Patents Assigned to Textron
  • Increased Capacity Spherical Lined Bearings
    Publication number: 20130108447
    Abstract: A rotary system and method to control feathering movement of a rotor blade. The system having a yoke arm configured to rotate a rotor blade. A first bearing and a second bearing are utilized to secure the rotor blade to the yoke arm and are configured to restrict longitudinal and transverse movement, while allowing feathering movement of the rotor blade relative to yoke arm.
    Type: Application
    Filed: October 28, 2011
    Publication date: May 2, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Frank B. Stamps, Bryan W. Marshall
  • All glass fiber laser cladding mode stripper
    Patent number: 8433161
    Abstract: A system configured to generate an optical beam from a fiber laser is presented. The system includes a fiber gain medium having a core and a cladding, the core being configured to convert radiation from a pump beam into an output beam, the cladding having a mode propagating section and a mode stripping section bounded on a near end and a distal end by the mode propagating section, the mode stripping section of the cladding being configured to scatter excess pump radiation received from the mode propagating section in a substantially outwardly radial direction. The system also includes a rigid support member into which the fiber gain medium is placed, the rigid support member completely encompassing the mode stripping section of the cladding and joined to the fiber at the mode propagating section of the cladding.
    Type: Grant
    Filed: September 21, 2010
    Date of Patent: April 30, 2013
    Assignee: Textron Systems Corporation
    Inventors: Jason E. Langseth, Alexander E. Mandl
  • Constant-velocity joint with torque-combining differential
    Patent number: 8430757
    Abstract: A constant-velocity drive system for an aircraft rotor has a gimbal mechanism and a differential torque-combining mechanism. The gimbal mechanism has gimbals driven in rotation by a rotor mast about a mast axis, the gimbals providing for gimballing relative to the mast about gimbal axes generally perpendicular to the mast axis. The differential torque-combining mechanism is connected to the gimbal mechanism and configured to be driven in rotation about the mast axis by the gimbal mechanism. The differential mechanism is capable of gimballing relative to the mast about the gimbal axes, the differential torque-combining mechanism having an output component attached to a yoke of the rotor for driving the yoke in rotation with the differential torque-combining mechanism.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: April 30, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Frank B. Stamps, Patrick R. Tisdale
  • HYBRID OVERRUNNING CLUTCH ASSEMBLY AND METHOD OF MAKING SAME
    Publication number: 20130098732
    Abstract: A hybrid overrunning clutch includes a metal outer race and a composite outer ring that are each sized and configured such that the metal race generates a preload on the composite outer race throughout the operational temperature of the clutch. The composite outer ring significantly reduces that total weight of the clutch, as compared to a completely metal outer race. The present application further includes a method of assembling the metal outer race and composite outer ring so that thermal expansion of the metal outer race creates the preload in the composite outer ring. The present application also includes a method of designing a hybrid overrunning clutch.
    Type: Application
    Filed: September 14, 2012
    Publication date: April 25, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Ryan T. Ehinger, Eric S. Olson
  • Extended optical range system for monitoring motion of a member
    Patent number: 8428686
    Abstract: A system and method for monitoring a physiological parameter includes a garment that includes a fabric that exhibits both a light transmission property and a light reflection property. The amount of light transmitted through the fabric relative to the amount of light reflected by the fabric changes when the fabric stretches in response to motion, such as the motion induced by physiological activity (e.g., heart rate). The system includes at least one source of radiation having wavelength(s) in the range of 400 to 2200 nanometers and at least one detector responsive to such incident radiation. The source and detector are associated with the fabric such that the reception of incident radiation by the detector is directly affected by a change in the amount of light transmitted through the fabric relative to the amount of light reflected by the fabric when the fabric stretches.
    Type: Grant
    Filed: April 9, 2010
    Date of Patent: April 23, 2013
    Assignee: Textronics, Inc.
    Inventors: Chia Kuo, George W. Coulston
  • Rotor hub vibration attenuator
    Patent number: 8424799
    Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency.
    Type: Grant
    Filed: April 24, 2007
    Date of Patent: April 23, 2013
    Assignee: Textron Innovations Inc.
    Inventors: David A. Popelka, Richard E. Rauber, Frank B. Stamps
  • Method and Apparatus for Out-of-Autoclave Adhesive Shear Bonding of Structures
    Publication number: 20130092792
    Abstract: The shear bonding method is configured to facilitate bonding of structures in an out-of-autoclave environment. The shear bonding method includes bonding a plurality of frame members to the interior of a tapered tailboom. The frames are located on a bayonet type tool. An adhesive pack is applied to each frame. The bayonet type tool is inserted into the tailboom until the adhesive packs come into contact with the interior walls of the tailboom. Conductive heating tiles are applied to the tailboom. The conductive heating tiles are controlled to achieve and maintain viscosity of the adhesive packs. During this period the bayonet tool is actuated so that the frames are translated in relation to the tailboom. The heating tiles are then controlled to achieve and maintain the adhesive at a requisite curing temperature.
