Patents Assigned to Textronics, Inc.
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Publication number: 20190323596Abstract: An exemplary passive oil system includes a reservoir housing configured in operation to rotate around a rotational axis, the reservoir housing defining a reservoir between a top wall, a bottom wall, innermost side, and an outer sidewall; and an outlet positioned adjacent the outer sidewall to discharge a lubrication fluid contained in the reservoir in response to the reservoir housing rotating around the rotational axis.Type: ApplicationFiled: April 24, 2018Publication date: October 24, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Eric Stephen OLSON, David BOCKMILLER
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Publication number: 20190322365Abstract: An aircraft includes a fuselage coupled to a wing having a dihedral root section with first and second outboard sections pivotably coupled to respective outboard ends thereof. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has an M-wing configuration with the center of gravity of the aircraft located between the outboard sections of the wing. In a wing-borne forward flight mode, the wing has a gull wing configuration with the center of gravity of the aircraft located below the outboard sections of the wing.Type: ApplicationFiled: April 18, 2018Publication date: October 24, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Sean Robert Gaffney, Robert Rex Graham, JR., Colton Edward Campbell, Kevin Krisnil Prasadk, Isaiah Neves Martinez, Jared Michael Rosenkrance, Lukas N. Everhart, William Paul Crisler
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Publication number: 20190322366Abstract: An aircraft includes a fuselage coupled to a wing having a root section and first and second outboard sections each having first and second wing layers pivotably coupled to respective outboard ends of the root section. A thrust array is coupled to the wing. A power system is operably associated with the thrust array to provide power to each of a plurality of propulsion assemblies. A flight control system is operably associated with the thrust array and the wing. The flight control system is operable to control the thrust output from the propulsion assemblies and the configuration of the wing. In a thrust-borne vertical lift mode, the wing has a split wing configuration such that the thrust array forms a two dimensional thrust array. In the wing-borne forward flight mode, the wing has a monoplane configuration such that the thrust array forms a one dimensional thrust array.Type: ApplicationFiled: April 19, 2018Publication date: October 24, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Sean Robert Gaffney, Robert Rex Graham, JR.
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Publication number: 20190323563Abstract: A driveshaft includes a first end, a second end, and a length extending from the first end to the second end. The driveshaft includes an engagement section at the first end configured to cooperatively engage and transfer torque to a gearbox. The driveshaft also includes a compressible section configured to selectively decrease the length of the driveshaft. The driveshaft being configured to transition between an engaged configuration, wherein the engagement portion is engaged with the gearbox, and a disengaged configuration, wherein the compressible section is compressed, and the engagement portion is disengaged from the apparatus.Type: ApplicationFiled: April 24, 2018Publication date: October 24, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Colton Gilliland, Russell L. Mueller
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Patent number: 10450060Abstract: A laminated elastomeric bearing has layers of elastomeric material and layers of metal. A tab is located on a periphery of one of the layers of metal and protrudes from the bearing. A thermoelectric device is coupled to the tab, and heat generated within the bearing during use is conducted to the tab and to the thermoelectric device, allowing for measurement of the heat.Type: GrantFiled: August 5, 2016Date of Patent: October 22, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Clifton B. Day, Frank B. Stamps, Jason Hoyle
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Patent number: 10450058Abstract: 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: GrantFiled: August 23, 2017Date of Patent: October 22, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Gary Miller, Frank B. Stamps
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Patent number: 10450054Abstract: An airframe assembly for an aircraft. The airframe assembly includes a first airframe member having a first skin, a second skin, a large cell core joined between the first and second skins and a solid insert having a side surface. The solid insert is joined between the first and second skins such that at least a portion of the side surface is adjacent to the large cell core. The first skin has a first surface disposed opposite the solid insert. The airframe assembly also includes a second airframe member having a second surface. An adhesive joint is disposed between the first and second surfaces structurally bonding the first airframe member to the second airframe member such that the second airframe member is positioned opposite the solid insert.Type: GrantFiled: May 22, 2017Date of Patent: October 22, 2019Assignee: Bell Textron Inc.Inventors: James Everett Kooiman, George Ryan Decker, Keith Alan Stanney, Robert Mark Chris
