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公开(公告)号：US10882598B2
公开(公告)日：2021-01-05
申请号：US15951539
申请日：2018-04-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeremy Robert Chavez , Brent Chadwick Ross
Abstract: 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.
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公开(公告)号：US10881929B2
公开(公告)日：2021-01-05
申请号：US16241603
申请日：2019-01-07
Applicant: Textron Inc.
Inventor： Paul Morgan
Abstract: An auxiliary storage compartment for a golf car, wherein the auxiliary storage compartment comprises a storage receptacle disposed on a rear deck of a body of a golf car behind and accessible from a seating structure of the golf car. In various instances, the storage receptacle comprising at least one sidewall that defines an interior storage space of the storage receptacle.
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公开(公告)号：US10851841B1
公开(公告)日：2020-12-01
申请号：US16540633
申请日：2019-08-14
Applicant: Bell Textron Inc.
Inventor： George Matthew Thompson , Jonathan Knoll , Nicholas Carlson
Abstract: One embodiment is a bearing carrier assembly including a circular shield having top and bottom surfaces; and a number of bearing separators integrated with the bottom surface of the shield, wherein each pair of bearing separators defines a receptacle for receiving and retaining a bearing therewithin and wherein the shield blocks the received bearings from debris and retains lubricant around the received bearings. Each of the bearing separators may include a spacer element for separating adjacent ones of the bearings. The bearing carrier assembly may be made up of a number of carrier sections that interconnect to form the bearing carrier assembly.
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公开(公告)号：US10829239B2
公开(公告)日：2020-11-10
申请号：US16059655
申请日：2018-08-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Dewey Parsons
IPC: B64D41/00 , B60R16/03 , H02B1/20 , B64C27/04 , H02P101/30
Abstract: Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.
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公开(公告)号：US10829200B2
公开(公告)日：2020-11-10
申请号：US15807843
申请日：2017-11-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric R. Gonzalez , Frank B. Stamps
Abstract: A multirotor aircraft comprises at least three proprotors. Each proprotor has a plurality of rotor blades pivotably attached to a mast assembly. When a rotor blade pitch angle is changed for a proprotor, all rotor blades on the proprotor change to a same pitch angle. The proprotors are configured to spin freely when a power source is disengaged or fails. In various embodiments, one or more engines provides power to each proprotor, or at least one engine provides power to two or more proprotors. A rotor blade control system is configured to control a collective rotor blade pitch angle on each proprotor independently of the rotor blade pitch on the other proprotors. The rotor blade control system is configured to set a negative collective rotor blade pitch angle on an unpowered proprotor, such as in response to manual inputs by a pilot or in response to current engine conditions.
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Patent Agency Ranking
公开(公告)号：US10816085B2
公开(公告)日：2020-10-27
申请号：US15874054
申请日：2018-01-18
Applicant: Bell Helicopter Textron Inc.
Inventor： Eric S. Olson , David R. Bockmiller
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.
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公开(公告)号：US10815008B2
公开(公告)日：2020-10-27
申请号：US15662147
申请日：2017-07-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Brent C. Ross , Kendall Goodman , Steven R. Ivans
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.
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公开(公告)号：US20200333228A1
公开(公告)日：2020-10-22
申请号：US16912934
申请日：2020-06-26
Applicant: Bell Textron Inc.
Inventor： Xiaoming Li , Bogdan R. Krasnowski , Robert A. Figueroa , Robert Wardlaw
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.
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公开(公告)号：US20200331216A1
公开(公告)日：2020-10-22
申请号：US16922831
申请日：2020-07-07
Applicant: Bell Textron Inc.
Inventor： Michael Burnett , Wei-Yueh Lee , Michael Dearman
IPC: B29C70/56 , G01M5/00 , G01N3/08 , B29C70/32 , G01N3/02 , G01N3/04 , G06F30/23 , B29C70/30 , B29C70/54
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.
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公开(公告)号：US10809281B2
公开(公告)日：2020-10-20
申请号：US16118283
申请日：2018-08-30
Applicant: Bell Helicopter Textron Inc.
Inventor： David W. Fuessel , Russel Mark Berkley
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.
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