Patents Assigned to Textronics, Inc.
  • ADAPTABLE ROTOR CONTROL SYSTEM FOR A VARIABLE NUMBER OF BLADES
    Publication number: 20190375496
    Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.
    Type: Application
    Filed: August 21, 2019
    Publication date: December 12, 2019
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Gary Miller, Frank B. Stamps
  • Teetering rotor hub system
    Patent number: 10501175
    Abstract: The present invention includes a rotor hub system, comprising: a teetering rotor hub disposed about a mast, the teetering rotor hub comprising: a first and a second yoke; each connected to a set of rotor blades, wherein the second set of rotor blades and the first set of rotor blades are disposed in a common plane, but the first and the second yoke do not come in contact.
    Type: Grant
    Filed: January 9, 2017
    Date of Patent: December 10, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Drew Alan Sutton, Frank Brad Stamps
  • Hard stop apparatus for aimable devices
    Patent number: 10495288
    Abstract: The present invention includes a first frame attached to an aerial vehicle or a mounting plate attached to the aerial vehicle, and a second frame attached to an aimable device moveably connected to the aerial vehicle or the mounting plate. The first frame and the second frame are configured to collectively provide a hard stop that prevents the aimable device from pointing at the aerial vehicle.
    Type: Grant
    Filed: April 12, 2018
    Date of Patent: December 3, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventor: Francis Turgeon
  • System and method of rotorcraft usage monitoring
    Patent number: 10496787
    Abstract: A method of monitoring usage of a component of an aircraft can include: monitoring a usage of the component by using a torque measurement system to calculate torque events in a time period; categorizing the usage of the component by assigning a usage value based upon whether the number of torque events in the period of time is above or below a threshold; and determining a life used of the component.
    Type: Grant
    Filed: July 2, 2014
    Date of Patent: December 3, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Brian Tucker, Tom Wood, Robert Wardlaw, Bang Nguyen, Allen Altman
  • Hub bolt supported inboard bearing assemblies
    Patent number: 10494091
    Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a bearing cage, a shear bearing and a centrifugal force bearing. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. Hub bolts couple each of the bearing cages to the yoke such that the hub bolts provide centrifugal force load paths between the bearing assemblies and the yoke inboard of the inboard pockets.
    Type: Grant
    Filed: May 26, 2018
    Date of Patent: December 3, 2019
    Assignee: Bell Textron Inc.
    Inventors: Amarjit Olenchery Kizhakkepat, Robert Patrick Wardlaw, John Richard McCullough, Frank Bradley Stamps, Tyler Wayne Baldwin
  • Rotor hub with structural reinforcements
    Patent number: 10494090
    Abstract: In one embodiment, a rotor hub comprises a hub plate, a yoke for attaching a plurality of rotor blades, a plurality of yoke support bearings, and a plurality of cushioned damper bearings for attaching a plurality of dampers.
    Type: Grant
    Filed: September 8, 2017
    Date of Patent: December 3, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Jason C. Owens, Frank B. Stamps, Andrew Paul Haldeman, Robert P. Wardlaw, John R. McCullough, Gary Miller, Andrew Ryan Maresh, Drew A. Sutton
  • SYSTEMS AND METHODS FOR CONTROLLED FILTERING OF AIRCRAFT CONTROL INPUT
    Publication number: 20190359321
    Abstract: In one embodiment, a method is performed by a control computer. The method includes receiving a time series of control inputs in relation to a control axis of an aircraft, where the control computer causes actuation in response to each control input in the time series as the control input is received. The method also includes determining aircraft oscillation over a sample period corresponding to the time series. The method also includes evaluating information related to the determined aircraft oscillation using engagement settings associated with a control filter. The method also includes engaging the control filter responsive to the information satisfying the engagement settings, where the engaged control filter systematically attenuates future control inputs in relation to the control axis prior to actuation responsive thereto.
    Type: Application
    Filed: May 23, 2018
    Publication date: November 28, 2019
    Applicant: Bell Helicopter Textron Inc.
    Inventor: Jeffrey BOSWORTH
  • Inboard bearing assemblies having independent shoes
    Patent number: 10486807
    Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode includes a yoke having a plurality of blade arms each having an inboard pocket with a load transfer surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets. Each of a plurality of inboard beams is disposed at least partially between a centrifugal force bearing and a shear bearing of each bearing assembly and has a proprotor blade coupled thereto. Each of a plurality of independent shoes is coupled between one of the centrifugal force bearings and the yoke. Each shoe has a load transfer surface that has a contact relationship with the load transfer surface of the respective inboard pocket forming a centrifugal force load path therebetween.
    Type: Grant
    Filed: May 26, 2018
    Date of Patent: November 26, 2019
    Assignee: Bell Textron Inc.
