Patents Assigned to Textronics, Inc.
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Publication number: 20190130782Abstract: Systems and methods include providing a virtual reality (“VR”) flight teleport system that include a master aircraft and a plurality of remote slave aircraft connected through a network. A flight emulator in the master aircraft allows a user in the master aircraft to “teleport” into a remote slave vehicle in order to observe and/or assume control of the remote slave aircraft. Motion of, orientation of, and/or forces acting on the remote stave vehicle are emulated to the user of the master vehicle through a pilot control interface, a motion-control seat, and a head-mounted display to provide real-time feedback to the user of the master aircraft. Inputs made via the pilot control interface of the flight emulator system in the master aircraft are transferred through the network into the flight control system of the remote slave vehicle to control operation of the remote slave vehicle.Type: ApplicationFiled: March 27, 2018Publication date: May 2, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeffrey Paul Nissen, Daniel Brent McCall, Joshua Peter Riccobono
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Publication number: 20190130781Abstract: Systems and methods include providing a virtual reality (“VR”) flight emulator system that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. Motion, orientation, and/or forces experienced by the simulated vehicle are imparted to a user through a motion-control seat. Multiple flight emulators can be connected to a communication network, and a master flight emulator may teleport into a slave flight emulator in order to observe, overtake, override, and/or assume control of the slave flight emulator. Inputs made via the control interface of the master flight emulator or during playback of a pre-recorded training exercise or flight mission are translated into the control interface, head-mounted display, and motion-control seat of the slave flight emulator to provide real-time feedback to the user of the slave flight emulator.Type: ApplicationFiled: March 22, 2018Publication date: May 2, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeffrey Paul Nissen, Daniel Brent McCall, Joshua Peter Riccobono
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Publication number: 20190127054Abstract: A piston for use in a liquid inertia vibration elimination (“LIVE”) system. The piston includes a port that extends from a first end of the piston to an opposite second end of the piston, wherein a length of the port is longer than a length between the first and second ends of the piston.Type: ApplicationFiled: October 27, 2017Publication date: May 2, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Maurice D. Griffin, Taeoh Lee, John Frakes, Michael R. Smith, Scott Hemmen
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Publication number: 20190130783Abstract: Systems and methods include providing a virtual reality (“VR”) flight emulator that simulates control, operation, and response of a vehicle. The flight emulator includes a control interface and a head-mounted display worn by a user. The user of the flight emulator can virtually teleport into a slave virtual or remote aircraft in order to assume control of the slave virtual or remote aircraft. Motion of, orientation of, and/or forces acting on the slave virtual or remote aircraft are imparted to a user through a plurality of galvanic vestibular stimulation (GVS) devices when the user of the flight emulator is virtually teleported into the slave virtual or remote aircraft. The flight emulator can be connected through a communication network to a plurality of other flight emulators. The flight emulator can also be installed in an aircraft and connected through the communication network to a plurality of other remote aircraft.Type: ApplicationFiled: March 27, 2018Publication date: May 2, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeffrey Paul Nissen, Daniel Brent McCall, Joshua Peter Riccobono
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Publication number: 20190127059Abstract: There is provided a rotorcraft, including a body, including a front portion and a tail portion; a main rotor system coupled to the front portion of the body, the main rotor system operable to provide a lifting force on the body; and an anti-torque system coupled to the tail portion of the body, the anti-torque system including a primary tail rotor system and a secondary tail rotor system; wherein the primary tail rotor system and the secondary tail rotor system are operable to provide a first anti-torque force and a second anti-torque force. In other aspects, there are methods of providing anti-torque force in a rotorcraft.Type: ApplicationFiled: October 30, 2017Publication date: May 2, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Levi C. Hefner, Frank B. Stamps
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Publication number: 20190127082Abstract: Embodiments are directed to flight instrument warnings that are configured to automatically adjust a low airspeed warning band on an airspeed indicator based on available torque margin and radar altimeter height. Warnings may be presented on a primary flight display or on flight instruments when a low airspeed band is entered.Type: ApplicationFiled: October 26, 2018Publication date: May 2, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Erik John Oltheten, Thomas Wayne Brooks
