Patents Assigned to Textron
  • Hub Assembly with Grease Lubricated Roller Bearing and Tension-Torsion Strap
    Publication number: 20130164129
    Abstract: A rotary system and method to control feathering and centrifugal forces of a rotor blade during flight. The rotary system having a hub assembly, which includes a hollow yoke arm to receive a spindle section of the rotor blade. A tension-torsion strap extends through the hollow yoke arm and couples the rotor blade and the hub assembly. The method includes allowing the spindle section of the rotor blade to pivot within the hollow yoke arm and controlling rotational and centrifugal movement of the rotor blade with the tension-torsion strap.
    Type: Application
    Filed: December 26, 2011
    Publication date: June 27, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Richard Rauber, Frank B. Stamps, David Popelka, Patrick Tisdale, Tom Donovan
  • Dual Gain Digital Engine Control
    Publication number: 20130166169
    Abstract: An engine control system having an engine, a digital engine control, and a gain logic disposed within the digital engine control for use with an aircraft. The digital engine control is configured to receive and process inputs from systems within the aircraft. Gain logic uses the inputs to generate command data to regulate the performance of the engine so as to allow rotor speed deviations from a set point.
    Type: Application
    Filed: December 26, 2011
    Publication date: June 27, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: James M. McCollough
  • System and Method of Tuning a Liquid Inertia Vibration Eliminator
    Publication number: 20130161884
    Abstract: A vibration isolator includes an upper housing and a lower housing; an upper reservoir housing defining a upper fluid chamber; a lower reservoir housing defining a lower fluid chamber; a piston spindle resiliently coupled to the upper housing with an upper elastomer member, the piston spindle being resiliently coupled to the lower housing with a lower elastomer member; an inertia track having a tuning passage, the inertia track being removably coupled to the piston spindle; and a tuning fluid disposed within the upper fluid chamber, the lower fluid chamber, and the tuning passage. The vibration isolator cancels vibratory forces at an isolation frequency, the isolation frequency being at least partially dependent upon a size of the tuning passage.
    Type: Application
    Filed: December 26, 2011
    Publication date: June 27, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Maurice D. Griffin, Scott Hemmen, Matt Ledbetter
  • Flight control system having a three control loop design
    Patent number: 8473124
    Abstract: A flight control system is configured for controlling the flight of an aircraft utilizing a three control loop design to robustly increase system performance. An inner loop comprises an improved linear quadratic regulator (LQR) search method, and an outer loop comprises a classic feedback summary gain design. A third loop comprises a steady state trim search method.
    Type: Grant
    Filed: November 8, 2005
    Date of Patent: June 25, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Shyhpyng Jack Shue, John J. Shillings
  • Aircraft wing extension and nozzle system
    Patent number: 8469308
    Abstract: A system and method to control flight of an aircraft. The aircraft having an engine with a rotatably nozzle assembly configured to create forward propulsion and yaw control of the aircraft. The engine exhaust passing through the nozzle is redirected with a valve disposed within the nozzle. Lift is created with a lift system carried by the wing of the aircraft. Additional lift is created during flight with a retractable wing extension disposed within the wing of the aircraft.
    Type: Grant
    Filed: September 2, 2011
    Date of Patent: June 25, 2013
    Assignee: Textron Innovations Inc.
    Inventors: Daniel B. Robertson, Kirk L. Groninga
  • AFT-LOADING AIRCRAFT WITH TWIN T-TAIL ASSEMBLY
    Publication number: 20130153708
    Abstract: An aft-loading aircraft with a twin T-tail assembly is provided. In one example embodiment, the aft-loading aircraft includes a fuselage portion having an aft opening with a cargo door, a first and second vertical stabilizer attached to the fuselage portion, and, a horizontal stabilizer transversely attached to the first and second vertical stabilizers.
    Type: Application
    Filed: July 22, 2011
    Publication date: June 20, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: John Brunken, JR.
  • System and Method of Optimizing a Composite System
    Publication number: 20130154162
    Abstract: The present application relates to a method and system for optimizing a composite system by electrically monitoring the reactive and physiological behavior of the resin binder in a composite system, so as to develop the desired properties of the resin during the cure process. A method of manufacturing a composite part can include assembling a composite preform with a resinous material and an open circuit. Further, the method can include subjecting the composite preform to a curing cycle so that a resin in the resinous material melts and closes the open circuit. Further, the method can include electrically monitoring a current through the resin during the curing cycle. Further, the method can include selectively controlling a manufacturing variable in response to the step of electrically monitoring the current through the resin.
