公开(公告)号：US10196136B2

公开(公告)日：2019-02-05

申请号：US15630535

申请日：2017-06-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Smith ,  Cheng-Ho Tho ,  Anand Kumar Marimuthu

IPC: B64C27/00 ,  B26D1/25 ,  B26D1/12 ,  B26D1/00

Abstract: Some examples of a cable cutting system include a first cutting apparatus that includes a recess to receive a cable. The system includes a second cutting apparatus separate from and attached to the first cutting apparatus. The second cutting apparatus includes multiple cutting surfaces arranged to cut the cable received at the recess.

公开(公告)号：US20190032491A1

公开(公告)日：2019-01-31

申请号：US15658928

申请日：2017-07-25

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey Nissen ,  Jared M. Paulson ,  Thomas S. Chiang

IPC: F01D5/14 ,  F01D5/00 ,  B64C11/26 ,  B33Y50/02 ,  B22F3/00 ,  B29C64/386 ,  B33Y10/00 ,  B29C73/04 ,  B22F5/04 ,  B33Y80/00 ,  B23P6/00 ,  B23K15/00 ,  B23K26/342

Abstract: In a first aspect, there is a method of making a rotor blade, including designing at least one of an upper skin, a lower skin, a support network, and components therefor; and forming at least one of the upper skin, the lower skin, a support network, and components therefor using an additive manufacturing process. In a second aspect, there is an airfoil member having a root end, a tip end, a leading edge, and a trailing edge, the airfoil member including an upper skin; a lower skin; and a support network having a plurality of interconnected support members in a lattice arrangement and/or a reticulated arrangement, the support network being configured to provide tailored characteristics of the airfoil member. Also provided are methods and systems for repairing an airfoil member.

公开(公告)号：US20190031339A1

公开(公告)日：2019-01-31

申请号：US16154342

申请日：2018-10-08

Applicant: Bell Helicopter Textron Inc.

Inventor： John Richard McCullough ,  Paul K. Oldroyd

IPC: B64C29/02 ,  B64C39/04 ,  B64C39/08 ,  B64C11/46 ,  B64C11/32 ,  B64C1/00 ,  B64C39/02

Abstract: An aircraft operable to transition between thrust-borne lift in a VTOL orientation and wing-borne lift in a biplane orientation. The aircraft includes an airframe having first and second wings with first and second pylons extending therebetween. The first and second wings each having first and second outboard nacelle stations. A two-dimensional distributed thrust array is attached to the airframe. The thrust array including a plurality of outboard propulsion assemblies coupled to the first and second outboard nacelle stations of the first and second wings. A flight control system is coupled to the airframe and is operable to independently control each of the propulsion assemblies. A cargo hook module is coupled to the airframe. The cargo hook module is operable for external load operations.

公开(公告)号：US20190024780A1

公开(公告)日：2019-01-24

申请号：US15656487

申请日：2017-07-21

Applicant: Bell Helicopter Textron Inc.

Inventor： Ryan Thomas Ehinger ,  Ron Woods

IPC: F16H57/08 ,  F16H1/28 ,  G01M13/02

Abstract: A method of optimizing a planetary gear system for continued operation after failure of a planet gear includes providing a planetary gear system and reducing a backup ratio of a planet gear of the planetary gear system by reducing a rim thickness of the planet gear.

公开(公告)号：US20190023386A1

公开(公告)日：2019-01-24

申请号：US15658190

申请日：2017-07-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Richard E. Rauber ,  Frank Bradley Stamps

IPC: B64C27/35 ,  B64C27/14

CPC classification number: B64C27/35 ,  B64C27/14 ,  B64C27/41

Abstract: A rotor hub assembly that includes a yoke configured to attach blades thereto, a universal joint configured to attach to, and transmit forces between, a mast and the yoke, and an elastomeric member configured to attenuate vibrations transmitted from the universal joint to the mast.

