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公开(公告)号：US20200017205A1
公开(公告)日：2020-01-16
申请号：US16035381
申请日：2018-07-13
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey
IPC: B64C27/605 , B64C29/00 , B64C27/50
Abstract: Systems and methods of operating a tiltrotor aircraft include providing the tiltrotor with plurality of rotatable pylon assemblies. Each pylon assembly includes a rotor system having a plurality of rotor blades operatively coupled to a rotor mast and selectively rotatable in response to rotation of the rotor mast, a swashplate assembly operatively coupled to the plurality of rotor blades, a plurality of swashplate actuators operatively coupled to the swashplate assembly and selectively extendable and retractable to control the position and the orientation of the swashplate assembly, and a swashplate augmenting system. The swashplate augmenting system is selectively operable to cause axial translation of the swashplate actuators and swashplate assembly to augment the travel of the swashplate actuators in order to fold the plurality of rotor blades for operating the tiltrotor aircraft in an airplane forward flight mode.
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公开(公告)号：US20180079499A1
公开(公告)日：2018-03-22
申请号：US15269809
申请日：2016-09-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey
CPC classification number: B64C29/0033 , B64C3/56 , B64C5/02 , B64C11/28
Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.
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公开(公告)号：US11242158B2
公开(公告)日：2022-02-08
申请号：US16247745
申请日：2019-01-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey , Chyau-Song Tzeng
Abstract: A rotor assembly for use in an aircraft comprising has a rotor hub, a spinner structure comprising a spinner opening, and a rotor blade received through the spinner opening. The rotor blade has a rotor root located proximate to the rotor hub. The rotor assembly also has a motive fairing face that at least partially rests along the rotor hub.
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公开(公告)号：US20200223552A1
公开(公告)日：2020-07-16
申请号：US16247745
申请日：2019-01-15
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey , Chyau-Song Tzeng
Abstract: A rotor assembly for use in an aircraft comprising has a rotor hub, a spinner structure comprising a spinner opening, and a rotor blade received through the spinner opening. The rotor blade has a rotor root located proximate to the rotor hub. The rotor assembly also has a motive fairing face that at least partially rests along the rotor hub.
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公开(公告)号：US20180079500A1
公开(公告)日：2018-03-22
申请号：US15269825
申请日：2016-09-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey
Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.
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Patent Agency Ranking
公开(公告)号：US11440652B2
公开(公告)日：2022-09-13
申请号：US16056610
申请日：2018-08-07
Applicant: Bell Helicopter Textron Inc.
IPC: B29C70/30 , B64C27/473 , B29C70/54 , B32B1/08 , B32B5/12 , B32B5/02 , B32B5/26 , B32B37/18 , B32B38/18 , B29C70/32 , B29C53/56 , B64C11/26 , B29K105/08 , B29K105/24 , B29L31/08
Abstract: Embodiments are directed to systems and methods for creating a tubular composite structure. In one embodiment, a device comprises multiple layers of cured composite fabric bonded together to form a tubular composite structure, wherein alternating groups of the multiple layers comprise on-axis fabric and off-axis fabric. The tubular composite structure may form a spar for an aerodynamic component. The composite fabric may comprise one or more of carbon, fiberglass, or other composite materials, or a combination of materials. One or more stacks of the fabric wrap completely around the tubular composite structure, and other stacks of fabric may not wrap completely around the tubular composite structure.
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公开(公告)号：US10829199B2
公开(公告)日：2020-11-10
申请号：US16105215
申请日：2018-08-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey , Michael Christopher Burnett
Abstract: Embodiments are directed to an aerodynamic spinner fairing having a sidewall and one or more airflow intakes in the sidewall. The airflow intakes are closed during a first phase of flight and open during a second phase of flight. The first phase of flight may be an airplane mode for a tiltrotor aircraft, and the second phase of flight may be a helicopter mode for the tiltrotor aircraft. The airflow intakes may comprise an opening in the sidewall, and a door that is configured to move between a first position covering the opening and a second position exposing the opening to external airflow. An actuator coupled to the door may operate to move the door between the first position and the second position. One or more guide vanes within the aerodynamic spinner fairing may be configured to direct air received via the airflow intakes to provide convection cooling.
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公开(公告)号：US10787251B2
公开(公告)日：2020-09-29
申请号：US15871002
申请日：2018-01-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Christopher Edward Foskey
IPC: B64C27/46 , B64C27/473 , B64C27/37 , B64C27/39
Abstract: A helicopter has a mast axis and a rotorcraft blade assembly. The rotorcraft blade assembly has a main body and a blade tip movable relative to the main body. The rotorcraft blade assembly is selectively rotatable about the mast axis.
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公开(公告)号：US20190300164A1
公开(公告)日：2019-10-03
申请号：US16372289
申请日：2019-04-01
Applicant: Bell Helicopter Textron Inc.
Inventor： Andrew Ryan Maresh , Christopher Edward Foskey
Abstract: An elastomeric bearing assembly has a housing, a centrifugal force bearing axially captured relative to the housing, and a sliding cap disposed between the housing and the centrifugal force bearing.
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公开(公告)号：US20190106197A1
公开(公告)日：2019-04-11
申请号：US15728386
申请日：2017-10-09
Applicant: Bell Helicopter Textron Inc.
Abstract: A blade for an aircraft rotor has a trailing-edge tab, the tab being movable between a stowed position, in which substantially all of the tab is located within the blade, and a deployed position, in which at least a portion of the tab extends from a trailing edge of the blade. At least one actuator system is selectively operable to cause movement of the tab between the stowed position and the deployed position for changing a chord length of the blade.
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