公开(公告)号：US20190061930A1

公开(公告)日：2019-02-28

申请号：US15687350

申请日：2017-08-25

Applicant: Bell Helicopter Textron Inc.

Inventor： Dalton T. Hampton ,  Timothy Kent Ledbetter ,  Drew A. Sutton ,  Bryan W. Marshall ,  Paul Sherrill ,  Frank B. Stamps ,  James Donn Hethcock ,  Andrew Paul Haldeman ,  Paul K. Oldroyd

IPC: B64C27/473 ,  B64C27/06 ,  B64F5/40 ,  B29C73/04

Abstract: In one embodiment, a method may comprise coupling a plurality of reinforcement fibers to a plurality of spherical components; inserting the plurality of spherical components into an enclosure; and heating the enclosure to cause the plurality of spherical components to expand, wherein the plurality of spherical components expands to form a geodesic structure, wherein the geodesic structure comprises a plurality of polyhedron components configured in a geodesic arrangement.

公开(公告)号：US20190061927A1

公开(公告)日：2019-02-28

申请号：US15684385

申请日：2017-08-23

Applicant: Bell Helicopter Textron Inc.

Inventor： Gary Miller ,  Frank B. Stamps

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

CPC classification number: B64C27/33 ,  B64C27/605 ,  B64C29/0033

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：US10112709B2

公开(公告)日：2018-10-30

申请号：US14494036

申请日：2014-09-23

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： David E. Heverly, II ,  Frank B. Stamps ,  Michael Smith

IPC: B64C27/635 ,  B64C27/51

Abstract: A rotor system includes a hub assembly, a first, second, and third rotor blade rotatably attached to the hub assembly, a first, second, and third damper pivotally attached to the hub assembly and pivotally attached to the first, second, and third rotor blade, respectively, and a control system operably associated with the first, second, and third damper. A method to control vibratory forces exerted on the hub assembly via the first and second rotor blade includes separately controlling a dynamic spring rate of each of the first and second dampers with the control system.

公开(公告)号：US10106251B2

公开(公告)日：2018-10-23

申请号：US14485967

申请日：2014-09-15

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Christopher Foskey ,  Frank B. Stamps

IPC: B64C27/46 ,  B64C27/473

Abstract: A rotor blade system includes a rotor blade having an outboard section and an inboard section, a hinge joint rigidly attached to the outboard section, and an adhedral tip engaged with the hinge joint. A method includes pivotally attaching an adhedral tip to the rotor blade and pivoting the adhedral tip during flight to change the flight performance characteristics of the blade during flight.

公开(公告)号：US20180290738A1

公开(公告)日：2018-10-11

申请号：US16006552

申请日：2018-06-12

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Richard E. Rauber ,  Frank B. Stamps

IPC: B64C27/41 ,  B64C29/00 ,  B64C27/32

Abstract: The present application provides a drive link for a constant-velocity joint of an aircraft rotor, the link connecting a drive hub attached to a driveshaft to a rotor yoke. The link comprises a leading bearing connected to the drive hub, a trailing bearing connected to the yoke, a central portion between the bearings, and a tension loop connecting the bearings. The tension loop is formed from a composite material and is formed as a continuous band. The tension loop transfers drive forces from the leading bearing to the trailing bearing for driving the yoke in rotation with the driveshaft.

公开(公告)号：US20180273167A1

公开(公告)日：2018-09-27

申请号：US15468069

申请日：2017-03-23

Applicant: Bell Helicopter Textron Inc.

Inventor： Matthew R. Carr ,  Matthew E. Louis ,  Kirk L. Groninga ,  Daniel B. Robertson ,  Frank B. Stamps ,  Albert G. Brand ,  Eric A. Sinusas

IPC: B64C27/82 ,  F04D17/16 ,  F04D29/46

CPC classification number: B64C27/82 ,  B64C2027/8245 ,  B64C2027/8254 ,  F04D17/16 ,  F04D29/462

Abstract: In one embodiment, a rotorcraft comprises a fuselage, a tail boom, a rotor system, and a centrifugal blower system. The centrifugal blower system comprises a centrifugal blower configured to generate thrust using an airflow, wherein the centrifugal blower is located within the tail boom. The centrifugal blower system also comprises a plurality of ducts configured to control the thrust generated by the centrifugal blower, wherein the plurality of ducts is located on a portion of the tail boom surrounding the centrifugal blower, and wherein the plurality of ducts comprises one or more adjustable ducts configured to vary a size of an associated duct opening.

公开(公告)号：US10065730B2

公开(公告)日：2018-09-04

申请号：US14600180

申请日：2015-01-20

Applicant: Bell Helicopter Textron Inc.

Inventor： David E. Heverly, II ,  Jeremy DeWaters ,  Frank B. Stamps

IPC: B64C27/00 ,  B64C29/00

Abstract: A vibration control system for a rotor hub provides vibration attenuation in an aircraft by reducing the magnitude of rotor induced vibratory. The system can include a force generating device attached to a rotor hub which rotates along with the rotor at the rotational speed of the rotor. Vibratory shear force is generated by rotating unbalanced weights each about an axis non-concentric with the rotor hub axis at high speed to create large centrifugal forces. The rotational speed of the weights can be a multiple of the rotor rotational speed to create shear forces for canceling rotor induced vibrations. The amplitude of the generated shear force is controlled by indexing the positions of the unbalanced weights relative to each other, while the phase of the shear force is adjusted by equally phasing each weight relative to the rotor.

公开(公告)号：US10029783B2

公开(公告)日：2018-07-24

申请号：US14954694

申请日：2015-11-30

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Troy Schank ,  Frank B. Stamps

IPC: B64C27/41 ,  B64C27/30 ,  B64C27/50 ,  B64C27/52 ,  B64C27/32 ,  B64C27/615 ,  B64C11/28 ,  B64C27/605 ,  B64C29/00

Abstract: A method of selectively preventing flapping of a rotor hub includes providing a flapping lock proximate to a rotor hub and shaft assembly and moving the flapping lock from an unlocked position to a locked position, the flapping lock operable in the locked position to prevent at least some flapping movement of the rotor hub relative to the shaft, the flapping lock operable in the unlocked position to allow the at least some flapping movement of the rotor hub relative to the shaft.

公开(公告)号：US20170307009A1

公开(公告)日：2017-10-26

申请号：US15646546

申请日：2017-07-11

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Frank B. Stamps ,  Bryan W. Marshall

IPC: F16C23/04 ,  B64C27/48 ,  B64C27/82

Abstract: A rotary system and method to control feathering movement of a rotor blade. The system having a yoke arm configured to rotate a rotor blade. A first bearing and a second bearing are utilized to secure the rotor blade to the yoke arm and are configured to restrict longitudinal and transverse movement, while allowing feathering movement of the rotor blade relative to yoke arm.

公开(公告)号：US09764832B2

公开(公告)日：2017-09-19

申请号：US14510813

申请日：2014-10-09

Applicant: BELL HELICOPTER TEXTRON INC.

Inventor： Jason L. Hoyle ,  Frank B. Stamps

IPC: B64C27/56 ,  B64C27/605 ,  B64C27/32

CPC classification number: B64C27/605 ,  B64C27/32

Abstract: A rotor blade system includes a hub assembly pivotally attached to a rotor blade, a mast attached to the hub assembly, and a swashplate engaged with the mast, the swashplate includes a non-rotating ring and a rotating ring. The method to raise the swashplate includes using an anti-drive link system pivotally engaged with a transmission top case and pivotally engaged with the non-rotating ring.