Rudders And Empennage Patents (Class 244/87)
  • Patent number: 10967951
    Abstract: A method of controlling an elevator of an aircraft includes selecting a factor for increasing or decreasing a predetermined horizontal tail load alleviation (HTLA) authority limit for an elevator based on at least one aircraft parameter. The HTLA authority limit decreases with an increase in Mach number and/or airspeed. The method also includes computing an elevator position limit as a product of the HTLA authority limit and the factor, and moving the elevator to a commanded elevator position that is no greater than the elevator position limit.
    Type: Grant
    Filed: October 30, 2017
    Date of Patent: April 6, 2021
    Assignee: The Boeing Company
    Inventor: Vedad Mahmulyin
  • Patent number: 10800515
    Abstract: A lower attachment system for a trimmable horizontal stabiliser actuator comprising: a ballnut for being disposed on a screwshaft of the actuator and forming a part of a primary load path of the lower attachment system; a trunnion connected to the ballnut and forming a part of the primary load path of the lower attachment system; a failsafe plate disposed about the trunnion and forming a part of a secondary load path; a secondary connection connected to the failsafe plate and forming a part of the secondary load path; a sheet plate attached to a first mounting point on the secondary connection and a second mounting point on the ballnut; and an adjustment mechanism provided with the sheet plate for adjusting the size or position of the sheet plate to adapt it to fit a distance between the first and second mounting points.
    Type: Grant
    Filed: April 27, 2018
    Date of Patent: October 13, 2020
    Assignee: GOODRICH ACTUATION SYSTEMS SAS
    Inventors: Thomas Moulon, Quentin Ricard
  • Patent number: 10704496
    Abstract: Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: July 7, 2020
    Assignee: The Boeing Company
    Inventor: Robert Michael Lee
  • Patent number: 10683080
    Abstract: The present disclosure relates to a sealing device and an associated flight control surface mechanism and an associated aircraft. According to an aspect of the present disclosure, a sealing device (100, 100?) for a flight control surface mechanism (10) of an aircraft (1) is provided, the flight control surface mechanism includes a fixed part (20) and a movable wing surface (40), the movable wing surface is attached to the fixed part in a manner of being movable relative to the fixed part. The sealing device includes a fixed seal (120) attached to the fixed part and a movable seal (140, 140?) attached to the movable wing surface so as to move with the movement of the movable wing surface, the movable seal and the fixed seal cooperate with each other in order to provide an aerodynamic sealing for the flight control surface mechanism.
    Type: Grant
    Filed: March 22, 2017
    Date of Patent: June 16, 2020
    Assignee: AIRBUS SAS
    Inventors: Feng Zhang, Li Guo
  • Patent number: 10611465
    Abstract: Provided are flight control mechanisms, such as omnidirectional thrust mechanisms (OTMs), and methods of using such mechanisms. These mechanisms may be positioned in wings, tails, or other components of aircraft. A mechanism may comprise a center member and top and bottom panels. The center member may comprise two curved segments joint at a center edge. The top and bottom panels may be independently pivotable relative to the center member. At high speeds, the top panel and/or the bottom panel may be pivoted outward to change the lift, drag, roll, and/or other flight conditions. The mechanism may also include a gas nozzle to direct compressed gas to the center member. The center member and/or the top and bottom panels redirect this gas resulting in forces in one of four directions, which are used for controlling the aircraft at low speeds, down to hover.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: April 7, 2020
    Assignee: The Boeing Company
    Inventor: Robert Michael Lee
  • Patent number: 10584751
    Abstract: A load reduction assembly includes an annular bearing cone configured to extend between a bearing assembly and a frame assembly and form a first load path therebetween. The load reduction assembly further includes an annular recoupler member configured to extend between the bearing assembly and the frame assembly and form a second load path therebetween. The second load path is parallel to the first load path. The recoupler member includes a shape memory alloy configured to change stiffness in response to a change in a stress condition, thereby regulating an imbalance condition of a rotor shaft coupled to the bearing assembly.
    Type: Grant
    Filed: December 19, 2018
    Date of Patent: March 10, 2020
    Assignee: General Electric Company
    Inventors: Shuvajyoti Ghosh, Akash Joshi, Shivaram AC, Ravindra Shankar Ganiger, Praveen Sharma
  • Patent number: 10273735
    Abstract: An apparatus for opening and closing a deck lid of a vehicle body includes a jack-screw type drive unit having two elongated relatively rotatable drive elements which are threadably engaged for bi-directional displacement. An electric motor engages the rotatable drive element. A first mounting device pivotally connects the rotatable drive element to a relatively fixed point on the vehicle. A second mounting device pivotally connects the non-rotatable drive element to the deck lid, or vice versa. The motor is energized to affect bi-directional control of the drive unit while enabling low back-drive effort. A concentric spring counters loading due to the weight of the deck lid.