    Type: Application
    Filed: December 15, 2011
    Publication date: June 20, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Stephen K. Bishop, Jacob J. Hart
  • Blade-Pitch Control System with Feedback Lever
    Publication number: 20130156575
    Abstract: The present application includes a blade-pitch control system for controlling a pitch angle of each of a plurality of blades on an aircraft rotor. A feedback lever associated with each blade is pivotally mounted to the rotating portion of a swashplate assembly. A pitch link connects an output arm of a lever to a pitch horn of a corresponding blade, and a feedback link connects the input arm of the lever to a yoke. Flapping motion of the yoke causes motion of the feedback link, and this motion causes corresponding rotation of the lever. Rotation of the lever causes motion of the pitch link, which changes the pitch angle of the attached blade. This provides for selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the blades.
    Type: Application
    Filed: December 14, 2011
    Publication date: June 20, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: Frank B. Stamps
  • Constant-Velocity Drive System for Gimbaled Rotor Hubs
    Publication number: 20130156580
    Abstract: A constant-velocity drive system for a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed. A rotary-wing aircraft having a rotary-wing aircraft rotor comprising a differential torque-splitting mechanism and a gimbal mechanism is disclosed.
    Type: Application
    Filed: November 14, 2012
    Publication date: June 20, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: BELL HELICOPTER TEXTRON INC.
  • SLEEVE FOR A PUNCH ASSEMBLY
    Publication number: 20130145916
    Abstract: A punch assembly includes a punch, a sleeve, a draw stud and a die. The sleeve adds rigidity to the draw stud, thereby reducing elastic deflection of the draw stud, reducing bending moment on the draw stud, reducing punching force, and extending the punch, draw stud and die fatigue life. The sleeve also aids in axial alignment of the punch, die and workpiece with a pilot hole drilled through a workpiece.
    Type: Application
    Filed: December 4, 2012
    Publication date: June 13, 2013
    Applicant: Greenlee Textron Inc.
    Inventor: Greenlee Textron Inc.
  • PUNCH PROFILE FOR A PUNCH, AND THE ASSEMBLY IN WHICH THE PUNCH IS USED
    Publication number: 20130145915
    Abstract: A punch assembly includes a punch, a sleeve, a draw stud and a die. The punch has a punch profile which provides a cutting edge that has a uniform “sharpness” along entire perimeter of the punch. The punch assembly provides additional punch-to-die clearance over what was done in the prior art. This reduces excessive punching forces which result from axial deflection of the draw stud and “tipping” of a large diameter punch as the draw stud deflects under a load.
    Type: Application
    Filed: December 4, 2012
    Publication date: June 13, 2013
    Applicant: Greenlee Textron Inc.
    Inventor: Greenlee Textron Inc.
  • Preventing Rotation of a Fixed Ring of a Swashplate
    Publication number: 20130149150
    Abstract: According to one embodiment, a rotor system, comprise a mating element, a sleeve, a first swashplate ring, a locking element, and a second swashplate ring. The mating element having a first plurality of grooves a first plurality of ridges. The sleeve is positioned inside the mating element such that the sleeve prevents rotation of the mating element about the sleeve while allowing the mating element to translate along the sleeve. The sleeve has a second plurality of grooves mating with the first plurality of ridges and a second plurality of ridges mating with the first plurality of grooves. The first swashplate ring is positioned around the mating element, and the locking element prevents. the first swashplate ring from rotating about the sleeve. The second swashplate ring is rotatable about the sleeve.
    Type: Application
    Filed: December 9, 2011
    Publication date: June 13, 2013
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Mark Wiinikka, Maurice Griffin, Charles Speller
  • Multiple-Yoke Main Rotor Assembly
    Publication number: 20130149151
    Abstract: The present application includes a main rotor assembly for an aircraft. The rotor assembly has a main rotor mast configured for rotation about a mast axis and two yokes pivotally connected to the mast for rotation therewith about the mast axis. Each yoke is independently pivotable relative to the mast about at least one flap axis that is generally perpendicular to the mast axis. In at least one embodiment, a torque splitter connects the yokes and allows for limited rotation of the yokes relative to each other about the mast axis. Each yoke is configured for the attachment of rotor blades extending generally radially relative to the mast axis.