    Inventors: Michael Dean Dearman, Amarjit Olenchery Kizhakkepat, Tyler Wayne Baldwin, Michael Christopher Burnett
  • Assisted Landing Systems for Rotorcraft
    Publication number: 20190351999
    Abstract: A propulsion assembly for a rotorcraft includes a blade assembly, a drive shaft coupled to the blade assembly and an electric motor coupled to the drive shaft and operable to provide rotational energy to the drive shaft to rotate the blade assembly. The propulsion assembly includes a landing assistance turbine coupled to the drive shaft and operable to selectively provide rotational energy to the drive shaft during an underpowered descent to rotate the blade assembly and provide upward thrust, thereby reducing a descent rate of the rotorcraft prior to landing.
    Type: Application
    Filed: May 17, 2018
    Publication date: November 21, 2019
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Frank Bradley Stamps, Michael K. McNair, John Richard McCullough
  • CONTROL SYSTEMS AND METHODS FOR ROTATING SYSTEMS
    Publication number: 20190352002
    Abstract: In one embodiment, a local control system for a rotor assembly of an apparatus includes a first actuator disposed in the rotor assembly and configured to control motion of a first controllable element in the rotor assembly. The rotor assembly is mounted to the apparatus and is rotated responsive to torque and rotational energy provided thereto. The local control system also includes a first sensor disposed in the rotor assembly and configured to provide position feedback in relation to the first controllable element. The local control system also includes a first local control computer disposed in the rotor assembly and communicably coupled to a first central control computer disposed in the apparatus external to the rotor assembly, where the first local control computer is configured to transmit a control signal to the first actuator and receive a feedback signal from the first sensor.
    Type: Application
    Filed: May 15, 2018
    Publication date: November 21, 2019
    Applicant: Bell Helicopter Textron Inc.
    Inventors: Kynn Jerald Schulte, Troy Cyril Schank
  • Rotorcraft control mode transition smoothing
    Patent number: 10481615
    Abstract: A method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time. In the first mode, the translational speed of the rotorcraft is determined based on a pilot stick signal, and in the second mode, an output of an attitude rate controller is proportional to an amplitude of the pilot stick signal.
    Type: Grant
    Filed: March 1, 2017
    Date of Patent: November 19, 2019
    Assignee: Bell Textron Inc.
    Inventor: Sung Kyun Kim
  • Aircraft tail with cross-flow fan systems
    Patent number: 10479495
    Abstract: In one aspect, there is provided an aircraft, including a fuselage having a longitudinal axis extending from a front portion through an aft portion; first and second tail members extending from the aft portion; a first cross-flow fan system rotatably mounted to the first tail member; and a second cross-flow fan system rotatably mounted to the second tail member. The first and second cross-flow fan systems are configured to provide a forward thrust vector and an anti-torque vector on the aircraft. The first and second cross-flow fan systems can have a rotational axis oriented generally vertically. In another aspect, there is an aircraft including a fuselage having a front portion and a tail portion; and a cross-flow fan system supported by the tail portion. Embodiments include a cross-flow fan system retrofittable onto an aircraft and methods for retrofitting an aircraft with a cross-flow fan system.
    Type: Grant
    Filed: April 10, 2017
    Date of Patent: November 19, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Kirk L. Groninga, Daniel B. Robertson, Matthew E. Louis
  • Exhaust manifold for combining system exhaust plume
    Patent number: 10480386
    Abstract: Disclosed herein is an aircraft that includes an exhaust manifold for combining one or more system exhaust paths located upstream of equipment inlets and directing the exhausts upwards towards the rotor linkages such that the exhaust is expelled and diffused forward of the equipment inlets. According to one aspect of the present disclosure, the exhaust manifold includes a structure for supporting a transmission cowling at the top of the aircraft and/or on the sides of the aircraft. For example, the exhaust manifold may include a platform that contains the exhaust ducts and may include a frame extending from the platform that follows the contours of the cowling, such that the cowling lays along the support frame for additional mechanical support.
    Type: Grant
    Filed: September 22, 2017
    Date of Patent: November 19, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Keith C. Pedersen, Brent Scannell, Nam Dai Tran, Thomas Mast
  • Roller bearing lubrication systems
    Patent number: 10480582
    Abstract: The present invention includes a rolling element bearing system and method of using the same, comprising: a ball bearing comprising an inner race coupled to an inner shaft (journal) at an outer surface of the inner shaft, an outer race coupled to an outer shaft at an inner surface of the outer shaft, and a roller element disposed between the inner race and the outer race, wherein the inner race and the outer surface of the inner shaft form a pocket between a portion of the inner race and the outer surface, and the inner race comprises an orifice through the inner race to fluidly connect the pocket and the rolling element.
