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公开(公告)号：US11691723B2
公开(公告)日：2023-07-04
申请号：US17307845
申请日：2021-05-04
Applicant: Bell Textron Inc.
Inventor： Thomas C. Parham, Jr. , Frank Bradley Stamps , Jouyoung Jason Choi , Albert Gerard Brand , Michael Scott Seifert , Richard E. Rauber , John E. Brunken, Jr.
CPC classification number: B64C29/0033 , B64C11/008 , B64C11/02 , B64C11/32
Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.
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公开(公告)号：US20210380230A1
公开(公告)日：2021-12-09
申请号：US17406174
申请日：2021-08-19
Applicant: Bell Textron Inc.
Inventor： Carlos Alexander Fenny , Jouyoung Jason Choi
Abstract: An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.
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Patent Agency Ranking
公开(公告)号：US20220355924A1
公开(公告)日：2022-11-10
申请号：US17307845
申请日：2021-05-04
Applicant: Bell Textron Inc.
Inventor： Thomas C. Parham, JR. , Frank Bradley Stamps , Jouyoung Jason Choi , Albert Gerard Brand , Michael Scott Seifert , Richard E. Rauber , John E. Brunken, JR.
Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.
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公开(公告)号：US11649043B2
公开(公告)日：2023-05-16
申请号：US17406174
申请日：2021-08-19
Applicant: Bell Textron Inc.
Inventor： Carlos Alexander Fenny , Jouyoung Jason Choi
CPC classification number: B64C27/08 , B64C39/062 , B64D27/26 , G05D1/0202 , G05D1/0808 , B64D2027/262
Abstract: An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.
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公开(公告)号：US11414183B2
公开(公告)日：2022-08-16
申请号：US16541068
申请日：2019-08-14
Applicant: Bell Textron Inc.
Inventor： Jouyoung Jason Choi , Carlos Alexandra Fenny
Abstract: In an implementation, the compound helicopter may include at least one rotary wing system, at least one first power generator and at least one second power generator. The at least one first power generator may rotate the at least one rotary wing blade to provide lift and a primary thrust force in a first direction to the helicopter. The at least one second power generator may be connected to the helicopter and may provide lift and a secondary thrust force in a direction that is independent of a direction of the primary thrust force and may also provide a secondary thrust force in a direction that is substantially parallel to the primary thrust force.
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公开(公告)号：US20210047028A1
公开(公告)日：2021-02-18
申请号：US16541068
申请日：2019-08-14
Applicant: Bell Textron Inc.
Inventor： Jouyoung Jason Choi , Carlos Alexandra Fenny
Abstract: In an implementation, the compound helicopter may include at least one rotary wing system, at least one first power generator and at least one second power generator. The at least one first power generator may rotate the at least one rotary wing blade to provide lift and a primary thrust force in a first direction to the helicopter. The at least one second power generator may be connected to the helicopter and may provide lift and a secondary thrust force in a direction that is independent of a direction of the primary thrust force and may also provide a secondary thrust force in a direction that is substantially parallel to the primary thrust force.
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公开(公告)号：US11267561B2
公开(公告)日：2022-03-08
申请号：US16664675
申请日：2019-10-25
Applicant: Bell Textron Inc.
Inventor： David Heverly , Frank Bradley Stamps , Jouyoung Jason Choi , Michael R. Smith , Thomas C. Parham
Abstract: A vibration attenuator for a rotor of an aircraft has a track housing adapted for rotation relative to the rotor and configured for rotation at a second angular velocity greater than a first angular velocity of the rotor. A track is located within the track housing and has a reaction surface, a pair of weights being configured for movement within the track and in contact with the reaction surface. A stop assembly has a pair of stops spaced 180 degrees apart, the stops separating the weights from each other, and each weight being allowed to travel within the track between the stops. A motor rotates the track housing relative to the rotor. The weights are free to travel relative to each other between a minimum-force configuration, in which the weights are positioned 180 degrees apart, and a maximum-force configuration, in which both weights are adjacent one of the stops.
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