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Patent number: 10275950Abstract: A system and method configured to monitor aircraft flight performance data. The system includes a wireless transmitter in data communication with an avionics system of the aircraft, a portable wireless transceiver associated with the wireless transmitter, and a wireless database associated with the wireless transmitter. The method includes sensing flight performance data with the sensor, transmitting sensed flight performance data to the wireless transmitter, wirelessly transmitting the sensed flight performance data to the wireless database, and monitoring flight performance data with a display operably associated with the wireless database.Type: GrantFiled: July 26, 2013Date of Patent: April 30, 2019Assignee: Bell Helicopter Textron Inc.Inventors: William D. Girard, Brian E. Tucker
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Publication number: 20190118942Abstract: Systems and methods of operating a tiltrotor aircraft include providing a control system that includes sensors and/or gauges that provide feedback regarding hub shear forces in rotor systems of the aircraft that produce aeroelastic instability known as whirl flutter. Feedback from the sensors and/or gauges is communicated to a flight control subsystem that includes an algorithm that provides a cascading set of responses to control whirl flutter and a failsafe that adjusts operational characteristics of the aircraft in response to the continuation or excitation of the whirl flutter.Type: ApplicationFiled: October 24, 2017Publication date: April 25, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Sung Kim, Jouyoung Jason Choi, Frank Bradley Stamps
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Publication number: 20190118961Abstract: A rotor system including a hub; a rim configured to rotate about the hub, the rim including an interior surface and an engagement surface; a plurality of rotor blades extending from the hub and coupled to the interior surface of the rim; and one or more outer drive gears disposed adjacent to the engagement surface of the rim; each of the one or more outer drive gears including a plurality of teeth for engaging the engagement surface of the rim; wherein the one or more outer drive gears are configured to rotate the rim such that the plurality of rotor blades rotates about the hub. Other aspects provide an aircraft rotor system and methods of operating an aircraft rotor system.Type: ApplicationFiled: October 19, 2017Publication date: April 25, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Alison Ann Woodruff, Charles Speller
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Publication number: 20190118523Abstract: An intentionally activated frangible bonding system comprises a frangible adhesive, adhesive primer, composite material matrix, and/or the like, having a polydispersion of at least one additive spread throughout the frangible bonding material. The additive degrades a bond provided by the frangible bonding material, upon application of a specific energy to the frangible bonding material. An energy emitter is configured to selectively direct the specific energy toward a structure or assembly comprising components bonded by the frangible bonding material to degrade the frangible bonding material bonding the components for disassembly.Type: ApplicationFiled: October 19, 2017Publication date: April 25, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Thomas S. Chiang, Jared Mark Paulson
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Patent number: 10266252Abstract: A pylon assembly for a tiltrotor aircraft includes a rotor assembly operable to rotate between a generally vertical orientation, in a VTOL flight mode, and a generally horizontal orientation, in a forward flight mode, and having an intermediate orientation therebetween, in a conversion flight mode. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension, positioned outboard of the rotor assembly, has a minimal dimension and an outboard end. A winglet is coupled to the outboard end of the wing extension and has a minimal dimension. The wing extension and the winglet are operable to rotate generally with the rotor assembly such that the minimal dimensions of the wing extension and the winglet remain in the slipstream of the proprotor.Type: GrantFiled: September 19, 2016Date of Patent: April 23, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Adam Bryant Anderson, Steven Ray Ivans, Jeremy Robert Chavez
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Patent number: 10266250Abstract: In some embodiments, a control manager is disposed between the rotor system and the flight control inceptor. The control manager is configured to receive control commands wirelessly from a ground control station, translate the control commands into one or more axes associated with the flight control inceptor, and transmit the translated control commands to the rotor system in place of the instructions received from the pilot via the flight control inceptor.Type: GrantFiled: May 27, 2016Date of Patent: April 23, 2019Assignee: Bell Helicopter Textron Inc.Inventor: ShyhPyng Jack Shue
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Publication number: 20190113426Abstract: Systems and methods of operating a test apparatus to simulate testing a production aircraft component include assembling a test assembly having a test specimen and a wear protection material disposed on opposing sides of the test specimen, an outer plate disposed on each side of the test specimen in contact with the wear protection material, and a bolt disposed through the test specimen and the outer plates and applying a preload against the wear protection material. The test assembly is secured in a test machine, and the test machine is operated to provide a predetermined displacement of the test specimen relative to the outer plates at a predetermined frequency at a determined frequency of displacement cycles. The preload, the predetermined displacement, and the predetermined frequency of displacement cycles are determined through finite element analysis of an analytical model of the production component.Type: ApplicationFiled: October 12, 2017Publication date: April 18, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Ramesh Thiagarajan, Suvankar Mishra