    Type: Grant
    Filed: December 28, 2015
    Date of Patent: April 30, 2019
    Assignee: STRATTEC POWER ACCESS LLC
    Inventors: Jeffrey S. Hamminga, Waldemar Wawrzyniec Gmurowski
  • Patent number: 10023294
    Abstract: According to one embodiment, an empennage attachment system features an aft attachment mechanism and a forward attachment system. The aft attachment mechanism is configured to be coupled to a tail section of a body of an aircraft and to an empennage proximate to an aft spar of the empennage. The aft attachment mechanism defines a pitch axis such that the aft attachment mechanism allows the empennage to rotate about the pitch axis. The forward attachment system is configured to be coupled to the tail section of the body and to the empennage proximate to a forward spar of the empennage. The forward attachment system is configured to restrict rotation of the empennage about the pitch axis to an allowable range of motion.
    Type: Grant
    Filed: June 23, 2015
    Date of Patent: July 17, 2018
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Matthew Carl VanBuskirk, Michael Scott Seifert, Michael Christopher Burnett, Mark Loring Isaac
  • Patent number: 9873503
    Abstract: Tailplanes and empennages for aircraft are disclosed. An exemplary tailplane disclosed includes a stabilizer having a fixed shape and an elevator movably secured to the stabilizer. The elevator is movable from a neutral position relative to the stabilizer. The stabilizer and the elevator define an airfoil cross-sectional shape having a positive camber when the elevator is in the neutral position. The positive camber of the airfoil cross-sectional shape may facilitate movement of the elevator during some flight conditions. Also disclosed are tailplanes having camber distributions that vary along the spans of the tailplanes.
    Type: Grant
    Filed: July 21, 2014
    Date of Patent: January 23, 2018
    Assignee: LEARJET INC.
    Inventors: Reuben Chandrasekharan, Nick Iarocci, Shermineh Vafa, Iyad Akel
  • Patent number: 9745053
    Abstract: An aerodynamic component which in particular is suitable for use in an aircraft includes an outer skin sheet having an inner surface and an outer surface and being provided with perforation openings allowing a flow of air therethrough. The outer surface of the outer skin sheet forms an aerodynamic surface of the aerodynamic component. The aerodynamic component further includes a sandwich panel which includes an outer layer facing the inner surface of the outer skin sheet, an inner layer facing away from the inner surface of the outer skin sheet and a foam core sandwiched between the outer layer and the inner layer. The sandwich panel is provided with connection openings extending through the sandwich panel between the outer layer and the inner layer and allowing a flow of air therethrough.
    Type: Grant
    Filed: November 10, 2015
    Date of Patent: August 29, 2017
    Assignee: Airbus Operations GmbH
    Inventor: Benjamin Teich
  • Patent number: 9718534
    Abstract: An aircraft lifting surface attached to the rear or frontal end of the aircraft fuselage with a variable sweep angle ? in an inboard part and with a constant sweep angle ?1 in an outboard part. The aircraft lifting surface can be for example a horizontal tail plane or a vertical tail plane attached to the rear end fuselage or a canard attached to the frontal end fuselage.
    Type: Grant
    Filed: July 16, 2013
    Date of Patent: August 1, 2017
    Assignee: Airbus Operations S.L.
    Inventors: Angel Pascual Fuertes, Sergio Rodriguez Sanchez
  • Patent number: 9694900
    Abstract: An actuator assembly includes an actuator body, a ram, and a cross pin. The actuator body has an internal axial cavity bounded by an actuator body wall and defines a pivot axis. A longitudinal slot extends along a portion of the length of the actuator body wall and is in communication with the internal axial cavity. The ram is slidably received within the axial cavity of the actuator body. The cross pin is mounted to the ram and extends laterally from the ram and into the longitudinal slot for converting linear motion of the ram into rotational motion about the pivot axis for displacing a control surface of an air vehicle.
    Type: Grant
    Filed: March 27, 2014
    Date of Patent: July 4, 2017
    Assignee: Simmonds Precision Products, Inc.
    Inventor: Martin E. Buttolph
  • Patent number: 9561844
    Abstract: A method for providing a controllable side force to an air vehicle having a vertical stabilizer arrangement includes (a) selectively causing the vertical stabilizer arrangement to generate a first side force in a first side direction to provide the controllable side force, the first side force inducing a corresponding first yaw moment in a first yaw direction; and (b) selectively providing to the air vehicle a second yaw moment in a second yaw direction, the second yaw moment being induced by a force component of an auxiliary force applied to the air vehicle, the force component being in a force direction that is non-parallel with respect to the first side direction and the force component being spaced from a center of gravity of the air vehicle; wherein the second yaw direction is opposed to the first yaw direction. Also disclosed is a corresponding auxiliary yaw generating system.
