公开(公告)号：US20200070996A1

公开(公告)日：2020-03-05

申请号：US16120676

申请日：2018-09-04

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi C. Hefner ,  Frank B. Stamps ,  Alan C. Ewing ,  Jaret F. Burgess ,  Carey W. Cannon

IPC: B64D35/04 ,  B64C27/26 ,  B64C27/14 ,  B64C27/06 ,  B64C27/82 ,  B64C11/30

Abstract: A pusher rotorcraft is provided in one example embodiment and may include at least one engine in mechanical communication with a drop-down gearbox; a driveshaft in mechanical communication with the drop-down gearbox, a main rotor gearbox, and a tail system gearbox; a main rotor system in mechanical communication with the main rotor gearbox; an anti-torque system in mechanical communication with the tail system gearbox; and a pusher propeller system in mechanical communication with the tail system gearbox.

公开(公告)号：US10543916B2

公开(公告)日：2020-01-28

申请号：US15603019

申请日：2017-05-23

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Ken Shundo ,  Mithat Yuce ,  Frank B. Stamps

IPC: B64C27/80 ,  B64C27/52 ,  B64C27/10 ,  B64C27/32 ,  B64C27/35 ,  B64C27/48 ,  B64C27/51

Abstract: A rotor assembly includes a yoke operably associated with a rotor blade. The yoke includes a first device and a second device that attach the rotor blade to the yoke. The first device is configured to allow transverse movement of the rotor blade about a chord axis and rotational movement about a pitch-change axis. The second device is configured to allow rotational movement of the rotor blade solely about the pitch-change axis. The method includes rotating rotor assembly about a first plane of rotation, while retaining a relatively stiff out-of-plane rotation and a relatively soft in-plane rotation during flight.

公开(公告)号：US20190375496A1

公开(公告)日：2019-12-12

申请号：US16547003

申请日：2019-08-21

Applicant: Bell Helicopter Textron Inc.

Inventor： Gary Miller ,  Frank B. Stamps

IPC: B64C27/33 ,  B64C27/605 ,  B64C29/00

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, an adapter ring, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the swashplate and the adapter ring, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the swashplate and the adapter ring, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

公开(公告)号：US20190263502A1

公开(公告)日：2019-08-29

申请号：US16408057

申请日：2019-05-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Gary Miller ,  Frank B. Stamps

IPC: B64C11/32 ,  B64C11/06 ,  B64C29/00 ,  B64C11/30 ,  B64C27/605

Abstract: In one embodiment, a rotor hub comprises a yoke for attaching a plurality of rotor blades, a constant velocity joint to drive torque from a mast to the yoke and to enable the yoke to pivot, and a rotor control system configured to adjust an orientation of the plurality of rotor blades. Moreover, the rotor control system comprises: a swashplate, a phase adapter fulcrum, a plurality of actuators controlled based on a flight control input, a plurality of lower pitch links configured to transfer motion between the plurality of actuators and the swashplate, a plurality of phase adjustment levers configured to adjust a control phase associated with motion transferred between the plurality of actuators and the plurality of lower pitch links, and a plurality of upper pitch links configured to adjust a pitch of the plurality of rotor blades, wherein there are more upper pitch links than lower pitch links.

公开(公告)号：US10210856B1

公开(公告)日：2019-02-19

申请号：US15933810

申请日：2018-03-23

Applicant: Bell Helicopter Textron Inc.

Inventor： Levi C. Hefner ,  Frank B. Stamps

IPC: G10K11/178 ,  G10K11/175 ,  B64C27/04 ,  B64C27/82 ,  H04R1/28

Abstract: A noise control system for a ducted rotor assembly, the ducted rotor assembly including a hub, a duct, and two or more blades coupled to the hub and supported by the duct. The noise control system including a microphone configured to receive a sound input generated by the ducted rotor assembly, the microphone configured for association with the hub; a speaker unit configured to generate a cancellation noise, the speaker configured for association with the hub; and a controller operably connected to the microphone and the speaker unit, the controller configured to selectively adjust harmonics of the cancellation noise to reduce an acoustic signature of the ducted rotor assembly. In another aspect, there is provided a rotorcraft with a ducted rotor assembly in a tail portion including a noise control system. In a third aspect, there is a method of reducing an acoustic signature of a ducted rotor assembly.

公开(公告)号：US20180186447A1

公开(公告)日：2018-07-05

申请号：US15398919

申请日：2017-01-05

Applicant: Bell Helicopter Textron, Inc.

Inventor： Gary Miller ,  Frank B. Stamps

IPC: B64C27/35 ,  B64C27/48

CPC classification number: B64C27/35 ,  B64C27/33 ,  B64C27/48 ,  B64C27/51 ,  B64C27/54

Abstract: An aircraft rotor assembly has a central yoke and a plurality of rotor blades coupled to the yoke for rotation with the yoke about an axis, each blade having a Lock number of approximately 5 or greater. A lead-lag pivot for each blade is a radial distance from the axis and allows for in-plane lead-lag motion of the associated blade relative to the yoke, each pivot allowing for in-plane motion from a neutral position of at least 1 degree in each of the lead and lag directions. Lead and lag motion of each blade is opposed by a biasing force that biases 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.

