-
公开(公告)号：US10829204B2
公开(公告)日：2020-11-10
申请号：US16206088
申请日：2018-11-30
Applicant: Textron Innovations Inc.
Inventor： Carlos Fenny , Sung Kim , Kip Campbell , Jouyoung Jason Choi
Abstract: An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.
-
公开(公告)号：US10793254B2
公开(公告)日：2020-10-06
申请号：US15375394
申请日：2016-12-12
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , Jouyoung Jason Choi , Thomas Clement Parham, Jr. , Gary Miller , Richard Erler Rauber
Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of blade support assemblies coupling the proprotor blades with the hub. Each blade support assembly includes a flapping bearing coupled to the hub and a yoke having first and second longitudinal sections with outboard grip members and an inboard arcuate section connecting the first and second longitudinal sections and coupled to the flapping bearing. A lead-lag damper is coupled between the hub and an inboard station of the respective proprotor blade. A twist shank is coupled between the outboard grip members of the yoke and an outboard station of the respective the proprotor blade. The twist shank defines a virtual lead-lag hinge outboard of the yoke and coincident with the respective pitch change axis.
-
公开(公告)号：US10518868B2
公开(公告)日：2019-12-31
申请号：US15375385
申请日：2016-12-12
Applicant: Textron Innovations Inc.
Inventor： Thomas Clement Parham, Jr. , Jouyoung Jason Choi , Gary Miller , Frank Bradley Stamps , Richard Erler Rauber
Abstract: A soft-in-plane proprotor system for a tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub, a plurality of proprotor blades and a plurality of loop yokes, each coupling one of the proprotor blades with the hub and each including first and second longitudinal sections extending between inboard and outboard arcuate sections and a bearing assembly disposed between the inboard and outboard arcuate sections of each loop yoke. Each bearing assembly includes a flapping bearing disposed generally within the inboard arcuate section of the respective loop yoke and coupled to the hub, a lead-lag damper coupled to the hub, a centrifugal force bearing disposed generally within the outboard arcuate section of the respective loop yoke and a blade anchor coupled between the lead-lag damper and the centrifugal force bearing. The blade anchor is also coupled to the respective proprotor blade.
-
Patent Agency Ranking
公开(公告)号：US11724800B2
公开(公告)日：2023-08-15
申请号：US17567874
申请日：2022-01-03
Applicant: Textron Innovations Inc.
Inventor： Frank Bradley Stamps , David Heverly , Michael R. Smith , Michael Scott Seifert , Thomas C Parham, Jr. , Gary Miller , Jouyoung Jason Choi , Richard E. Rauber
IPC: B64C27/00
CPC classification number: B64C27/001 , B64C2027/003 , B64C2027/005
Abstract: A vibration attenuator is configured for use on an aircraft rotor rotatable about a mast axis and has upper and lower weight assemblies, each comprising a weight with a center of gravity being a radial distance from the mast axis. The weight assemblies are configured for rotation together relative to the rotor at a selected angular rate about the mast axis, the weights being located on opposing sides of the mast axis. A first motor is configured for selective translation of one of the weight assemblies relative to the other weight assembly along the mast axis between a minimum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in the same plane, and a maximum-moment configuration, in which the centers of gravity of the weights revolve about the mast axis in different planes for producing a whirling moment about the mast axis.
-
公开(公告)号：US11148790B2
公开(公告)日：2021-10-19
申请号：US16794075
申请日：2020-02-18
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Stamps , Thomas Parham, Jr. , Amarjit Olenchery Kizhakkepat
Abstract: A vibration attenuation system for attenuating vibrations in a mast of an aircraft includes a weight attached to the mast but free to orbit about the mast. The weight can be comprised of one or more weight assemblies. Embodiments can include a single weight, or plural weight assemblies wherein each weight assembly can include a mechanical interconnecting mechanism so that each weight assembly receives feedback regarding the position and movement of one or more other weight assemblies. Each weight can be associated with a spring that urges the weight towards a neutral position. Rotation of the mast can cause the weight to orbit about the mast and self-excite such that the weight acts against the urging of the spring towards an attenuating position.
-
公开(公告)号：US10974822B2
公开(公告)日：2021-04-13
申请号：US16169745
申请日：2018-10-24
Applicant: Textron Innovations Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi
Abstract: An anti-tail buffet device leverages existing rotorcraft components to attenuate a tailboom's lateral “ringing” from air buffeting. Anti-buffet masses are tuned to the tailboom's lateral-bending or torsional natural frequency such that when lateral motion occurs, the response at this frequency is cancelled by the anti-buffet system, preventing this vibration from entering into the tailboom structure. Motion stops prevent over-travel. The mass of the tail rotor actuator is soft-mounted, such that its natural frequency is equal to the tailboom's lateral-bending or torsional natural frequency. When lateral loading occurs on the tail rotor disk, the lateral response at this frequency is attenuated by the soft-mounted tail rotor actuator, thereby preventing the vibration in the tailboom structure.
-
公开(公告)号：US20210016873A1
公开(公告)日：2021-01-21
申请号：US17038893
申请日：2020-09-30
Applicant: Textron Innovations Inc.
Inventor： Carlos Fenny , Sung Kim , Kip Campbell , Jouyoung Jason Choi
Abstract: An electric reaction control system that can selectively expel a “burst” or “puff” of air to alter the orientation of the aircraft during flight. An aircraft incorporating ducting, an air compressor, an electric motor, and a plurality of nozzles can facilitate in-flight trajectory modifications. When an air burst is needed to provide thrust for the purposes of reaction control, nozzles are selectively opened and closed to provide roll, pitch, and yaw of the aircraft. The ERCS can facilitate an electric aircraft that would be very agile and very light, utilizing electric power, as opposed to jet power.
-
公开(公告)号：US10569870B2
公开(公告)日：2020-02-25
申请号：US15355347
申请日：2016-11-18
Applicant: Textron Innovations Inc.
Inventor： Jouyoung Jason Choi , Gary Miller , Richard Erler Rauber , Thomas Clement Parham, Jr. , Alan Carl Ewing , Frank Bradley Stamps
Abstract: A proprotor system for tiltrotor aircraft having a helicopter mode and an airplane mode. The proprotor system includes a hub and a plurality of proprotor blades coupled to the hub such that each proprotor blade is operable to independently flap relative to the hub and independently change pitch. In the airplane mode, the proprotor blades have a first in-plane frequency greater than 2.0/rev.
-
-
-
-
-
-
-
Search Results
18
records
(took 0.015 seconds)