    Type: Grant
    Filed: July 18, 2012
    Date of Patent: February 7, 2017
    Assignee: Israel Aerospace Industries Ltd.
    Inventors: Itzhak Yogev, Michael Shepshelovich, Danny Abramov
  • Patent number: 9090325
    Abstract: A supplementary control surface structure for airplanes is installed atop the fuselage of an airplane to enhance the roll rate of the airplane and thereby assists in reducing bending loads on the wings by enabling a smaller aileron deflection for a given roll rate. The supplementary control surface structure desirably includes a moveable vertically oriented roll control surface member desirably installed in a vertically oriented fin or strake that extends atop the fuselage from the flight deck to the vertically oriented tail fin. The supplementary control surface structure is desirably interconnected with the conventional aileron controls of the airplane in order to operate in concert with the ailerons. The supplementary control surface structure is also adaptable to other roll control systems, such as spoilers and wing warping.
    Type: Grant
    Filed: September 30, 2014
    Date of Patent: July 28, 2015
    Inventor: Ahmad Abdullah Al-Jassem Qanaei
  • Patent number: 8960594
    Abstract: Apparatus and methods for controlling yaw of a rotorcraft in the event of one or both of low airspeed and engine failure are disclosed. A yaw propulsion provides a yaw moment at low speeds. The yaw propulsion device may be an air jet or a fan. A pneumatic fan may be driven by compressed air released into a channel surrounding an outer portion of the fan. The fan may be driven by hydraulic power. Power for the yaw propulsion device and other system may be provided by a hydraulic pump and/or generator engaging the rotor. Low speed yaw control may be provided by auxiliary rudders positioned within the stream tube of a prop. The auxiliary rudders may one or both of fold down and disengage from rudder controls when not in use.
    Type: Grant
    Filed: October 27, 2011
    Date of Patent: February 24, 2015
    Assignee: Groen Brothers Aviation, Inc.
    Inventor: David L. Groen
  • Patent number: 8960599
    Abstract: A tail section for an aerospace vehicle is provided. The tail section comprises a rudder which is movable about an axis to generate a yawing moment on the aerospace vehicle. The tail section further comprises a thruster having, in flow series, an air intake, an electrically powered device for accelerating the air received through the intake, and an air outlet which directs the accelerated air to increase the yawing moment generated by the rudder.
    Type: Grant
    Filed: July 5, 2011
    Date of Patent: February 24, 2015
    Assignee: Rolls-Royce PLC
    Inventors: Huw L. Edwards, Stephen M. Husband, Paul Fletcher
  • Publication number: 20150048215
    Abstract: An apparatus forming an aircraft which is designed for flight by movement through the air, the aircraft has a front and rear portions and a center of mass, with left and right sides when divided by a central plane of reference. The aircraft has inboard portions closer to said central plane of reference and outboard portions farther from said central plane of reference. Further, the aircraft contains at least one positive lifting aerodynamic surface configured to affect the flow of air near said at least one positive lifting aerodynamic surface when said aircraft is appropriately moving forward, and at least one elevon structure configured to create negative aerodynamic force when said aircraft is appropriately moving forward. The elevon structure is constructed so as to have outboard portions thereof positioned outward of said central plane of reference to a distance at least three-fourths of the distance from said central plane of reference to a tip end of said at least one wing.
    Type: Application
    Filed: April 30, 2013
    Publication date: February 19, 2015
    Inventor: John William McGinnis
  • Patent number: 8944366
    Abstract: An aircraft is disclosed having an engine and a propeller mounted to a fuselage. An empennage mounts to the aircraft and includes first and second horizontal stabilizers separated by a distance greater than the diameter of a stream tube of the propeller at the horizontal stabilizers. A rudder extends between the horizontal stabilizers and is positioned within the stream tube of the propeller. A bulkhead is positioned rearwardly from the cockpit and oriented perpendicular to a longitudinal axis of the airframe. A tailboom and engine are mounted to the airframe by means of the bulkhead having the engine mounted between the tailboom and a lower edge of the bulkhead. Landing gear may mount to the bulkhead proximate a lower edge thereof.
    Type: Grant
    Filed: September 6, 2012
    Date of Patent: February 3, 2015
    Assignee: Groen Brothers Aviation, Inc.