    Type: Application
    Filed: October 13, 2011
    Publication date: April 18, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Paul Oldroyd, James Donn Hethcock, Robert Clive Fews
  • METHOD FOR PRODUCING A FUEL CONTAINER FOR MOTOR VEHICLES AND FUEL CONATINER FOR MOTOR VEHICLES
    Publication number: 20130092317
    Abstract: A method for producing a fuel container and a fuel container for motor vehicles. The method comprises the extrusion of web-type preforms, the shaping of the preforms to form shell-shaped intermediate products in a first step, and forming a container in the same moulding tool in a second step, at least one tank-filling and/or operational venting device being fastened to the inner wall of at least one intermediate product between the first and second steps by a material and/or form-fitting joint in one work cycle, the wall of the intermediate product being penetrated by a connection fitting during assembly, with a use of at least one conduit section of variable length as a part of a vent line.
    Type: Application
    Filed: October 1, 2012
    Publication date: April 18, 2013
    Applicant: KAUTEX TEXTRON GMBH & CO. KG
    Inventor: KAUTEX TEXTRON GMBH & CO. KG
  • SYSTEM AND METHOD OF MANUFACTURING A STRUCTURE WITH A HIGH PERFORMANCE METAL ALLOY
    Publication number: 20130094919
    Abstract: The method of the present application includes machining complex part features in a flat metal sheet, and subsequently forming the machined flat metal sheet to have the desired shape and contours. Prior to the step of machining the complex part features, the method includes calculating a scaled location of the complex part features so that the subsequent forming step acts to translate and deform the complex part features into a desired location. The present application further includes a method for machining high performance metal alloy, such as titanium. Further, the present application includes a heated mandrel for applying heat to a high performance metal alloy, such as titanium, during stretch forming.
    Type: Application
    Filed: August 28, 2012
    Publication date: April 18, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Stephen K. Bishop, Stephen S. Swenson, Crystal L. Wilson, Paulette D. Lemond
  • SYSTEM AND METHOD OF MANUFACTURING A STRUCTURE
    Publication number: 20130091918
    Abstract: The system and method of the present application can include machining complex part features in a flat metal sheet, and subsequently forming the machined flat metal sheet to have the desired shape and contours. Prior to the step of machining the complex part features, the method can include calculating a scaled location of the complex part features so that the subsequent forming step acts to translate and deform the complex part features into a desired location.
    Type: Application
    Filed: August 28, 2012
    Publication date: April 18, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Stephen K. Bishop, Stephen S. Swenson, Crystal L. Wilson, Paulette D. Lemond
  • Extrusion blow molding machine and method for the production of a hollow plastic body
    Patent number: 8419993
    Abstract: The invention relates to an extrusion blow molding machine (1) with at least one extrusion head (2) and with at least two sheet dies (3), arranged next to one another, for the extrusion of sheet-like plastic preforms (4), with a multipart molding die (5) for processing two preforms into an essentially closed hollow body, having a device for handling the preforms (4). The device for handling the preforms comprises at least two grippers (10), arranged next to one another on a common carrier (8), for receiving the preforms (4), the distance between the grippers (10) being variable.
    Type: Grant
    Filed: May 6, 2008
    Date of Patent: April 16, 2013
    Assignee: Kautex Textron GmbH & Co. KG
    Inventors: Matthias Franke-Maintz, Klaus Maier, Frank Pritz
  • Crash attenuation system for aircraft
    Patent number: 8418957
    Abstract: A crash attenuation system for an aircraft, the system having an airbag carried by the aircraft and inflatable generally adjacent an exterior of the aircraft. The airbag has at least one vent for releasing gas from the interior of the airbag. A gas source is in fluid communication with the interior of the airbag for inflating the airbag with gas generated provided by the gas source. A vent valve is provided for controlling a flow of gas through each vent, each vent valve being selectively configurable between an open state, in which gas can pass through the associated vent from the interior of the airbag, and a closed state, in which gas is retained within the interior of the airbag. The gas source is provided for at least partially re-inflating the airbag after venting of gas through the at least one vent.
    Type: Grant
    Filed: May 18, 2011
    Date of Patent: April 16, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Michael R. Smith, Cheng-Ho Tho, Somen Chowdhury
  • Method of making a rotor yoke and rotor yoke thereof
    Patent number: 8419375
    Abstract: A method of making a rotor yoke includes preparing a cured composite rotor yoke preform on a single-sided curing tool and machining at least one portion of the cured rotor yoke preform to form a rotor yoke. In one embodiment, preparing the cured composite rotor yoke is accomplished by applying successive layers of uncured polymeric composite material to a single-sided tool in a configuration to produce an uncured rotor yoke preform; disposing a semi-rigid caul to an untooled side of the uncured rotor yoke preform; enclosing the uncured rotor yoke preform and the semi-rigid caul by substantially hermetically sealing a vacuum bag to the tool; substantially evacuating a volume defined by the vacuum bag and the tool of air; and heating the uncured rotor yoke preform, sometimes under pressure, to form the cured composite rotor yoke preform.
