Patents Assigned to Textron, Inc.
  • Patent number: 10822954
    Abstract: A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.
    Type: Grant
    Filed: October 25, 2018
    Date of Patent: November 3, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Paul K. Oldroyd, Drew Sutton, Andrew Maresh, Christopher Foskey
  • Patent number: 10823289
    Abstract: A duct interface system and method includes a duct having a first end and a second end; a first receptacle for the first end of the duct and/or a second receptacle for the second end of the duct; and one or more first seals between the first end of the duct and the first receptacle and/or one or more second seals between the second end of the duct and the second receptacle.
    Type: Grant
    Filed: November 17, 2017
    Date of Patent: November 3, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Keith David Weaver, David Angell, Nicholas Plagianos, Thomas Mast
  • Patent number: 10822075
    Abstract: The present invention includes a span-balance pocket in a surface of a rotor blade, the span-balance pocket including an inboard surface and an outboard surface; and one or more weights disposed in the span-balance pocket to span-balance the rotor blade; and at least one of one or more retention devices to retain the one or more weights against the outboard surface of the span-balance pocket or the span-balance pocket is machined or molded into a tip block of the rotor blade.
    Type: Grant
    Filed: July 31, 2017
    Date of Patent: November 3, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Paul Sherrill, Tim Ledbetter, Kelli Yates, Robert Self, Nathan Green, Russell Cole
  • Publication number: 20200340894
    Abstract: A method of offset load testing a tubular composite specimen with two pairs of aligned holes and having at least one defect, the method comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; securing the pair of arms using a fastener assembly in each of the two pairs of aligned holes; and moving the mobile arm to impart an offset load force to the tubular specimen. One aspect includes a method of offset load testing comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; providing a tubular composite specimen with a top portion and a bottom portion; securing the pair of arms to the top and bottom portions of the tubular composite specimen; and moving the mobile arm to impart an offset load force to the tubular composite specimen.
    Type: Application
    Filed: July 8, 2020
    Publication date: October 29, 2020
    Applicant: Bell Textron Inc.
    Inventors: Wei-Yueh Lee, Michael Burnett, Michael Dearman
  • Publication number: 20200339254
    Abstract: An aircraft rotor system including a hub having a hub axis about which the hub is configured to rotate; a plurality of rotor blades configured to extend from the hub and rotate about the hub axis, at least one of the rotor blades rotatable about a respective pitch change axis; wherein the hub is configured to be rotated about the hub axis only by the plurality of rotor blades. Another aspect includes a method of operating the rotor system.
    Type: Application
    Filed: July 10, 2020
    Publication date: October 29, 2020
    Applicant: Bell Textron Inc.
    Inventors: Alison Ann Davis, Charles Speller
  • Patent number: 10816085
    Abstract: A system is provided in one example embodiment and may include a first reservoir for a lubricant; a second reservoir for the lubricant, wherein the first reservoir and the second reservoir are interconnected; a first pumping element to pump the lubricant from the first reservoir at a first flow rate; a second pumping element to pump the lubricant at a second flow rate, wherein the first flow rate and the second flow rate are different; and a gearbox coupled to the first pumping element and the second pumping element. The first reservoir may have a larger volume than the second reservoir and the first flow rate may be higher than the second flow rate.
    Type: Grant
    Filed: January 18, 2018
    Date of Patent: October 27, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Eric S. Olson, David R. Bockmiller
  • Patent number: 10815008
    Abstract: A method for facilitating the design and manufacturing of a tiltrotor aircraft, including the steps of: determining a compatible mission data set; identifying lift propulsion module components for the compatible mission data set; determining compatible specifications; and generating a design for a lift propulsion module; wherein the lift propulsion module is configured to be connected to at least two different fuselages. There is also a method of designing a tiltrotor aircraft, comprising the step of modularizing a lift propulsion system, wherein the lift propulsion system is configured to be connected to at least two different fuselages. In another aspect, there is a tiltrotor aircraft including a fuselage; and a lift propulsion module, the lift propulsion module including a mounting surface; wherein the lift propulsion module is coupled to the fuselage on the mounting surface. Also included are methods of assembling and systems including a lift propulsion module.