    Inventor: Jacob Johannes van der Westhuizen
  • Patent number: 8936216
    Abstract: The invention relates to a composite structuring panel (1) for the trailing edge of an aircraft element, having: an upper surface (3); a lower surface (5); an edge (7) connecting said upper (3) and lower (5) surfaces; the upper surface (3) and the lower surface (5) being connected by transverse stiffeners (9) and the structuring panel being made of a unitary part forming the upper surface (3), the lower surface (5), the edge (7), and the transverse stiffeners (9). The invention also relates to a method for manufacturing such a panel (1), and to an aircraft element comprising such a panel (1).
    Type: Grant
    Filed: May 28, 2010
    Date of Patent: January 20, 2015
    Assignee: Societe Lorraine de Construction Aeronautique
    Inventors: Didier Remene, Denis Millepied, Paulo Francisco, Valérian Montagne, Jean-Luc Pacary, Arnaud Bertrand
  • Patent number: 8888039
    Abstract: The stabilizing device (1) comprises auxiliary stabilizers (6) which are mounted on the horizontal tailplane (2) of the aircraft and which generate a lateral stabilizing effect when brought into a deployed position.
    Type: Grant
    Filed: July 13, 2011
    Date of Patent: November 18, 2014
    Assignee: Airbus Operations SAS
    Inventors: Pierre-Emmanuel Gall, Christophe Cros, Mickaël Lallemand
  • Patent number: 8876044
    Abstract: An aircraft having an elongated fuselage and a lifting surface fastened to the fuselage. The aircraft has a device for controlling the torque around the yaw axis GZ of the aircraft in which aerodynamic forms that have devices to generate aerodynamic drag are fastened to each end of the lifting surface at non-zero distances from each side of a vertical plane of symmetry XZ of the aircraft. The drag-generating devices are commanded to produce a different aerodynamic drag at each of the two ends to generate a yaw torque on the aircraft. The aerodynamic forms, for example, have winglets improving the aerodynamics of the lifting surface, and are provided with aerodynamic drag generators.
    Type: Grant
    Filed: July 30, 2010
    Date of Patent: November 4, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Olivier Cazals, Thierry Druot
  • Publication number: 20140312169
    Abstract: An aircraft apparatus is disclosed that has a fuselage boom having proximal and distal ends, a wing coupled to a proximal end of the fuselage boom and at least one transparent stabilizer coupled to a distal end of the fuselage boom.
    Type: Application
    Filed: February 19, 2014
    Publication date: October 23, 2014
    Inventors: Christopher Eugene Fisher, Steven Bradley Chambers, Pavil Belik, Austin Craig Gunder, John Peter Zwaan
  • Patent number: 8857764
    Abstract: Techniques and apparatus for providing a fly away caul plate are disclosed. In an embodiment, a method for curing a composite structure includes placing a pre-cured caul plate proximate an uncured composite lay-up, the lay-up may or may not include one or more stiffeners extending substantially perpendicular to the lay-up surface, the caul plate including an aperture for receiving the at least one stiffener. A force may be exerted against the caul plate to engage the composite lay-up. Heat and/or pressure may be applied to the composite lay-up to cure the stiffener panel and co-bond the caul plate to the composite lay-up.
    Type: Grant
    Filed: August 9, 2012
    Date of Patent: October 14, 2014
    Assignee: The Boeing Company
    Inventors: Thomas A. Albertson, Karl R. Bernetich, Robert J. Freeman
  • Patent number: 8844874
    Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising a balancer fitting, three lugs and a waiting link. When there is a failure in one of the lugs, the balancer fitting acts supporting loads in the transversal direction of the aircraft. The waiting link only acts if a failure in other link occurs. This waiting link is able to support loads in the longitudinal direction of the aircraft.
    Type: Grant
    Filed: October 5, 2011
    Date of Patent: September 30, 2014
    Assignee: Airbus Operations, S.L.
    Inventors: José Maria Pina López, Pablo Timoteo Sanz Martinez
  • Patent number: 8814083
    Abstract: An aircraft (1) provided with a tail boom (4) including a tail plane (100) provided with an airfoil surface (5), the airfoil surface (5) being provided with at least one stabilizer portion (11, 12) extending laterally outside the tail boom (4) and with a central portion (13) extending inside the tail boom (4), said stabilizer portion (11, 12) being implanted in an orifice (6, 7) of the tail boom (4) that is defined by a peripheral wall (6?, 7?), clearance (21, 22) existing between said stabilizer portion (11, 12) and said peripheral wall (6, 7). The aircraft includes combating means (30) for combating the flutter phenomenon, which means are provided with stiffener means (31, 32) exerting predetermined compressive stress on said stabilizer portion (11, 12), said stiffener means (31, 32) being arranged at the root of the stabilizer portion (11, 12).