    Type: Grant
    Filed: January 31, 2008
    Date of Patent: April 16, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Tricia L. Hiros, Frank Bradley Stamps, Pat Tisdale, Ron Measom, Jim Braswell, Tom Campbell, Paul K. Oldroyd, Richard Barbour
  • ADAPTIVE TWIST SYSTEM FOR A ROTOR BLADE
    Publication number: 20130089422
    Abstract: The system of the present application includes an adaptive twist system for a rotor blade. The adaptive twist system includes a slider mechanism coupled to a spar and to a skin. The slider mechanism provides structural connectivity between the spar and the skin while also selectively translated the skin relative to the spar, thereby causing the rotor blade to twist. A control system is used to operate the slider mechanism so that the rotor blade is automatically twisted into the optional shape during changes in flight modes.
    Type: Application
    Filed: November 12, 2010
    Publication date: April 11, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: John E. Brunken, JR.
  • SYSTEM AND METHOD FOR MEASURING WRINKLE DEPTH IN A COMPOSITE STRUCTURE
    Publication number: 20130088222
    Abstract: In accordance with one embodiment, a method is provided for non-destructive examination of a composite structure having a non-conductive surface and a conductive substrate. The method may include applying an alternating current to a probe having a coil conductor, scanning the probe across the non-conductive surface to induce eddy currents in the conductive substrate, and measuring changes in an electrical property of the probe in response to changes in the eddy currents indicative of variations in the depth of the conductive substrate.
    Type: Application
    Filed: May 10, 2011
    Publication date: April 11, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: Jeffrey P. Nissen
  • SELF-ALIGNING INLET PLENUM SYSTEM FOR ROTORCRAFT
    Publication number: 20130087663
    Abstract: An inlet system for a rotorcraft includes a cowl door assembly and a plenum assembly. The cowl door assembly includes a door member, a cowl inlet opening, and a cowl inlet duct. The plenum assembly is configured to free float in relation to the cowl door. The plenum assembly includes a plenum duct with a plenum band configured to attach the plenum assembly to an inlet opening. An aft seal is located between the aft plenum flange and a firewall, the aft seal being configured to provide a compressive contact between the plenum assembly and the firewall.
    Type: Application
    Filed: April 28, 2011
    Publication date: April 11, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Zachary E. Dailey, Thomas M. Mast
  • AIRFOIL SHAPED TAIL BOOM
    Publication number: 20130087653
    Abstract: A tail boom adapted for counteracting a fuselage torque created by an engine carried by a fuselage of a rotary aircraft. The tail boom is positioned within the rotorwash from the rotary and includes a first side surface contoured to create a low-pressure region of an airfoil and a second opposing side surface contoured to create a high-pressure region of an airfoil. The pressure difference between the high-pressure region and the low-pressure region causes the tail boom to move towards the low-pressure region, resulting in a lateral force opposing the torque on the fuselage.
    Type: Application
    Filed: September 20, 2010
    Publication date: April 11, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Albert G. Brand, Jimmy Narramore, James H. Harse, Brendan P. Lanigan
  • FLIGHT CONTROL LAWS FOR FULL ENVELOPE BANKED TURNS
    Publication number: 20130090788
    Abstract: A flight control system and method for controlling full envelope banked turns of an aircraft, the flight control system including one or more of a control law architectures having one or more control laws adapted for controlling the flight of an aircraft for full envelope banked turns.
    Type: Application
    Filed: March 29, 2011
    Publication date: April 11, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill, Nicholas Dean Lappos
  • Hydraulically Operated Tool Including A Bypass Assembly
    Publication number: 20130081843
    Abstract: A bypass assembly varies the hydraulic motor revolutions per minute (rpm) of a hydraulically driven tool, such as a wrench or a drill. This controls the torque of a driven mechanical mechanism, such as used on an impact wrench. The tool includes a body having a supply channel capable of being connected a source of fluid, a bypass spool channel in fluid communication with the supply channel, and a return channel in fluid communication with the bypass spool channel via a port and in fluid communication with the source. A bypass spool seats in the bypass spool channel. The bypass spool can be rotated to three discrete positions within the bypass spool channel to provide three different settings of revolutions per minute (rpm) of the gear motor.
    Type: Application
    Filed: September 27, 2012
    Publication date: April 4, 2013
    Applicant: GREENLEE TEXTRON INC.
    Inventor: Greenlee Textron Inc.
  • METHOD AND APPARATUS FOR ACTIVELY MANIPULATING AERODYNAMIC SURFACES
    Publication number: 20130082136
    Abstract: A method and apparatus is provided, including an actuator system that may be connected to a wing frame for controlling an active element. The actuator system may include sliding elements movable along an axis parallel to the span-wise axis of the wing. The sliding elements may be connected to fixed elements and a crank element, the crank element generally comprising a beam element and a pivot element. The beam element may be offset from the pivot element so that the crank element is rotatable about the pivot element with a negative stiffness under an external force that tends to pull the sliding elements away from the fixed elements.
    Type: Application
    Filed: November 1, 2010
    Publication date: April 4, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Troy C Schank, Peter H Kintzinger, Paul B Sherrill, Thomas Parham