    Type: Grant
    Filed: July 27, 2017
    Date of Patent: October 27, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Brent C. Ross, Kendall Goodman, Steven R. Ivans
  • Patent number: 10814567
    Abstract: In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a cavity with a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the cavity, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the cavity. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the cavity.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: October 27, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David G. Carlson, John R. McCullough, Douglas K. Wolfe, Andrew G. Baines, George R. Decker
  • Patent number: 10814960
    Abstract: A dynamic rotor-phasing unit can phase rotors in-flight for dynamic rotor tuning and in an idle state for aircraft storage. The input and output shafts can be clocked (e.g., rotated) from 0 degrees apart to in excess of 360 degrees apart or from 0 degrees apart to 140 degrees apart. Such rotation can minimize the footprint of an aircraft for stowing purposes, as the rotor blades can be folded to fit within a smaller area without disconnecting the drive system. Additionally, the unit can allow tiltrotor blades to be clocked during flight, which can allow the live-tuning of the aircraft's rotor dynamics. A fail-safe rotary actuator can rotate a stationary planet carrier to clock the input shaft and the output shaft. Alternatively, an actuator can position a slider housing to clock the input shaft and the output shaft.
    Type: Grant
    Filed: August 12, 2020
    Date of Patent: October 27, 2020
    Assignee: Bell Textron Inc.
    Inventors: Colton Gilliland, Tyson Henry
  • Patent number: 10814963
    Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.
    Type: Grant
    Filed: August 3, 2018
    Date of Patent: October 27, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: David E. Heverly, II, Jeremy DeWaters, Frank B. Stamps
  • Publication number: 20200333228
    Abstract: A notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer; isolating the notch; and selectively etching the notch to provide an etched surface of the notch; wherein at least a portion of the re-melt material layer has been removed from the notch. In one aspect, there is provided a notch treatment method for flaw simulation including providing the specimen with the notch, the notch having a re-melt material layer, the specimen includes steel or an alloy thereof; isolating the notch; and selectively etching the notch with a first etching solution and a second etching solution to provide an etched surface on the notch; wherein at least a portion of the re-melt material layer has been removed from the notch.
    Type: Application
    Filed: June 26, 2020
    Publication date: October 22, 2020
    Applicant: Bell Textron Inc.
    Inventors: Xiaoming Li, Bogdan R. Krasnowski, Robert A. Figueroa, Robert Wardlaw
  • Publication number: 20200331626
    Abstract: A detachable cargo mirror assembly for use on a rotorcraft surface that includes a bracket for mounting to a surface on the rotorcraft, the bracket comprising a base portion and a retainer portion having a first pair of opposing holes, an elongated arm having two opposing ends, a first end for coupling with the bracket and a second end coupled to a mirror apparatus, the first end having a passage; and a releasable connector that engages with the first pair of opposing holes and the passage in the elongated arm when the elongated arm is in a first position to display a desired image on the mirror apparatus. The detachable cargo mirror assembly can be removed or in a stowed position when not in use.
    Type: Application
    Filed: July 7, 2020
    Publication date: October 22, 2020
    Applicant: Bell Textron Inc.
    Inventors: Brian Lafon, Ricky Jenkins, Sean Morgan, William P. Sumner, William L. Neal
  • Publication number: 20200331216
    Abstract: In an aspect, there is a method of determining allowable defects for a composite component comprising identifying at least one wrinkle characteristic of a composite component wrinkle defect; making a first plurality of specimens each having a predetermined wrinkle defect representative of the composite component wrinkle defect; measuring each of the predetermined wrinkle defects in the first plurality of specimens for at least one performance metric to generate performance data; and generating an allowable wrinkle defect profile based on the performance data from the first plurality of specimens. In other aspects, there are methods of making a specimen with a predetermined wrinkle defect.
    Type: Application
    Filed: July 7, 2020
    Publication date: October 22, 2020
    Applicant: Bell Textron Inc.
    Inventors: Michael Burnett, Wei-Yueh Lee, Michael Dearman
  • Patent number: 10809281
    Abstract: A support bracket for grounding a current sensor is disclosed. The support bracket comprises a first surface and a second surface. The first surface is electrically coupled to a current sensor to provide a current path to ground the current sensor. The second surface is physically coupled to the current sensor in order to support the current sensor.