    Type: Grant
    Filed: October 17, 2011
    Date of Patent: August 26, 2014
    Assignee: Airbus Helicopters
    Inventors: Rodolphe Lhermenault, Thomas Meyer, Jean Azeau, Julien Guitton
  • Patent number: 8814085
    Abstract: A fault-tolerant actuating system with at least one flap, adjustable on a respective wing of an aircraft, and with a control and monitoring device, includes: drive devices that are functionally connected to the control and monitoring device, with one of these drive devices in each case being associated with a flap, where each flap in each case is associated with a drive device, in each case including: two drive motors, two brake mechanisms, where each drive motor is associated with a brake mechanism for stopping rotation of the output of the respective drive motor, a differential that couples the outputs of the aforesaid to the aforesaid in a summing manner, an output shaft for coupling the output of the differential to drive connections, and a differential lock that is functionally connected to the control and monitoring device, which differential lock is coupled to the control and monitoring device in this manner, where each of the brake mechanisms as well as the differential lock can be operated by way of
    Type: Grant
    Filed: May 5, 2009
    Date of Patent: August 26, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Martin Richter, Andreas Fleddermann
  • Patent number: 8800915
    Abstract: A device for boundary layer suction on the outer skin of an aircraft, on which outer skin a surface where drawing off by suction can take place comprising openings is connected to a suction source by way of at least one suction line, wherein the surface where drawing off by suction can take place is formed by at least one panel-shaped composite component that comprises an extruded profile, made of light metal, as a base body, which extruded profile comprises several suction channels that are open towards the outer skin, onto which base body, for the purpose of forming the outer skin, a micro-perforated metal cover sheet has been applied in the region of the surface where drawing off by suction can take place.
    Type: Grant
    Filed: March 30, 2012
    Date of Patent: August 12, 2014
    Assignee: Airbus Operations GmbH
    Inventor: Martin Gerber
  • Patent number: 8783606
    Abstract: A method for improving the aerodynamic efficiency of the vertical tail of an aircraft includes varying the thickness of the trailing edge of the rudder as a function of the span of the vertical tail. This variation is intended to adapt the local value of the coefficient of lateral lift applied to the vertical tail closer to a maximum allowable value. The maximum allowable value is specifically the value at which a separation of the aerodynamic flow is observed on the surface of the vertical tail.
    Type: Grant
    Filed: April 4, 2012
    Date of Patent: July 22, 2014
    Assignee: Airbus Operations (SAS)
    Inventor: Alain Tanguy
  • Patent number: 8783618
    Abstract: Weathertight fitting (41) for the mounting of the tail vertical stabilizer of an aircraft in a rear area of its fuselage, the construction being based on a casing (5) made with a composite material as one unitary piece and some frames (7) that are comprised of: one first piece (43) comprised of two bodies (45, 45?), that include the mounting lugs (47, 47?) for the tail vertical stabilizer and some vertical walls (49, 49?) for joining the fitting (43) to the frames (7) of the fuselage, and a weathertight central profile (51); two pairs of additional pieces (55, 55?; 65, 65?) of angular shape, that include some horizontal walls (57, 57?; 67, 67?) for joining to the casing (5) and some vertical walls (59, 59?; 69, 69?) for joining to the aforementioned bodies (45, 45?). All the weathertight fitting's (41) pieces are made with a composite material.
    Type: Grant
    Filed: July 20, 2011
    Date of Patent: July 22, 2014
    Assignee: Airbus Operations S.L.
    Inventors: Enrique Vera Villares, Elena Arévalo Rödríguez, José Maria Pina López, Javier Cabeza Huertas, Diego Folch Cortés
  • Patent number: 8783604
    Abstract: An aircraft wing has hinged ribs, and a skin covering the ribs. The ribs each include plural rib sections, array from the leading edge of the wing, to the trailing edge of the wing, and a lock to hold the rib sections together in a deployed state or condition. The wings are initially in a stowed state, with the ribs and the rib sections having a curved chord, and deploy to the deployed state, in which the ribs have a straightened chord that defines an airfoil state. The wing may have foam material between the ribs to allow the wings to expand in the wingspan direction, for instance after the ribs have been placed in the deployed state.
    Type: Grant
    Filed: October 21, 2011
    Date of Patent: July 22, 2014
    Assignee: Raytheon Company
    Inventors: Terry M. Sanderson, Michael S. Cherry, Jack W. Reany
  • Patent number: 8757538
    Abstract: An aircraft having a variable geometry for adapting the flight characteristics to different flight situations includes a fuselage with a pair of wings projecting on both sides of the fuselage in the transverse direction (y), each of which wings has an inner wing section arranged stationarily with respect to the fuselage and an outer wing section adjacent thereto and pivotable about a pivot axis. The pivot axis is oriented in a direction deviating from the longitudinal direction (x) of the aircraft by a maximum of 40°.