    Type: Grant
    Filed: November 1, 2016
    Date of Patent: November 19, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brian Stanley Modrzejewski, Siddhesh Pradeep Raje, Kenneth Myron Jackson
  • Engagement member for splicing a spar assembly
    Patent number: 10479477
    Abstract: In one aspect, there is an engagement member for splicing a spar assembly in an aircraft wing including a joining portion having a first attachment for connecting to a first spar and a second attachment surface for connecting to a second spar; and a rib post extending from the joining portion and disposed between the first attachment surface and the second attachment surface. In an embodiment, the rib post is integral to the joining portion and is configured to couple with a rib web.
    Type: Grant
    Filed: February 3, 2017
    Date of Patent: November 19, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: James E. King, James E. Kooiman, Charles D. Hogue
  • Cable cutter system
    Patent number: 10479488
    Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.
    Type: Grant
    Filed: August 10, 2018
    Date of Patent: November 19, 2019
    Assignee: BELL TEXTRON INC.
    Inventors: Michael Smith, Cheng-Ho Tho, Anand Kumar Marimuthu
  • Inboard bearing assemblies having load transfer shoe bolts
    Patent number: 10479497
    Abstract: A proprotor system for a tiltrotor aircraft having helicopter and airplane flight modes includes a yoke having a plurality of blade arms each having an inboard pocket with an outboard surface. Each of a plurality of bearing assemblies is disposed at least partially within one of the inboard pockets with each bearing assembly including a shear bearing and a centrifugal force bearing having an integral shoe with an outboard surface. Each of a plurality of inboard beams is disposed at least partially between one of the centrifugal force bearings and one of the shear bearings. Each of a plurality of proprotor blades is coupled to one of the inboard beams. The integral shoes are coupled to the yoke such that there is a spaced apart relationship between the outboard surfaces of the integral shoes and the outboard surfaces of the pockets to prevent centrifugal force load transfer therebetween.
    Type: Grant
    Filed: May 26, 2018
    Date of Patent: November 19, 2019
    Assignee: Bell Textron Inc.
    Inventors: Robert Patrick Wardlaw, John Richard McCullough, Amarjit Olenchery Kizhakkepat, Tyler Wayne Baldwin
  • Rotor assembly with high lock-number blades
    Patent number: 10472057
    Abstract: An aircraft rotor assembly has a central hub and a plurality of rotor blades coupled to the hub for rotation with the hub about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is formed by a flexure coupling the associated blade to the hub. Each pivot is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the hub, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure produces a biasing force for biasing the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.
    Type: Grant
    Filed: February 14, 2017
    Date of Patent: November 12, 2019
    Assignee: Bell Helicopter Textron Inc.
    Inventors: Gary Miller, Frank B. Stamps, Jouyoung Jason Choi, Thomas C. Parham, Jr., Alan Ewing, Richard E. Rauber
  • Aircraft fleet maintenance system
    Patent number: 10474973
    Abstract: According to one example embodiment, an aircraft fleet maintenance system includes a maintenance analysis engine and an operator feedback system. The maintenance analysis engine is configured to receive, from each of a plurality of aircraft maintainers, feedback information associated with how each of the aircraft maintainers performed an aircraft maintenance action and to compile the received feedback information from two or more of the plurality of aircraft maintainers to yield compiled maintenance trend data. The operator feedback system is configured to transmit the compiled maintenance trend data to at least one of the plurality of aircraft maintainers.
    Type: Grant
    Filed: May 19, 2015
    Date of Patent: November 12, 2019
    Assignee: BELL HELICOPTER TEXTRON INC.
    Inventors: Brian Tucker, Brian Mesing
  • Inboard bearing assemblies for proprotor systems
    Patent number: 10472059
    Abstract: A proprotor system for a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a yoke having a plurality of blade arms with inboard pockets. A centrifugal force and shear bearing assembly is disposed in each of the inboard pockets of the yoke. Each of a plurality of proprotor blades is coupled to the yoke by one of the bearing assemblies such that each proprotor blade has a pitch change degree of freedom about a pitch change axis and a tilting degree of freedom about a focal point. Each bearing assembly includes a centrifugal force bearing coupled to the yoke, a shear bearing coupled to the yoke and an inboard beam coupled between the centrifugal force bearing and the shear bearing. Each inboard beam is coupled to a respective proprotor blade.
    Type: Grant
    Filed: July 13, 2017
    Date of Patent: November 12, 2019
    Assignee: Bell Textron Inc.
    Inventors: Kyle Thomas Cravener, Amarjit Kizhakkepat, Ken Shundo, Jared Mark Paulson, Tyler Wayne Baldwin