Patents Assigned to Textron
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Patent number: 9151162Abstract: According to one embodiment, a rotor system includes an anti-rotation sleeve featuring an outer recess portion and a tilt sleeve positioned about the anti-rotation sleeve and having an opening therethrough. A first swashplate ring is positioned about the tilt sleeve and features an inner recess portion. An anti-rotation mechanism is disposed through the opening and at least partially in the outer recess portion and the inner recess portion. The anti-rotation mechanism is operable to prevent the first swashplate ring from rotating about the anti-rotation sleeve. A second swashplate ring is positioned about the first swashplate ring and rotatable about the anti-rotation sleeve.Type: GrantFiled: November 8, 2012Date of Patent: October 6, 2015Assignee: Bell Helicopter Textron Inc.Inventors: George M. Thompson, Frank B. Stamps, Glenn A. Shimek
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Publication number: 20150274282Abstract: According to one embodiment, a flight control system includes a pilot control module configured to receive commands from a pilot, a flight control module operable to transmit an instruction to change at least one operating condition of an aircraft, and a flight control computer in communication between the flight control module and the pilot control module. The flight control computer is configured to receive a pilot command to change a first flight characteristic, wherein changing the first flight characteristic would result in an expected change to a second flight characteristic. The flight control computer may instruct the flight control module to transmit an instruction to change a first operating condition of the aircraft and instruct the flight control module to transmit an instruction to change a second operating condition of the aircraft to at least partially offset the expected change to the second flight characteristic.Type: ApplicationFiled: December 19, 2014Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Sung K. Kim, Christopher M. Bothwell, Robert Lee Fortenbaugh
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Publication number: 20150274290Abstract: According to one embodiment, a rotor blade rotation system includes a hub, a rotor blade in mechanical communication with the hub and pivotable about an axis of rotation, a swashplate, a pitch link, and an actuator. The swashplate includes a rotating portion and a non-rotating portion. The pitch link is coupled to the rotating portion of the swashplate and in mechanical communication with the rotor blade. The actuator is coupled to the non-rotating portion of the swashplate and operable to reposition the swashplate from a first position to a second position such that the pitch links pivot the rotor blade from a deployed position to a folded position.Type: ApplicationFiled: July 24, 2013Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Carlos A. Fenny, Troy Schank, Frank B. Stamps
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Publication number: 20150274313Abstract: According to one example embodiment, a method of assessing use of an aircraft component installed on an aircraft includes receiving, from one or more sensors installed on the aircraft, one or more measurements representative of at least one load applied against the aircraft component; selecting at least one usage model from a plurality of usage models, each usage model of the plurality of usage models relating aircraft loads with received sensor data; determining at least one load value based on the selected at least one usage model and the received one or more measurements; and calculating, based on the determined at least one load value, an amount of change in probability of failure caused by application of the at least one load against the aircraft component.Type: ApplicationFiled: December 19, 2014Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventor: Kevin Conrad
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Publication number: 20150274312Abstract: According to one example embodiment, a method of assessing reliability of an aircraft component includes identifying, aboard an aircraft, a first probability of failure of the aircraft component installed on the aircraft. One or more measurements representative of at least one load applied against the aircraft component are received. Determined, aboard the aircraft, is a second probability of failure of the aircraft component based on the first probability of failure and the received one or more measurements representative of the at least one load applied against the aircraft component, the second probability of failure representing a probability of failure of the aircraft component after application of the at least one load.Type: ApplicationFiled: December 19, 2014Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventor: Kevin Conrad
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Publication number: 20150274315Abstract: According to one example embodiment, a method of assessing use of an aircraft component installed on an aircraft includes assessing whether received one or more measurements are sufficient to support calculation of a usage-based change in remaining useful life and, if the one or more measurements are sufficient to support calculation of the usage-based change in remaining useful life, calculating the usage-based change in remaining useful life based on the received one or more measurements and changing the second remaining useful life of the aircraft component by the difference between the default change in remaining useful life and the usage-based change in remaining useful life.Type: ApplicationFiled: December 19, 2014Publication date: October 1, 2015Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Kevin Conrad