    Type: Grant
    Filed: October 10, 2011
    Date of Patent: June 24, 2014
    Assignee: EADS Deutschland GmbH
    Inventor: Jost Seifert
  • Patent number: 8752789
    Abstract: A method for controlling control surfaces. A position limit is identified for movement of a control surface based on a load limit set for the control surface and a number of vehicle current operation parameters to form an identified position limit. Responsive to receiving a command to move the control surface on a vehicle to a new position, the control surface is commanded to move to a position within the identified position limit.
    Type: Grant
    Filed: December 16, 2012
    Date of Patent: June 17, 2014
    Assignee: The Boeing Company
    Inventors: Chuong B. Tran, Kioumars Najmabadi, Edward E. Coleman, David W. Grubb
  • Patent number: 8733696
    Abstract: A method for enhancing aerodynamic efficiency of a vertical tail includes varying the ratio between the control surface local chord and the vertical stabilizer local chord along the height of the vertical tail. This variation is configured to adapt the local value of the coefficient of the side lift applied to the vertical tail to a maximum acceptable value of the side lift coefficient. As a result, the aerodynamic efficiency is maximized by applying a coefficient approaching the maximum acceptable side lift coefficient.
    Type: Grant
    Filed: May 17, 2010
    Date of Patent: May 27, 2014
    Assignee: Airbus Operations (SAS)
    Inventor: Alain Tanguy
  • Patent number: 8726652
    Abstract: A rotational actuator assembly employs a drive torque actuator having a shape memory alloy (SMA) tube with a first trained twist direction and a return actuator having a SMA tube with an opposite trained twist direction collinear with the drive torque actuator with abutting proximal ends. A central fitting joins the proximal ends. A control system employs a position sensor for the drive torque actuator and the torque sensor for the return actuator for combined antagonistic rotation of the central fitting.
    Type: Grant
    Filed: July 27, 2011
    Date of Patent: May 20, 2014
    Assignee: The Boeing Company
    Inventor: Ian M. Gunter
  • Patent number: 8720817
    Abstract: Apparatus and methods provide for an aircraft empennage that utilizes two torque tube members to create opposing sides of the empennage. The torque tube members are connected using a bridging member that is attached at opposing ends to the top portions of the torque tube members. The torque tube members and bridging member provide structural support for access cut-outs within the aircraft skin between the torque tube members for access to a payload space within. The torque tube members may include any number of walls, any of which may provide a pressure barrier to the payload space.
    Type: Grant
    Filed: December 3, 2012
    Date of Patent: May 13, 2014
    Assignee: The Boeing Company
    Inventors: Max Kismarton, Aaron J. Kutzmann, Kevin Lutke
  • Publication number: 20140103159
    Abstract: Aircraft comprising a single wing suspended under a closed sided chassis. The wing spar is mounted to the sides that enclose and channel the airflow over and under the wing to provide lift. Airflow is provided by a source located in front of the wing by means of either propeller, ducted fan or similar devise. Engines mounted on a rotational engine mount can provide downward thrust to lift front of craft to obtain an angle great enough for lift-off Once aircraft has sustained-angle for lift off engine(s) rotate to produce airflow parallel to wing for flight. Rudders mounted behind the air source and prior to the wing provide steering.
    Type: Application
    Filed: October 17, 2012
    Publication date: April 17, 2014
    Inventor: Wayne Curtis Bert
  • Patent number: 8684315
    Abstract: An active winglet includes a body portion substantially parallel to a wing of an aircraft, as if it were an extension of the wing. The body portion is attachable to an aircraft wing and includes a controllable airflow modification device coupled thereto. By virtue of having a controllable airflow modification device, the winglet is capable of adjusting a control surface of the controllable airflow modification device in response to in-flight conditions, to reduce wing loads, increase range, and/or increase efficiency.
    Type: Grant
    Filed: March 30, 2011
    Date of Patent: April 1, 2014
    Assignee: Tamarack Aerospace Group, Inc.
    Inventor: Nicholas R. Guida
  • Publication number: 20140077029
    Abstract: An easily removable and lightweight horizontal stabilizer configured to provide aerodynamic stability for a rotorcraft. The horizontal stabilizer comprising a spar removably coupled to a tailboom with a removable spar attachment means, the spar being located transversely through a tailboom opening and configured to provide structural support for at least a first horizontal airfoil and a second horizontal airfoil. The first and second horizontal airfoils are configured to fittingly receive the spar so that the spar fits at least partially inside the first and second horizontal airfoils. The first and second horizontal airfoils extend outboard from the tailboom to provide aerodynamic pitch stability.
