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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：US20200347903A1
公开(公告)日：2020-11-05
申请号：US16399458
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc.
Inventor： Peter Quinn Romano , Michael S. Seifert , Jeffrey M. Bosworth
Abstract: An aircraft comprises an aircraft component, a sensor, and a multiple frequency vibration absorber (absorber). The sensor is operable to detect a frequency of a vibration of the aircraft component. The absorber is coupled to the aircraft component and configured to absorb the vibration. The absorber comprises a beam element, a fluidic flexible matrix composite (FFMC) tube, a valve, and a controller. The beam element is attached to the aircraft component. The fluidic flexible matrix composite (FFMC) tube is coupled to the beam element and is operable to absorb the vibration based on a stiffness of the FFMC tube. The valve is fluidically coupled to the FFMC tube and is to control the stiffness of the FFMC tube based on regulating a flow of a liquid through the FFMC tube. The controller can actively control absorption of the vibration via the FFMC tube based on opening and/or closing the valve.
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公开(公告)号：US20200346732A1
公开(公告)日：2020-11-05
申请号：US16399922
申请日：2019-04-30
Applicant: Bell Helicopter Textron Inc,
Inventor： Albert Gerard Brand
Abstract: Various implementations described herein are directed to an aircraft. The aircraft includes an airframe; and a windshield system having a transparent canopy coupled to the airframe and a transparent inner panel having a portion thereof disposed within the transparent canopy and coupled to the airframe.
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公开(公告)号：US20200339256A1
公开(公告)日：2020-10-29
申请号：US16398222
申请日：2019-04-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Steven Ray Ivans
Abstract: Various implementations described herein are directed to a vertical takeoff and landing system. In one implementation, the vertical takeoff and landing system includes a carriage. The carriage includes a thrust component configured to provide vertical and/or horizontal thrust for the carriage and one or more housings configured to receive an aircraft in a joined configuration of the carriage and the aircraft.
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公开(公告)号：US20200339252A1
公开(公告)日：2020-10-29
申请号：US16398106
申请日：2019-04-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Daniel Bryan Robertson
IPC: B64C27/82
Abstract: According to one implementation of the present disclosure, a tail rotor system of a rotorcraft includes an electric motor, a swiveling actuator, a spindle, and a hub assembly. The hub assembly may be configured to position two or more blades. Also, in response to a control signal, the swiveling actuator may be configured to actuate swivel rotation of the spindle around a vertical axis such that the hub assembly turns from a first horizontal directional axis to a second horizontal directional axis.
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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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