公开(公告)号：US10005553B2

公开(公告)日：2018-06-26

申请号：US14598961

申请日：2015-01-16

Applicant: Bell Helicopter Textron Inc.

Inventor： Emily Schofield ,  Chad Jarrett ,  Dan Sottiaux ,  Frank B. Stamps

IPC: B64C27/35 ,  F16C11/08 ,  F16F1/38 ,  F16C27/06 ,  B64C27/41 ,  F16D3/62 ,  B23P19/04 ,  F16C7/04

CPC classification number: B64C27/35 ,  B23P19/04 ,  B64C27/41 ,  F16C7/04 ,  F16C11/083 ,  F16C27/063 ,  F16C2326/43 ,  F16D3/62 ,  F16F1/3863 ,  Y10T29/49643 ,  Y10T29/4984

Abstract: An apparatus comprising a drivelink comprising a housing including a socket, wherein the socket comprises a cross-sectional area, and a bearing cartridge disposed within the socket, wherein a cross-sectional area of the cartridge is less than the cross-sectional area of the socket. An apparatus comprising a drivelink comprising a housing having a socket, and a bearing cartridge positioned within the socket and comprising a first portion and a second portion, wherein the first portion is configured to undergo compression when a load is applied to the drivelink, and wherein the second portion is configured to not be in tension when the load is applied to the drivelink.

公开(公告)号：US20180148160A1

公开(公告)日：2018-05-31

申请号：US15365061

申请日：2016-11-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Eric R. Gonzalez ,  Frank B. Stamps

IPC: B64C11/18 ,  B64C27/467 ,  B64C27/35 ,  B64C27/52 ,  B64C27/473 ,  B64C11/20 ,  B64C29/00

CPC classification number: B64C11/18 ,  B64C11/20 ,  B64C27/35 ,  B64C27/467 ,  B64C27/473 ,  B64C27/52 ,  B64C29/0033

Abstract: A rotor blade including a root portion adapted to be connected to a helicopter rotor hub for rotation therewith, the root portion having a first edge surface; a first movable member having a first movable surface adjacent to the first edge surface; a first elastomeric joint disposed between the root portion and the first movable member, the first elastomeric joint having an inner surface facing the first edge surface of the root portion and an outer surface facing the movable surface of the first movable member; and an actuating system mounted within the root portion and the first movable member for moving the first movable member. The first elastomeric joint deforms to adjust for shear from actuation of the first movable member to a first position during helicopter mode; and to a second position during airplane mode.

公开(公告)号：US09951808B2

公开(公告)日：2018-04-24

申请号：US14481177

申请日：2014-09-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Peter Q. Romano ,  Frank B. Stamps ,  Stephen R. Johnston ,  Peter H. Kintzinger

IPC: F16C11/06 ,  B64C27/00

CPC classification number: F16C11/0695 ,  B64C27/001 ,  B64C2027/002 ,  F16C11/0614 ,  F16C11/0628 ,  F16C11/0652 ,  F16C2326/43

Abstract: A bearing assembly can include a top retainer; a middle retainer having a first concave spherical surface; a bottom retainer having a second concave spherical surface; a spherical ball member; and an elastomeric member coupled to the first concave spherical surface, the second concave spherical surface, and an outer surface of the spherical ball member.

公开(公告)号：US09840325B2

公开(公告)日：2017-12-12

申请号：US14533869

申请日：2014-11-05

Applicant: Bell Helicopter Textron Inc.

Inventor： Drew Sutton ,  Frank B. Stamps

IPC: B64C27/605 ,  F16C17/10 ,  B23P15/00 ,  F16C11/08 ,  B64C27/54 ,  F16C11/06 ,  F16C27/06 ,  F16F1/393 ,  F16C33/20

CPC classification number: B64C27/605 ,  B23P15/003 ,  B23P2700/01 ,  B64C27/54 ,  F16C11/0614 ,  F16C11/083 ,  F16C17/10 ,  F16C27/063 ,  F16C33/20 ,  F16C2208/32 ,  F16C2326/43 ,  F16F1/393 ,  Y10T29/49636 ,  Y10T29/49643 ,  Y10T29/4971

Abstract: According to one embodiment, a bearing is situated between a pitch link and a swashplate or a hub. The bearing comprises an outer housing having a first opening therethrough, an intermediate housing adjacent the housing inside the first opening and having a second opening therethrough, and an inner housing adjacent the intermediate housing inside the second opening and having a third opening therethrough. The inner housing comprising a first inner surface and a second inner surface defining the third opening. A first member is adjacent the first inner surface inside the third opening having a fourth opening therethrough. A second member is adjacent the second inner surface inside the third opening having a fifth opening therethrough coaxial with the fourth opening.