    Type: Application
    Filed: November 25, 2013
    Publication date: March 20, 2014
    Inventors: William D. Dennison, Carl A. May
  • Publication number: 20140077026
    Abstract: A pitch stabilizer [10] equipped with an upper stabilizer surface [15] and a lower stabilizer surface [20], with the upper stabilizer surface [15] being located in an upper plane [P1] and with the lower stabilizer surface [20] being located in a lower plane [P2], with the upper plane [P1] overhanging the lower plane [P2]. The upper stabilizer surface [15] is rotatable about an upper axis of rotation [AX1], with the said lower stabilizer surface [20] being rotatable about a lower axis of rotation [AX2], with the stabilizer means [10] having linking means [30] whereby a rotary movement of one stabilizer surface causes an equal rotary movement of the other stabilizer surface.
    Type: Application
    Filed: September 17, 2013
    Publication date: March 20, 2014
    Applicant: EUROCOPTER
    Inventor: Frederic Beroul
  • Patent number: 8651422
    Abstract: A fuselage section for the pressure fuselage of an aircraft which comprises a fuselage shell structure and at least one pressure bulkhead made of a fiber composite material, the pressure bulkhead being formed in one piece with the fuselage shell structure. A fuselage shell comprising at least one fuselage section of this type.
    Type: Grant
    Filed: January 31, 2011
    Date of Patent: February 18, 2014
    Assignee: Airbus Operations GmbH
    Inventors: Torsten Noebel, Birgit Willms
  • Patent number: 8613409
    Abstract: A trailing edge aerodynamic airfoil of a load-bearing aerodynamic surface of an aircraft of the crocodile type has two airfoil flaps, with each flap being integral in a forward section with a rotational shaft that determines the axis of rotation of the airfoil flap. In a position called the zero setting, the airfoil flaps are essentially joined and form a rear section of the load-bearing surface, and each airfoil flap is movable in translation independently of the other airfoil flap, relative to the load-bearing surface, with each flap being entrained in rotation relative to the load-bearing surface around its axis of rotation by the motion in translation. The ends of the rotational shaft have extensions guided by runners fastened to these ends and acting conjointly with racks fastened to the load-bearing surface.
    Type: Grant
    Filed: November 8, 2010
    Date of Patent: December 24, 2013
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Olivier Cazals, Thierry Druot
  • Publication number: 20130320137
    Abstract: A rudder system for an aircraft includes a centre box, a rudder and actuators, wherein the rudder is pivoted around a hinge line relative to the centre box. The actuators are arranged at an acute angle relative to the hinge line, and connected with at least one pivoted pivot lever, wherein the pivot lever is fastened to the rudder by way of a first push rod. This provides considerably more installation space in a vertical stabilizer of an aircraft for a centre box, so that the latter can comprise a distinctly smaller wall thickness than usual in prior art to absorb air load-induced torsion and bending stresses.
    Type: Application
    Filed: May 10, 2013
    Publication date: December 5, 2013
    Applicant: AIRBUS OPERATIONS GMBH
    Inventor: Christian Maenz
  • Patent number: 8579230
    Abstract: An aircraft engine assembly including a turboshaft engine with a propeller and an attachment pylon intended to be laterally attached on a rear portion of the structure of the aircraft is disclosed. The pylon has an outer surface forming an aerodynamic profile incorporating a trailing edge which is arranged upstream of the propeller of the turboshaft engine. The pylon includes a mobile rear flap at least partially defining the trailing edge and a controller which steers the incidence of the flap according to a law depending on the incidence of the aircraft.
    Type: Grant
    Filed: April 1, 2011
    Date of Patent: November 12, 2013
    Assignee: AIRBUS Operations S.A.S.
    Inventors: Lionel Diochon, Steve Bedoin, Damien Prat
  • Patent number: 8573539
    Abstract: The invention comprises a triform fitting 1, essentially made from non-metallic composite materials including several strengthening cross ribs 4 for joining symmetrical flanges 3 and a longitudinal flange 2. The symmetrical flanges 3 include cross slots 8 for receiving the run-out 16 of the webs 11 of several T-shaped internal stringers 9 that form part of the torsion boxes 6. The feet 10 of the stringers 9 are joined along one of their faces to the skins 7 of the torsion boxes 6, while the end zones of the free faces of said feet 10 are placed against the outer face of the symmetrical flanges 3 of the triform fitting 1. This ensures that the symmetrical flanges 3 of the triform fitting 1 remain inside the torsion boxes 6. Alternatively, the fitting 1 may not include the cross slots 8.
    Type: Grant
    Filed: September 25, 2012
    Date of Patent: November 5, 2013
    Assignee: Airbus Operations, S.L.