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Publication number: 20190112041Abstract: A rotor assembly has a composite driveshaft extending between a transmission and a yoke for providing torque from the transmission to the yoke to cause rotation of the yoke and a plurality of rotor blade assemblies attached thereto. The rotor hub also has a composite static mast coupled to the yoke and a frame. The static mast being configured to carry the lift and thrust forces from the yoke to the frame.Type: ApplicationFiled: October 18, 2017Publication date: April 18, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Andrew Paul Haldeman, Dalton T. Hampton, Frank Bradley Stamps, John Lloyd, Gilberto Morales
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Publication number: 20190112028Abstract: A propulsion and lift system of a tiltrotor aircraft includes a wing having an outboard end, a wing tip assembly having an inboard end, a fixed nacelle coupled to the wing tip assembly and a wing-nacelle splice assembly having inboard and outboard sides. The inboard side of the wing-nacelle splice assembly is coupled to the outboard end of the wing, and the outboard side of the wing-nacelle splice assembly is coupled to the inboard end of the wing tip assembly, thereby coupling the fixed nacelle to the wing.Type: ApplicationFiled: October 18, 2017Publication date: April 18, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeffrey Matthew Williams, George Ryan Decker, Michael Edwin Rinehart, Andrew G. Baines, James Elbert King
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Publication number: 20190113098Abstract: A vibration attenuating fluid mount with a partitioned compensator includes an inner member, an outer member, a flexible member having a castellated transition between a fluid passageway and at least one operating chamber. A membrane may be disposed in a volume compensator in fluid communication with one or more operating chambers. The inner member and outer member may be connected via a castellated connection, a swaged lock ring, or a split-lock ring.Type: ApplicationFiled: October 16, 2017Publication date: April 18, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Michael Reaugh Smith, Frank Bradley Stamps, Craig Turner, Maurice Griffin
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Patent number: 10259576Abstract: A rotary system including a grip having an opening forming a first bridge for receiving a centrifugal force bearing that faces inwardly towards the rotor mast. A rotor blade couples to the grip and a pitch horn positioned outside the opening pitches the rotor blade during flight. A bearing assembly attaches the first bridge to the yoke and controls blade forces exerted against the hub assembly during flight.Type: GrantFiled: September 19, 2017Date of Patent: April 16, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Chad Lewis Jarrett, Frank Bradley Stamps, Glenn Shimek
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Patent number: 10261517Abstract: A rotorcraft including a flight control computer (FCC) providing a vertical speed hold for the rotorcraft, a collective control, and a collective trim motor connected to the collective control. The collective trim motor moves the collective control according to a collective set command generated by the FCC according to a target vertical speed and when the FCC determines the collective control is in-detent. A collective position sensor is connected to the collective control. The collective position sensor generates, and sends to the FCC, a collective position signal indicating the position of the collective control. A flight control device controls a flight parameter of the rotorcraft in response to a flight control device control signal received from the FCC. The FCC generates the flight control device control signal according to the collective position signal, and sends the flight control device control signal to a flight control device.Type: GrantFiled: April 11, 2017Date of Patent: April 16, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Christopher Mike Bothwell, Sung Kyun Kim, Jillian Samantha Alfred, Robert Earl Worsham, II, Luke Dafydd Gillett, Morganne Cody Klein
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Patent number: 10259560Abstract: A modular payload system for an aircraft includes a modular bay recessed within the aircraft. The modular bay includes a modular bay interface. The modular payload system includes a plurality of payload modules each having a respective function and a payload interface adapted to connect to at least a portion of the modular bay interface. The plurality of payload modules are interchangeably insertable into the modular bay to enable the modular bay to support the functions of the plurality of payload modules.Type: GrantFiled: September 20, 2016Date of Patent: April 16, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Steven Ray Ivans, Brent Chadwick Ross
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Patent number: 10259572Abstract: A method and apparatus for determining failure diagnosis of drive systems of rotorcrafts through measuring the spectral characteristics of rotational oscillations and torsional oscillations and steady windup of a drive shaft. Mechanical anomalies of the drive system will alter the spectral characteristics of rotational oscillations and torsional oscillations and steady windup as detected by a pair of variable reluctance sensors in conjunction with a radial grating mounted on the drive shaft.Type: GrantFiled: April 16, 2015Date of Patent: April 16, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Rodney Keith Hale, Steven Kirk Spears, Brian Tucker