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公开(公告)号：US10392098B2
公开(公告)日：2019-08-27
申请号：US16289438
申请日：2019-02-28
Applicant: Bell Helicopter Textron Inc.
IPC: B63H1/06 , B64C11/34 , B64C29/00 , B64C27/605 , B64C27/41 , B64C11/00 , F16D3/62 , B64C27/473
Abstract: A high stiffness hub assembly for a rotor system operable to rotate with a mast of a rotorcraft. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has a plurality of blade arms each configured to hold a rotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, a plurality of drive links and a plurality of pillow blocks. The trunnion assembly is coupled to the mast and has a plurality of outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate.
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公开(公告)号：US20170259911A1
公开(公告)日：2017-09-14
申请号：US15350073
申请日：2016-11-13
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Brad Stamps , Thomas Parham, JR. , Amarjit Olenchery Kizhakkepat
IPC: B64C27/00
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.
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公开(公告)号：US11084575B2
公开(公告)日：2021-08-10
申请号：US16084970
申请日：2017-03-14
Applicant: Bell Helicopter Textron, Inc.
Inventor： Jouyoung Jason Choi , David Heverly , Michael Seifert , Michael Smith , Frank Bradley 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.
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公开(公告)号：US10472057B2
公开(公告)日：2019-11-12
申请号：US15432910
申请日：2017-02-14
Applicant: Bell Helicopter Textron Inc.
Inventor： Gary Miller , Frank B. Stamps , Jouyoung Jason Choi , Thomas C. Parham, Jr. , Alan Ewing , Richard E. Rauber
IPC: B64C27/635 , B64C27/605 , B64C27/72
Abstract: An aircraft rotor assembly has a central hub and a plurality of rotor blades coupled to the hub for rotation with the hub about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is formed by a flexure coupling the associated blade to the hub. Each pivot is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the hub, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Elastic deformation of the flexure produces a biasing force for biasing the associated blade toward the neutral position, and the biasing force is selected to achieve a first in-plane frequency of greater than 1/rev for each blade.
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公开(公告)号：US20190300152A1
公开(公告)日：2019-10-03
申请号：US15938979
申请日：2018-03-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Frank B. Stamps
Abstract: One example of a rotor assembly comprises: a rotor hub operable to rotate based on rotation of a mast; a first rotor blade pivotally attached to the rotor hub; a bracing member pivotally attached to the rotor hub at a first end and pivotally attached to the first rotor blade at a second end; and a linkage mechanism coupling the first rotor blade to a second rotor blade. The bracing member is operable to transfer a coning movement of the first rotor blade to a movement of the linkage mechanism and a corresponding coning movement of the second rotor blade.
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Patent Agency Ranking
公开(公告)号：US20190263512A1
公开(公告)日：2019-08-29
申请号：US16284931
申请日：2019-02-25
Applicant: Bell Helicopter Textron Inc.
Inventor： David Heverly , Frank Bradley Stamps , Gary Miller , Richard E. Rauber , Thomas C. Parham, JR. , Michael R. Smith , Michael Scott Seifert , Jouyoung Jason Choi
Abstract: A vibration attenuator for a rotor is rotatable about a mast axis and has a frame configured for rotation about the mast axis relative to the rotor. A first mass is axially translatable in a first direction relative to the frame parallel to a first axis, and a first biasing force urges the first mass toward a first-mass rest position in which the first mass is symmetric about the mast axis. A second mass is axially translatable in a second direction relative to the frame parallel to a second axis, and a second biasing force urges the second mass toward a second-mass rest position in which the second mass is symmetric about the mast axis. A selected first or second mass moves radially outward from the rest position to oppose vibrations in the rotor.
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公开(公告)号：US10384776B2
公开(公告)日：2019-08-20
申请号：US15438972
申请日：2017-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Daniel Bryan Robertson , Kirk Landon Groninga , Frank Bradley Stamps , Matthew Edward Louis
IPC: B64C39/00 , B64C3/32 , B64C3/14 , B64D27/12 , B64D27/26 , B64C29/00 , B64C27/26 , B64C27/28 , B64C27/52 , B64C23/02
Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.
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公开(公告)号：US20190193836A1
公开(公告)日：2019-06-27
申请号：US16289438
申请日：2019-02-28
Applicant: Bell Helicopter Textron Inc.
IPC: B64C11/34 , B64C27/605 , B64C29/00 , B64C11/00
CPC classification number: B64C11/34 , B64C11/008 , B64C27/41 , B64C27/605 , B64C29/0033 , B64C2027/4736
Abstract: A high stiffness hub assembly for a rotor system operable to rotate with a mast of a rotorcraft. The hub assembly includes a yoke and a constant velocity joint assembly. The yoke has a plurality of blade arms each configured to hold a rotor blade. The constant velocity joint assembly provides a torque path from the mast to the yoke that includes a trunnion assembly, a plurality of drive links and a plurality of pillow blocks. The trunnion assembly is coupled to the mast and has a plurality of outwardly extending trunnions. Each drive link has a leading bearing coupled to one of the trunnions and a trailing bearing coupled to one of the pillow blocks. Each pillow block is independently mounted between an upper surface of the yoke and a hub plate.
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公开(公告)号：US20180237136A1
公开(公告)日：2018-08-23
申请号：US15438972
申请日：2017-02-22
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Daniel Bryan Robertson , Kirk Landon Groninga , Frank Bradley Stamps , Matthew Edward Louis
IPC: B64C39/00 , B64C3/32 , B64C3/14 , B64D27/12 , B64D27/26 , B64C29/00 , B64C27/26 , B64C27/28 , B64C27/52
CPC classification number: B64C39/005 , B64C3/14 , B64C3/32 , B64C23/02 , B64C27/26 , B64C27/28 , B64C27/52 , B64C29/0033 , B64C39/003 , B64C2003/143 , B64D27/12 , B64D27/26 , B64D2027/262 , Y02T50/12
Abstract: A tiltrotor aircraft has a fuselage and a wing having upper and lower surfaces with a plurality of channels extending therebetween, each with a cycloidal rotor mounted therein. At least two pylon assemblies are rotatably coupled to the wing to selectively operate the tiltrotor aircraft between helicopter and airplane flight modes. Each pylon assembly includes a mast and a proprotor assembly operable to rotate with the mast to generate thrust. At least one engine provides torque and rotational energy to the proprotor assemblies and the propulsion assemblies. Each of the cycloidal rotors has a plurality of blades that travels in a generally circular path and has a plurality of pitch angle configurations such that each cycloidal rotor is operable to generate a variable thrust and a variable thrust vector, thereby providing vertical lift augmentation, roll control, yaw control and/or pitch control in the helicopter flight mode.
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公开(公告)号：US20180162526A1
公开(公告)日：2018-06-14
申请号：US15375367
申请日：2016-12-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, JR. , Jouyoung Jason Choi , Gary Miller , Frank Bradley Stamps , Richard Erler Rauber
CPC classification number: B64C29/0033 , B64C27/41 , B64C27/51 , B64C27/54
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 about a flapping axis and independently change pitch about a pitch change axis. The proprotor blades have a first in-plane frequency less than 1.0/rev.
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