公开(公告)号：US20190016441A1

公开(公告)日：2019-01-17

申请号：US16035397

申请日：2018-07-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Troy Cyril Schank ,  Andrew Ryan Maresh ,  Chyau-Song Tzeng

IPC: B64C11/28 ,  B64C11/32 ,  B64C27/30 ,  B64C29/00

Abstract: A mechanism for folding a rotor blade that is rotatably coupled to a blade cuff about a blade-fold axis between an extended position and a folded position. The mechanism includes a swash plate configured to translate relative to a mast, a pitch link rotatably coupled to the swash plate, a pitch horn rotatably coupled to the pitch link, a crank coupled to the pitch horn, and a link rotatably coupled to the crank and rotatably coupled to the rotor blade. The pitch horn and the crank being configured to commonly rotate relative to the blade cuff about a crank axis in response to translation of the swash plate, wherein the crank axis passes through the blade cuff.

公开(公告)号：US10179438B2

公开(公告)日：2019-01-15

申请号：US15273775

申请日：2016-09-23

Applicant: Bell Helicopter Textron Inc.

Inventor： Sylvain Tessier ,  Richard Gingras ,  Jacques Dionne ,  Bryan Linington

IPC: B29C70/38 ,  B29C70/34 ,  B29C70/54 ,  B64C1/12 ,  B64C1/14 ,  B29C70/30 ,  B64C27/04 ,  B64F5/10 ,  B29K105/06 ,  B29L31/30 ,  B29L31/00

Abstract: A method of manufacturing a door skin and a fuselage wall having a doorway and a member extending into the doorway for abutting the door includes placing a first sheet of uncured composite material on a mold plate to define the door and fuselage skin, disposing an insert over the first sheet overlapping a desired periphery of the door, placing a second sheet of uncured composite material on a peripheral portion of the insert and over the first sheet adjacent the peripheral portion of the insert to form the member, curing the sheets and bonding the sheets together adjacent the insert during the cure, removing the insert from between the sheets after cure, and separating the door skin from the wall skin after cure by moving a cutting tool through the first sheet and without penetrating the second sheet around the desired periphery of the door. An assembly for manufacturing the door skin and a fuselage wall is also discussed.

公开(公告)号：US20190009898A1

公开(公告)日：2019-01-10

申请号：US15645110

申请日：2017-07-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey M. Bosworth ,  Kyle T. Cravener

IPC: B64C27/605 ,  B64C27/72

CPC classification number: B64C27/605 ,  B64C27/72 ,  B64C2027/7294

Abstract: A pitch horn assembly for an aircraft including a blade attachment member having a first end, a second end configured to be coupled to a rotor blade; and a blade attachment axis extending between the first end and the second end of the blade attachment member; a moveable arm configured to be coupled to the blade attachment member at a pitch horn axis, the moveable arm having a first end configured to be coupled to a pitch link; a second end; and a moveable arm axis extending between the first end and the second end of the moveable arm; an extendable member configured to be coupled to the blade attachment member and the moveable arm of the pitch horn, wherein the extendable member moves the moveable arm about the pitch horn axis. An embodiment provides a method of adjusting a pitch-flap coupling in an aircraft.

公开(公告)号：US10173771B2

公开(公告)日：2019-01-08

申请号：US15990610

申请日：2018-05-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Steven Ray Ivans ,  Nathan Gabriel Wu

IPC: B64C27/22 ,  B64C29/00 ,  B64C11/00 ,  B64C3/38 ,  B64C7/02 ,  B64C5/08 ,  B64C27/28 ,  B64C29/02

Abstract: A pylon assembly for a tiltrotor aircraft includes a fixed pylon having an outboard end. A rotor assembly is rotatably coupled to the fixed pylon and is operable to rotate between a a vertical takeoff and landing orientation and a forward flight orientation. The rotor assembly includes a proprotor operable to produce a slipstream. A wing extension is rotatably coupled to the outboard end of the fixed pylon. The wing extension is operable to rotate generally with the rotor assembly such that a minimal dimension of the wing extension remains in the slipstream of the proprotor.

公开(公告)号：US20190004542A1

公开(公告)日：2019-01-03

申请号：US16108479

申请日：2018-08-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Sung Kyun Kim

IPC: G05D1/08 ,  G05D1/10 ,  B64C13/04

Abstract: In accordance with an embodiment, a method of operating a rotorcraft includes transitioning from a first mode to a second mode when a velocity of the rotorcraft exceeds a first velocity threshold. Transitioning between the first and second modes includes fading out a gain of a dynamic controller over a first period of time, and decreasing a value of an integrator of the dynamic controller over a second period of time.