    Inventor: Francisco Javier Honorato Ruíz
  • Patent number: 8573530
    Abstract: A rear tail assembly for an aircraft, including a fuselage, a wing and at least one propulsion engine attached in the rear portion of the fuselage located behind the wing along the X longitudinal axis of the aircraft, wherein the aforementioned assembly includes aerodynamic surfaces connected in the rear portion of the fuselage. The tail assembly essentially includes horizontal aerodynamic surfaces and essentially vertical aerodynamic surface arranged so as to form an annular structure including at least one ring attached to the fuselage. At least one engine is held in the ring formed by the tail assembly. In one embodiment, a central fin is used for defining two rings in the annular structure. In particular embodiments of an aircraft including such a tail assembly, one or two engines can be fitted in the ring area.
    Type: Grant
    Filed: November 29, 2007
    Date of Patent: November 5, 2013
    Assignee: Airbus Operations SAS
    Inventors: Olivier Cazals, Thierry Druot
  • Patent number: 8561948
    Abstract: A method for ensuring the safety of an aircraft flying horizontally at low speed includes an operation in which, when the flaps of the aircraft are disposed in a maximum extended position and are blown on by airscrews, the flaps are at least partially retracted, automatically, based on whether the thrust of the engines is at least equal to a predetermined lift value.
    Type: Grant
    Filed: November 27, 2006
    Date of Patent: October 22, 2013
    Assignee: Airbus Operations SAS
    Inventor: Stephane Chardon
  • Patent number: 8550398
    Abstract: Optimization of structures subjected to hot gas streams. The invention refers to a fairing (10) for aircraft horizontal stabilizer (3) comprising a front part (11) and a rear part (12), the front part (11) covering a limited extent of the fairing (10) surface, which is the part of the fairing (10) receiving hot air stream (6) coming from the aircraft engines (4), this front part (11) being made of an anti-erosion material, the rear part (12) covering the rest of the surface of the fairing (10), this rear part (12) being made of a material resisting the aerodynamic loads existing on the fairing (10). The invention also refers to an aircraft comprising a horizontal stabilizer (3) with a fairing (10) such as the one described.
    Type: Grant
    Filed: April 21, 2011
    Date of Patent: October 8, 2013
    Assignee: Airbus Operations S.L.
    Inventors: José Javier Almendros Gómez, Yolanda De Gregorio Hurtado
  • Patent number: 8544800
    Abstract: Methods and systems for efficiently increasing the wing area of an aircraft are disclosed herein. An integrated wingtip extension configured in accordance with one embodiment of the invention includes a tapered wing section and a winglet. The tapered wing section includes an inboard end portion having a first chord length and an outboard end portion having a second chord length that is less than the first chord length. The winglet is fixedly attached to the outboard end portion. The inboard end portion is configured to be fixedly attached to a tip portion of an aircraft wing. In one embodiment, the tapered wing section and the winglet can be integrally formed from composite materials.
    Type: Grant
    Filed: July 21, 2005
    Date of Patent: October 1, 2013
    Assignee: The Boeing Company
    Inventor: Victor K. Stuhr
  • Patent number: 8496203
    Abstract: An aircraft includes, but is not limited to a central fuselage body without horizontal stabilizer, at least one high-lift control surface, at least one vertical stabilizer that is arranged on the central fuselage body and at least one extendable compensation control surface. The compensation control surface may be moved independently of the high-lift control surface of the aircraft and generates a positive tail-heavy pitching moment when it is moved into the flow against the aircraft. Due to this measure, a negative pitching moment during the actuation of high-lift control surfaces may be at least partially eliminated without influencing the high lift. Rudder segments that may be moved opposite to one another on two vertical stabilizers that are arranged mirror-symmetrical referred to the longitudinal axis of the aircraft preferably are used for this purpose.
    Type: Grant
    Filed: October 27, 2010
    Date of Patent: July 30, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Malte Schwarze, Andreas Westenberger
  • Patent number: 8490925
    Abstract: A wing tip device for a wing includes a root and a tip, and the following determinant characteristics: the local dihedral of the wing tip device continuously increases or decreases from the root to the tip; the local sweep of the trailing edge continuously increases along its progression from the root to the tip of the wing tip device; where the local sweep of the leading edge continuously increases in the progression of the leading edge from the root to a first intermediate point; continuously decreases from the first intermediate point to a second intermediate point; and continuously increases from the second intermediate point at least to a region before of the tip of the wing tip device; as well as a wing comprising a wing tip device.
    Type: Grant
    Filed: April 30, 2010
    Date of Patent: July 23, 2013
    Assignee: Airbus Operations GmbH
    Inventors: Alexander Buescher, Michael Karwin, Frank Theurich