representation of a geometric description of the matrix-transformed starting constraints, a computer-assisted determination of limiting point sets of the geometric description of the starting constraints through a computer-assisted geometric search procedure in the vector space and the application of the matrix-transformed minimization criterion to the points of the limiting point sets.
    Type: Grant
    Filed: March 17, 2004
    Date of Patent: October 6, 2009
    Assignee: EADS Astrium GmbH
    Inventor: Peter Zentgraf
  • Patent number: 7581381
    Abstract: 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 mechanism (18), the air splitter mechanism (18) being arranged to divert the air stream into two or more subsidiary streams for delivery to respective jet nozzles (9) of the plant. The plant may be used in a vehicle such as an aircraft in order to provide a vertical take-off and hover capability as well a level flight power source.
    Type: Grant
    Filed: June 27, 2003
    Date of Patent: September 1, 2009
    Assignee: Vtol Technologies Limited
    Inventor: Ashley Christopher Bryant
  • Patent number: 7578472
    Abstract: An ejection seat having pitch, roll, and yaw control provided by three separate rocket motors where each rocket motor has a fixed nozzle and the entire rocket motor is rotated about a single axis corresponding to the minimum principal moment of inertia of the rocket. Actuation for each rocket motor is by means of a hydraulic rack and pinion actuator. Power for the hydraulic actuators is provided by a unique hydro-pneumatic amplifier that converts stored gas energy into pressurized hydraulic fluid. The high pressure hydraulic fluid is directed through conventional servo valves into the appropriate actuators to provide main, roll, pitch, and yaw thrust as required to achieve upright orientation and vertical flight.
    Type: Grant
    Filed: June 2, 2006
    Date of Patent: August 25, 2009
    Assignee: AMI Industries, Inc.
    Inventor: Brad Mastrolia
  • Patent number: 7559507
    Abstract: Aircraft systems having thrust reversers with locking assemblies are disclosed herein. In one embodiment, an aircraft system includes a fan casing and a thrust reverser attached to the fan casing. The fan casing includes a first member. The thrust reverser includes a nozzle inner wall, a second member proximate to the nozzle inner wall for engaging with the first member, and a locking member positioned proximate to the first member. The locking member is movable between (a) a first position in which the first member is positioned between the locking member and the second member such that the locking member inhibits disengagement of the first and second members, and (b) a second position in which the locking member does not inhibit disengagement of the first and second members. The first member can be a V-groove, and the second member can be a V-blade.
    Type: Grant
    Filed: June 27, 2005
    Date of Patent: July 14, 2009
    Assignee: The Boeing Company
    Inventors: Geoffrey E. Harrison, Joe E. Sternberger, Michael K. Lallement, John T. Strunk, William S. Byrd, Darrell C. Jundt
  • Patent number: 7555893
    Abstract: 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 to a turbofan engine, the electrical generator is driven by output power of the turbofan engine to output electric power, and an electromagnetic driving fan is driven by the electric power. On the other hand, after bringing each of coils in the electromagnetic driving fan to a superconductive state, liquid hydrogen is introduced to a heat exchanger, collects the energy of exhaust as heat, is then vaporized, and thereafter supplied to a combustor and to a fuel cell. Further, the electromagnetic driving fan is changed in its rotational phase by a rotating mechanism portion, is made movable in a width direction of a wing and a wing chord direction by a slide mechanism portion, and can be stored inside or outside the wing by a storage mechanism portion.
    Type: Grant
    Filed: January 23, 2006
    Date of Patent: July 7, 2009
    Assignees: Japan Aerospace Exploration Agency, Nihon University
    Inventors: Keiichi Okai, Takeshi Tagashira, Ryoji Yanagi, Hiroshi Nomura
  • Patent number: 7555894
    Abstract: Swivelling nozzle for an aircraft engine, the nozzle 10 being pivotally mounted about a transverse yaw axis by means of two elastically deformable one-piece articulations 24 mounted on two external pivots 22 of the nozzle and housed in engine case elements, the nozzle being caused to pivot by an actuator 46 mounted on the engine case and connected by a link 50 to a pivot 22 of the nozzle.
    Type: Grant
    Filed: April 24, 2006
    Date of Patent: July 7, 2009
    Assignee: Snecma
    Inventors: Philippe Pierre Vincent Bouiller, Michel Francois Raymond Franchet, Jean-Pierre Ruis
  • Publication number: 20090151319
    Abstract: A method, system and apparatus for generating thrust. The method, system and apparatus can include a fuel that may be accelerated into one or more openings on a rotating wheel. The rotating wheel, which may be balanced, may then have a temporary increase in mass in one location on the wheel. Additionally, the fuel that is accelerated into one or more openings in the wheel may be decelerated and may exert an outward force on the wheel. This generation of force can be repeated and increased to provide thrust.
    Type: Application
    Filed: December 17, 2007
    Publication date: June 18, 2009
    Inventor: James Michael Fichera
  • Patent number: 7509797
    Abstract: 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 system for selectively varying distribution of air bled from the compressor into the exhaust nozzle for vectoring propulsion thrust.
    Type: Grant
    Filed: April 29, 2005
    Date of Patent: March 31, 2009
    Assignee: General Electric Company
    Inventor: James Edward Johnson
  • Patent number: 7481038
    Abstract: 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 layer of air. A vector slot injects cooling airflow into the exhaust passage normal to the primary stream. A cover plate partially blocks the vector slot to direct cooling airflow into the exhaust passage that in turn directs portions of the primary stream.
    Type: Grant
    Filed: October 28, 2004
    Date of Patent: January 27, 2009
    Assignee: United Technologies Corporation
    Inventors: Jack T. Blozy, Charles M. Willard, Nathan L. Messersmith, Miquel A. Velazquez
  • Publication number: 20090013664
    Abstract: An actuator arrangement comprises an actuator having a rotatable drive input, a motor, and a drive transmission arrangement for transmitting rotary drive from the motor to the rotatable drive input of the actuator, wherein the transmission arrangement includes a telescopic drive coupling.
    Type: Application
    Filed: March 28, 2008
    Publication date: January 15, 2009
    Applicants: Goodrich Actuation Systems Limited, Rohr Inc.
    Inventors: Tony Jones, John Herbert Harvey, Peter William Bacon, Mark Hubberstey, Brett John Wharton, Neil Charles Davies, Stephen Michael Roberts, Steven Andrew Wylie
  • Publication number: 20080250771
    Abstract: An actuator arrangement comprising a motor arranged to drive an input member, an extendable actuator having a rotatable shaft, a first drive transmission operable to transmit drive between the input member and the shaft when the shaft is under compression, and a second drive transmission operable to transmit drive between the input member and the shaft when the shaft is under tension, wherein the second drive transmission includes a ratchet mechanism.
    Type: Application
    Filed: April 8, 2008
    Publication date: October 16, 2008
    Applicant: Goodrich Actuation Systems Limited
    Inventor: Tony Jones