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Patent number: 10450059Abstract: A multi-piece inboard beam assembly for use in a rotor blade assembly of a rotorcraft. The inboard beam assembly includes an inboard beam connected to an inboard beam fitting with an anti-rotational connection. The inboard beam is connected to a yoke via bearings and the inboard beam fitting is connected to a grip in a double shear condition. In use, the grip, the inboard beam fitting with the double shear connection, the inboard beam, a centrifugal force bearing held by the inboard beam, and the yoke carry the centrifugal force created upon rotation of the rotor blade assembly.Type: GrantFiled: January 29, 2018Date of Patent: October 22, 2019Assignee: Bell Helicopter Textron Inc.Inventors: Kyle Thomas Cravener, Tyler Wayne Baldwin, Nicholas Allen Torske
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Publication number: 20190315448Abstract: Embodiments are directed to systems and methods for a sliding door in a pressurized aircraft. In one embodiment, an aircraft comprises a fuselage having a door opening, and a door configured to slide into the door opening from within the fuselage, the door held in a closed position in the door opening by excess air pressure within the fuselage during operation of the aircraft.Type: ApplicationFiled: April 12, 2018Publication date: October 17, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeremy Robert Chavez, Brent Chadwick Ross
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Publication number: 20190315076Abstract: Methods and systems for automated placement of composite material on a surface of a component, the composite material including unidirectional fibers, is provided. A set of fiber paths along the surface is established, the set of fiber paths comprising at least one ply, each ply comprising a respective plurality of fiber paths being substantially aligned with a respective direction. An isotropy factor for the component is determined based on the set of fiber paths, the isotropy factor being indicative of a distribution of the plurality of fiber paths on the surface. When the isotropy factor exceeds a predetermined threshold, a respective layer of composite material is applied to the surface of the component using an automated fiber placement machine and for each of the at least one ply, wherein the unidirectional fibers of the composite material are applied along the set of fiber paths.Type: ApplicationFiled: April 11, 2018Publication date: October 17, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Sébastien Duval, Pascal Flynn-Robitaille
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Publication number: 20190318711Abstract: Embodiments are directed to systems and methods for interacting with a touch-sensitive display in a vehicle. The display shows one or more objects. Vehicle motion is detected. The position of at least one object on the touch-sensitive display based upon the vehicle motion. User touches on the touch-sensitive display may be detected, and tactile feedback may be provided to the user via a glove. In a further embodiment, an imminent input to the touch-sensitive display may be detected, and the target point for the imminent input may be determined. The display may be zoomed around the target point to expand at least a portion of a targeted object. The vehicle may be an aircraft, and the targeted object may be a virtual flight instrument. The target point may also be displayed on the touch-sensitive display.Type: ApplicationFiled: April 16, 2018Publication date: October 17, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Jeremy Robert Chavez, Steven Wayne Kihara
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Publication number: 20190314949Abstract: A masking tool system includes a first masking body and a second masking body. The first masking body includes a bore passing through a portion of the first masking body and a first sealing element disposed on a first end of the first masking body. The second masking body includes a bore passing through the second masking body and a second sealing element disposed on a first end of the second masking body. The system may also include a rod configured to pass through the bores of the first and second masking bodies and to secure the first and second masking bodies to a metallic article placed therebetween. A diagonal length of the masking tool system induces a wobbling rotation during processing.Type: ApplicationFiled: April 13, 2018Publication date: October 17, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Michael Scott Lee Larson, Roland L. Walker, JR., Mark Philip Vance, James Joseph Meyer, Edward P. Michaels, JR.