    Type: Grant
    Filed: August 30, 2018
    Date of Patent: October 20, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: David W. Fuessel, Russel Mark Berkley
  • Patent number: 10807705
    Abstract: In one embodiment, a rotor blade may comprise a blade body, a spar structure, and a blade nose. The blade body may comprise a skin, wherein the skin is configured to form an airfoil shape, and wherein the airfoil shape comprises an inboard end, an outboard end, a leading edge, and a trailing edge. The spar structure may comprise a first spar cap and a second spar cap, wherein the first spar cap is coupled to an upper portion of the skin, and wherein the second spar cap is coupled to a lower portion of the skin. The blade nose may comprise a cavity, wherein the cavity is configured to house a plurality of modular weights at a plurality of radial blade locations, wherein the plurality of radial blade locations comprises a range of locations between the inboard end and the outboard end.
    Type: Grant
    Filed: March 24, 2017
    Date of Patent: October 20, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Drew A. Sutton, Mark E. Wasikowski, Andrew Ryan Maresh, Nolan B. Phillips
  • Patent number: 10808826
    Abstract: A system for monitoring lubrication of a drive train, including a lubricant pressure sensor to detect a pressure of the lubricant in the drive train and to provide a lubricant pressure signal; lubricant volume sensor to detect a volume of the lubricant in the drive train and to provide a lubricant volume signal; non-contact temperature sensor to detect a temperature of the drive train and to provide a non-contact temperature signal; and logic management system in communication with the lubricant pressure sensor, the lubricant volume sensor, and the non-contact temperature sensor; the logic management system configured to receive and process the lubricant pressure signal, the lubricant volume signal, and the non-contact temperature signal; wherein when the lubricant pressure signal reaches a predetermined minimum pressure level and the lubricant volume signal reaches a predetermined minimum volume level, the logic management system displays non-contact temperature measurement data to a display device.
    Type: Grant
    Filed: June 15, 2018
    Date of Patent: October 20, 2020
    Assignee: Bell Helicopter Textron Inc.
    Inventors: John Brodnicki, Ron Woods
  • Publication number: 20200324885
    Abstract: A multimodal unmanned aerial system includes a fuselage forming a payload bay, a control wing forward of the fuselage including a first plurality of propulsion assemblies and a primary wing aft of the fuselage including a second plurality of propulsion assemblies. The primary wing has a greater wingspan than the control wing. The multimodal unmanned aerial system includes linkages rotatably coupling the fuselage to the control wing and the primary wing. The fuselage, the control wing and the primary wing are configured to synchronously rotate between a vertical takeoff and landing flight mode and a forward flight mode. The fuselage, the control wing and the primary wing are substantially vertical in the vertical takeoff and landing flight mode and substantially horizontal in the forward flight mode.
    Type: Application
    Filed: April 15, 2019
    Publication date: October 15, 2020
    Applicant: Bell Textron Inc.
    Inventor: Guy Bernard
  • Publication number: 20200324884
    Abstract: An exemplary rotorcraft includes a propulsion system including a prime mover and a drive shaft coupled to the prime mover, the drive shaft including a coupling separating the drive shaft into an input shaft and an output shaft, the coupling operable between an engaged position rotationally coupling the input shaft and the output shaft and a disengaged position rotationally disengaging the output shaft from the input shaft, a main rotor coupled to the prime mover, a secondary rotor attached to the output shaft, and a motor coupled to the output shaft.
    Type: Application
    Filed: April 11, 2019
    Publication date: October 15, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Matthew Michael Wilcox, Aaron Alexander Acee
  • Publication number: 20200325937
    Abstract: Embodiments are directed to solid lubricant assemblies for providing over temperature protection for bearings and gears in rotorcraft systems. A solid lubricant enters a fluid state above a certain temperature and is positioned so that fluid lubricant is applied to the bearings or gears.
    Type: Application
    Filed: April 11, 2019
    Publication date: October 15, 2020
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Tyler Wayne Baldwin, Kyle Thomas Cravener, Tyson Henry
  • Patent number: 10801624
    Abstract: The present invention includes a helicopter rotor seal assembly comprising: a rotor mast having a longitudinal axis and an outer surface; a sleeve aligned longitudinally with the axis and surrounding a portion of the rotor mast, the sleeve having an outer surface, and an inner surface; an annular horizontal seal between the inner surface of the sleeve and the outer surface of the rotor mast; and an upper annular rotor mast seal affixed to the outer surface of the rotor mast and extending outwardly sufficient to cover the annular horizontal seal.
    Type: Grant
    Filed: September 13, 2017
    Date of Patent: October 13, 2020
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventor: Scott David Poster