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Publication number: 20150275998Abstract: According to one embodiment, a spring tension adjustment device for adjusting tension in a spring includes a rotation feature and a plurality of spring-attachment features. The rotation feature defines a first axis of rotation. Each spring-attachment feature is configured to receive one end of a spring, each spring-attachment feature being located at a different distance from the rotation feature.Type: ApplicationFiled: August 25, 2014Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Travis Yates, JR., Chad Haugeberg
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Publication number: 20150274314Abstract: According to one example embodiment, a method of reassessing use of an aircraft component installed on an aircraft includes receiving, from one or more sensors installed on the aircraft, one or more measurements representative of at least one load applied against the aircraft component; determining, based on the received one or more measurements and based on at least one other received input, an amount of change in probability of failure caused by application of the at least one load against the aircraft component; receiving a change to one of the received one or more measurements or the at least one other received input; and redetermining the change in probability of failure based on the received change.Type: ApplicationFiled: December 19, 2014Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventor: Kevin Conrad
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Publication number: 20150274287Abstract: A speed control assembly includes an input drive shaft coupled to a first gear subassembly having a rotatable gear, a second gear subassembly coupled to an output drive shaft, and a linkage coupling the first and second gear subassemblies, wherein the input drive shaft, the first and second gear subassemblies, and the linkage are configured such that a rotational speed of the rotatable gear adjusts a ratio of a rotational speed of the output drive shaft to a rotational speed of the output drive shaft. In some embodiments, the first gear subassembly includes a sun gear coupled to the input drive shaft, one or more planet gears, and a ring gear as the rotatable gear. In some embodiments, the second gear subassembly includes a sun gear coupled to the output drive shaft, one or more planet gears, and a fixed ring gear.Type: ApplicationFiled: March 10, 2014Publication date: October 1, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Daniel B. Robertson, Dudley E. Smith, Carlos A. Fenny, Walter West Riley
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Patent number: 9145277Abstract: A method of manufacturing a composite core can include: wrapping a mandrel in a mandrel wrapping process by securing a mandrel with a winding jig; orienting the composite material at a wrap angle to the mandrel; and depositing the composite material around a circumference of the mandrel. The method can further include assembling the wrapped mandrels in a tool and applying a pressure to the composite material during a curing cycle.Type: GrantFiled: March 1, 2013Date of Patent: September 29, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Phillip A. Kendrick, Paul K. Oldroyd, Levi H. Armstrong, Elizabeth Oberle
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Patent number: 9145946Abstract: An apparatus includes an active vibration isolation system that includes a vibration isolator, a dual fluid pump in fluid communication with the vibration isolator and a hydraulic system, wherein the dual fluid pump is configured to segregate a tuning fluid from a hydraulic fluid and an electric-hydraulic servo valve in fluid communication with the dual fluid pump.Type: GrantFiled: March 15, 2013Date of Patent: September 29, 2015Assignee: Bell Helicopter Textron Inc.Inventors: David E. Heverly, II, Taeoh Lee
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Patent number: 9146262Abstract: A non-contact, hand-held voltage detector is used to determine if AC voltage is present in a tamper-resistant receptacle. The voltage detector includes a pair of pins to open both shutters of the tamper-resistant receptacle.Type: GrantFiled: January 10, 2013Date of Patent: September 29, 2015Assignee: TEXTRON INNOVATIONS INC.Inventors: Zachary Lamoreux, Richard A Duke
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Publication number: 20150267762Abstract: In some embodiments, a redundant control system includes first and second control systems, having first and second clutches, and a shared clutch system. The shared clutch system may include a shared shaft configured to receive mechanical energy from a shared power source, a first shared clutch corresponding to the first clutch and configured to receive mechanical energy from the shared shaft, and a second shared clutch corresponding to the second clutch and configured to receive mechanical energy from the shared shaft. A first linkage provides mechanical communication between an output of the first clutch, an output of the first shared clutch, and a first output device in mechanical communication with the rotor system. A second linkage provides mechanical communication between an output of the second clutch, an output of the second shared clutch, and a second output device in mechanical communication with the rotor system.Type: ApplicationFiled: September 10, 2014Publication date: September 24, 2015Applicants: BELL HELICOPTER TEXTRON INC., Université Laval, Université de SherbrookeInventors: Pasquale Spina, Carlos A Fenny, Jean-Sebastian Plante, Patrick Chouinard, Jean-Philippe Lucking Bigué, Yves St-Amant