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Patent number: 10442544Abstract: A multi-engine power system is described that includes at least a first engine and a second engine configured to jointly provided mechanical power to the multi-engine power system. The multi-engine power system further includes a controller configured to estimate a deterioration factor of the first engine. The controller is further configured to adjust, based on the deterioration factor of the first engine, a first amount of mechanical power being provided by the first engine to increase a service time of the first engine, and adjust, based on the first amount of mechanical power being provided by the first engine, a second amount of mechanical power being provided by the second engine to compensate for the adjustment to the first amount of mechanical power.Type: GrantFiled: May 3, 2017Date of Patent: October 15, 2019Assignees: Rolls-Royce North American Technologies, Inc., Bell Helicopter Textron Inc.Inventors: Douglas Boyd, Brian Tucker
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Patent number: 10444132Abstract: A bipendulum impact test machine for imparting impact damage includes a frame of beams where a weighted sled swings from a pair of links extending from a carriage. The carriage and sled are vertically adjustable along a set of vertical shafts of the frame. The sled is permanently horizontally oriented and parallel with the carriage. Interchangeable impact tips are removably and adjustably engaged with the sled. The impact tips have a variety of shapes in order to simulate different impact scenarios. The device is mobile and capable of imparting impact damage to large aircraft parts even in an installed condition.Type: GrantFiled: June 30, 2017Date of Patent: October 15, 2019Assignee: Bell Helicopter Textron Inc.Inventor: Kevin Thomas Howie
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Patent number: 10442539Abstract: In one embodiment, a system may comprise an electro-thermal heating element and a controller. The electro-thermal heating element may be configured to heat a structure, and the controller may be configured to: identify a target temperature for the structure; identify a target rate of temperature change for the structure; identify a target voltage for heating the structure at the target rate of temperature change; and apply the target voltage to the electro-thermal heating element.Type: GrantFiled: May 12, 2017Date of Patent: October 15, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventor: Gary S. Froman
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Patent number: 10443706Abstract: According to one embodiment, a rotorcraft includes a body, a rotor blade, a drive system that can be operated to rotate the rotor blade, and an emergency valve control unit. The drive system contains a first gearbox assembly, a second gearbox assembly, a first lubrication system that can deliver lubricant to the first gearbox assembly, and a second lubrication system that can deliver lubricant to the second gearbox assembly. The drive system also contains an emergency valve that can be opened to deliver lubricant from the first lubrication system to the second gearbox assembly. The emergency valve control unit can instruct the emergency valve to open.Type: GrantFiled: November 6, 2018Date of Patent: October 15, 2019Assignee: BELL HELICOPTER TEXTRON INC.Inventor: Ryan T. Ehinger
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Patent number: 10442522Abstract: An aircraft operable to transition between a forward flight mode and a vertical takeoff and landing flight mode. The aircraft includes an airframe having first and second wings. A plurality of propulsion assemblies is attached to the airframe with each of the propulsion assemblies including a nacelle and a tail assembly having at least one active aerosurface. A flight control system is operable to independently control each of the propulsion assemblies. For each of the propulsion assemblies, the tail assembly is rotatable relative to the nacelle such that the active aerosurface has a first orientation generally parallel to the wings and a second orientation generally perpendicular to the wings.Type: GrantFiled: May 26, 2017Date of Patent: October 15, 2019Assignee: Bell Textron Inc.Inventors: Paul K. Oldroyd, John Richard McCullough
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Publication number: 20190308722Abstract: Systems and methods include providing an aircraft with a tail rotor system having a tail rotor housing that forms a cambered airfoil between an upper cambered surface and an lower cambered surface of the tail rotor housing. The cambered airfoil design of the tail rotor housing is capable of providing sufficient lifting force of an aircraft to offload the tail rotor during forward flight, thereby eliminating the need for a traditional vertical stabilizer or fin. The tail rotor blades of the tail rotor system are disposed within an aperture in the tail rotor housing, which minimizes or preferably eliminates exposure of the tail rotor blades to edgewise airflow typically encountered during forward flight, thereby allowing rigid rotor hubs, both in-plane and out-of-plane, to be used in the tail rotor system while also reducing noise output of the tail rotor system.Type: ApplicationFiled: April 10, 2018Publication date: October 10, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Dalton T. Hampton, Andrew Paul Haldeman, Aaron Alexander Acee, Matthew John Hill
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Publication number: 20190308738Abstract: An embodiment of the present invention provides a blocking door that is pivotally disposed on a fixed nacelle of a tiltrotor aircraft for pivoting between a stowed position when a proprotor pylon is in the substantially horizontal position and a protective blocking position in front of the proprotor pylon when the proprotor pylon is positioned in the non-horizontal position. In other aspects, there is provided a blocking door and a method of reducing infrared and/or radar signatures of rotorcraft with a rotatable proprotor.Type: ApplicationFiled: April 5, 2018Publication date: October 10, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Steven R. Ivans, Terry L. Gibson
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Publication number: 20190308750Abstract: A hook system has a mount that includes a first sidewall comprising a concave profile on a longitudinal end of the first sidewall, a second sidewall laterally offset in a fixed location relative to the first sidewall and defining a channel therebetween, the second sidewall having a second concave profile on a longitudinal end of the second sidewall. The hook system also has a first pin structure extending between the first sidewall and the second sidewall and a connector. The connector has a third concave profile, the third concave profile being configured to receive the first pin structure therein. The hook system also includes a second pin structure extending through the connector, wherein each of the first concave profile and the second concave profile are configured to receive the second pin structure therein. The connector is configured to be at least partially received within the channel.Type: ApplicationFiled: April 10, 2018Publication date: October 10, 2019Applicant: Bell Helicopter Textron Inc.Inventors: Sebastien Duval, Marc Ouellet