    Type: Application
    Filed: December 13, 2011
    Publication date: June 13, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Richard E. Rauber, Frank B. Stamps, David A. Popelka, Patrick R. Tisdale, Tommie L. Wood
  • HUMIDITY CONTROL FOR ABRASIVE BLASTING SYSTEMS
    Publication number: 20130143470
    Abstract: An abrasive blasting system includes an air subsystem being adapted to provide pressurized air, a fluid subsystem being adapted to provide fluid, a mixer being adapted to mix the fluid with the pressurized air, and a media subsystem being adapted to provide abrasive media. The method includes pressurizing the air, mixing the fluid with the air, thereby changing the relative humidity of the air, and blasting a surface of a structure with abrasive media mixed with the fluid and the pressurized air.
    Type: Application
    Filed: July 14, 2011
    Publication date: June 6, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Stephen Bishop, Jimmy D. Amerson, Steven Millican
  • Multi-ratio rotorcraft drive system and a method of changing gear ratios thereof
    Patent number: 8454475
    Abstract: A multi-ratio rotorcraft drive system and a method of changing gear ratios thereof are disclosed. According to one embodiment, the multi-ratio rotorcraft drive system comprises a rotor system comprising one or more rotors and one or more engines. Each engine of the one or more engines is coupled to the rotor system through a multi-ratio transmission. The multi-ratio transmission comprises an output shaft coupled to the rotor system, an input shaft coupled to a respective engine of the one or more engines, a high speed clutch integrated into a high speed gear train, and a low speed clutch integrated into a low speed gear train. The high speed clutch and the low speed clutch are freewheeling clutches without a friction plate and are capable of disconnecting the output shaft and the input shaft in an overrunning condition when the output shaft spins faster than the input shaft.
    Type: Grant
    Filed: March 12, 2012
    Date of Patent: June 4, 2013
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Ryan T Ehinger, Carlos A Fenny, Charles J Kilmain, Eric A Sinusas, Kevin Worrell
  • PILOT CYCLIC CONTROL MARGIN DISPLAY
    Publication number: 20130134255
    Abstract: A system to control flight of an aircraft includes a rotor blade, an actuator operably associated with the rotor blade, a controller operably associated with the actuator, and a flight control system. The flight control system having a subsystem adapted to modify a flight control limit of the aircraft based upon detection of an impending hazardous flight condition and a display showing available flight control limits provided by modification of design control limits based upon the detection of the impending hazardous flight condition.
    Type: Application
    Filed: July 12, 2011
    Publication date: May 30, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Robert L. Fortenbaugh, Frank Conway, Jeffery S. Greenwood
  • FLIGHT CONTROL LAWS FOR AUTOMATIC HOVER HOLD
    Publication number: 20130138270
    Abstract: A system and method to control hovering flight of a rotary aircraft. The system including a lateral speed hold loop, a longitudinal loop, a vertical control loop, and a directional loop. The method includes defining a first flight envelope having a first groundspeed threshold; defining a second flight envelope having a second groundspeed threshold, the second flight envelope being defined within the first envelope; engaging a hover hold with a control law hover hold architecture as the aircraft enters the first flight envelope; and engaging a position hold with a control law position hold architecture as the aircraft enters the second flight envelope.
    Type: Application
    Filed: July 15, 2011
    Publication date: May 30, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventors: Kevin Thomas Christensen, Shyhpyng Jack Shue, Troy Sheldon Caudill
  • BLADE-PITCH CONTROL SYSTEM WITH FEEDBACK SWASHPLATE
    Publication number: 20130136596
    Abstract: A blade-pitch control system for controlling a pitch angle of blades on a rotor has an input swashplate assembly having non-rotating and rotating portions, the rotating portion being operably connected to blade grips. A feedback swashplate assembly has non-rotating and rotating portions, the rotating portion being connected to the yoke for movement with the yoke during flapping of the yoke. Linear actuators connect the non-rotating portion of the input swashplate assembly to the non-rotating portion of the feedback swashplate assembly. Motion of the yoke during flapping causes a corresponding motion of the feedback swashplate assembly and input swashplate assembly for providing selected pitch-flap coupling between flapping motion of the yoke and pitch motion of the grips.
    Type: Application
    Filed: May 20, 2011
    Publication date: May 30, 2013
    Applicant: BELL HELICOPTER TEXTRON INC.
    Inventor: Frank B. Stamps
  • Plastic canister
    Patent number: D684062
    Type: Grant
    Filed: July 30, 2012
    Date of Patent: June 11, 2013
    Assignee: Kautex Textron GmbH & Co. KG
    Inventors: Tom Schneider, Klaus Dörries
  • Plastic canister
    Patent number: D684471
    Type: Grant
    Filed: July 30, 2012
    Date of Patent: June 18, 2013
    Assignee: Kautex Textron GmbH & Co. KG
    Inventors: Tom Schneider, Klaus Dörries