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Patent number: 9139296Abstract: A vibration attenuator for an aircraft has at least one weight mounted in a rotating system of a rotor hub of the aircraft, each weight being rotatable about an axis of rotation of the hub relative to the hub and to each other weight. Drive means are provided for rotating each weight about the axis of rotation at a selected speed for creating oscillatory shear forces that oppose and attenuate rotor-induced vibrations having a selected frequency. A vertically oriented vibration attenuator is configured to oppose and attenuate vertical rotor induced oscillatory forces that would otherwise travel vertical down the rotor mast and into the airframe.Type: GrantFiled: July 2, 2013Date of Patent: September 22, 2015Assignee: Textron Innovations Inc.Inventors: David A. Popelka, Frank B. Stamps
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Patent number: 9138885Abstract: A bypass assembly varies the hydraulic motor revolutions per minute (rpm) of a hydraulically driven tool, such as a wrench or a drill. This controls the torque of a driven mechanical mechanism, such as used on an impact wrench. The tool includes a body having a supply channel capable of being connected a source of fluid, a bypass spool channel in fluid communication with the supply channel, and a return channel in fluid communication with the bypass spool channel via a port and in fluid communication with the source. A bypass spool seats in the bypass spool channel. The bypass spool can be rotated to three discrete positions within the bypass spool channel to provide three different settings of revolutions per minute (rpm) of the gear motor.Type: GrantFiled: September 27, 2012Date of Patent: September 22, 2015Assignee: TEXTRON INNOVATIONS INC.Inventor: Gerald Jonathan Tully
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Publication number: 20150259065Abstract: One example of a retention system for a rotorcraft pedal assembly includes an insertion member, an axial retention member, and a transverse retention member. The insertion member, which is inserted through a side of a pedal assembly, includes a spring compressible against the side of the pedal assembly in response to the insertion member being inserted through the side. The axial retention member receives and retains the insertion member on an opposing side of the pedal assembly. The transverse retention member is inserted through a passage formed in the axial retention member to secure the axial retention member against the side of the pedal assembly.Type: ApplicationFiled: March 12, 2014Publication date: September 17, 2015Applicant: Bell Helicopter Textron Inc.Inventors: Patricia Wills, Brian Lafon, Ricky Jenkins
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Patent number: 9132729Abstract: The invention relates to a pressure equalizing valve (5) for a fuel tank or secondary fluid tank on a motor vehicle, comprising at least one valve housing (10), at least one valve body movably arranged in the valve housing (10), at least one venting opening on the tank side and on the connection side or on the atmosphere side, which form a venting path (16) which may be opened or closed by the valve body depending on the position of the tank, when a predetermined transverse force is exceeded relative to a normal force which holds the valve body in a valve seat, the valve body being able to be lifted or deflected from the valve seat and thus opening the venting path (16) and when falling below said transverse force automatically adopting again the position closing the venting path (16). The valve body is configured as a ball (15) and arranged so that when pressure prevails on the tank side, said valve body is held in the valve seat.Type: GrantFiled: February 9, 2012Date of Patent: September 15, 2015Assignee: Kautex Textron GmbH & Co. KGInventor: Volker Treudt
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Patent number: 9132728Abstract: The invention relates to a thermoplastic tank (1) with at least one insert part which is provided in the interior of the tank (1) and is inserted into the tank (1) through an opening (3) in a tank wall (2) and is sealed against a peripheral flange (4) provided in the region of the opening (3). The flange (4) is formed integrally with the tank wall (2) and is countersunk therein.Type: GrantFiled: July 5, 2011Date of Patent: September 15, 2015Assignee: Kautex Textron GmbH & Co. KGInventors: Timm Heidemeyer, Stefan Lenz, Dieter Schmitz, Volker Treudt
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Patent number: D738785Type: GrantFiled: May 20, 2014Date of Patent: September 15, 2015Assignee: Textron, Inc.Inventors: John Frederick Criss, Jr., Richard Franklin Krall
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Patent number: D739335Type: GrantFiled: October 24, 2013Date of Patent: September 22, 2015Assignee: Bell Helicopter Textron Inc.Inventors: Daniel Robertson, Berlin Benfield, Cory Hitte, Kirk Groninga