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公开(公告)号：US11136115B2
公开(公告)日：2021-10-05
申请号：US16013201
申请日：2018-06-20
Applicant: Bell Helicopter 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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公开(公告)号：US11097836B2
公开(公告)日：2021-08-24
申请号：US16360803
申请日：2019-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi , Joseph Richard Carpenter , Steve Michael Loveland
IPC: B64C27/00
Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
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公开(公告)号：US20200156773A1
公开(公告)日：2020-05-21
申请号：US16197761
申请日：2018-11-21
Applicant: Bell Helicopter Textron 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
Abstract: A vibration attenuator for an aircraft has first and second coaxial spinners configured for rotation about a mast axis and relative to a rotor. Upper and lower weights of each spinner are spaced radially from the axis and positioned 180 degrees from each other about the axis. The weights of each spinner are spaced from each other a distance parallel to the mast axis, each weight rotating about the mast axis in a different plane. The spinners rotate together relative to the rotor at a selected angular rate and are selectively rotatable relative to each other between a minimum-moment configuration, in which the upper weight of each spinner is angularly aligned with the lower weight of the other spinner, and a maximum-moment configuration, in which the upper weights are angularly aligned and the lower weights are angularly aligned, producing a whirling moment about the mast axis as the spinners rotate.
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公开(公告)号：US20190118942A1
公开(公告)日：2019-04-25
申请号：US15792430
申请日：2017-10-24
Applicant: Bell Helicopter Textron Inc.
Inventor： Sung Kim , Jouyoung Jason Choi , Frank Bradley Stamps
Abstract: Systems and methods of operating a tiltrotor aircraft include providing a control system that includes sensors and/or gauges that provide feedback regarding hub shear forces in rotor systems of the aircraft that produce aeroelastic instability known as whirl flutter. Feedback from the sensors and/or gauges is communicated to a flight control subsystem that includes an algorithm that provides a cascading set of responses to control whirl flutter and a failsafe that adjusts operational characteristics of the aircraft in response to the continuation or excitation of the whirl flutter.
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公开(公告)号：US20190002085A1
公开(公告)日：2019-01-03
申请号：US15636448
申请日：2017-06-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Thomas Clement Parham, JR. , Gary Miller , Frank Bradley Stamps
IPC: B64C11/06 , B64C29/00 , B64C11/32 , F16F15/121
CPC classification number: B64C11/06 , B64C11/32 , B64C27/35 , B64C27/51 , B64C27/635 , B64C29/0033 , F16C23/043 , F16C27/02 , F16C2326/43 , F16F15/1208 , F16F15/121 , F16F15/124
Abstract: A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.
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Patent Agency Ranking
公开(公告)号：US20180339773A1
公开(公告)日：2018-11-29
申请号：US15606275
申请日：2017-05-26
Applicant: Bell Helicopter Textron Inc.
Inventor： John Richard McCullough , Paul K. Oldroyd , Mark Adam Wiinikka , Jouyoung Jason Choi
Abstract: A rotor assembly for an aircraft is operable to generate a variable thrust vector. The rotor assembly includes a mast that is rotatable about a mast axis. A ball joint is positioned about and non rotatable with the mast. A tilt control assembly is positioned on and has a tilting degree of freedom relative to the ball joint. The tilt control assembly is non rotatable with the mast. A rotor hub is rotatably coupled to the tilt control assembly. The rotor hub is rotatable with the mast in a rotational plane and tiltable with the tilt control assembly. The rotor hub includes a plurality of grips each coupled to a rotor blade. Actuation of the tilt control assembly changes the rotational plane of the rotor hub relative to the mast axis, thereby generating the variable thrust vector.
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公开(公告)号：US11173521B2
公开(公告)日：2021-11-16
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：US20200298967A1
公开(公告)日：2020-09-24
申请号：US16360803
申请日：2019-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi , Joseph Richard Carpenter , Steve Michael Loveland
IPC: B64C27/00
Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
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公开(公告)号：US10457380B2
公开(公告)日：2019-10-29
申请号：US15636448
申请日：2017-06-28
Applicant: Bell Helicopter Textron Inc.
Inventor： Jouyoung Jason Choi , Thomas Clement Parham, Jr. , Gary Miller , Frank Bradley Stamps
IPC: B64C11/06 , B64C27/35 , B64C27/51 , B64C27/635 , B64C29/00 , B64C11/32 , F16F15/121 , F16C23/04 , F16C27/02 , F16F15/12 , F16F15/124
Abstract: A proprotor system operable for use on a tiltrotor aircraft having a helicopter flight mode and an airplane flight mode. The proprotor system includes a rotor hub and a plurality of proprotor blades coupled to the rotor hub such that each proprotor blade has three independent degrees of freedom relative to the rotor hub including blade pitch about a pitch change axis, blade flap about a flapping axis and lead-lag about a lead-lag axis. Each of a plurality of spherical bearings couples one of the proprotor blades with the rotor hub. In addition, each of a plurality of lead-lag dampers couples one of the proprotor blades with the rotor hub, wherein each lead-lag damper is aligned with the pitch change axis of the respective proprotor blade, thereby providing pitch independent lead-lag damping.
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公开(公告)号：US20190002078A1
公开(公告)日：2019-01-03
申请号：US15638345
申请日：2017-06-29
Applicant: Bell Helicopter Textron Inc.
Inventor： Thomas Clement Parham, Jr. , Jeffrey Bosworth , Gary Miller , Frank Bradley Stamps , Jouyoung Jason Choi , Paul K. Oldroyd , Richard Erler Rauber , Michael Scott Seifert
Abstract: A wing airframe for a wing of a tiltrotor aircraft includes a wing airframe core assembly and a wing skin assembly disposed on the wing airframe core assembly. The wing skin assembly includes an outer skin and a damping sublayer, the damping sublayer interposed between the outer skin and the wing airframe core assembly. The tiltrotor aircraft includes a pylon assembly subject to aeroelastic movement during forward flight. The wing is subject to deflection in response to the aeroelastic movement of the pylon assembly. The damping sublayer reduces the deflection of the wing, thereby stabilizing the wing during forward flight
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