公开(公告)号：US20180134853A1

公开(公告)日：2018-05-17

申请号：US15847753

申请日：2017-12-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Iosif Daniel Rosca ,  Martin Salameh ,  Suong Van Hoa

IPC: C08J3/20 ,  B64D15/00 ,  C08J3/00

CPC classification number: C08J3/2053 ,  B64C2230/26 ,  B64D15/00 ,  C08J2401/02 ,  Y02T50/166

Abstract: According to one embodiment, a method of dispersing nanoparticles into a destination material includes providing a plurality of nanoparticles suspended in a carrier, adding a solvent to the plurality of nanoparticles suspended in a carrier, removing at least some of the carrier to yield the plurality of nanoparticles suspended in the solvent, mixing the nanoparticles suspended in the solvent with a destination material, and removing at least some of the solvent from the mixture of nanoparticles suspended in the solvent and the destination material.

公开(公告)号：US20180119742A1

公开(公告)日：2018-05-03

申请号：US15340680

申请日：2016-11-01

Applicant: Bell Helicopter Textron Inc.

Inventor： Brian Stanley Modrzejewski ,  Siddhesh Pradeep Raje ,  Kenneth Myron Jackson

IPC: F16C33/66 ,  F16C19/54

CPC classification number: F16C33/6677 ,  F16C19/163 ,  F16C19/54 ,  F16C19/546 ,  F16C33/6662 ,  F16C2326/43

Abstract: The present invention includes a rolling element bearing system and method of using the same, comprising: a ball bearing comprising an inner race coupled to an inner shaft (journal) at an outer surface of the inner shaft, an outer race coupled to an outer shaft at an inner surface of the outer shaft, and a roller element disposed between the inner race and the outer race, wherein the inner race and the outer surface of the inner shaft form a pocket between a portion of the inner race and the outer surface, and the inner race comprises an orifice through the inner race to fluidly connect the pocket and the rolling element.

公开(公告)号：US20180099759A1

公开(公告)日：2018-04-12

申请号：US15844451

申请日：2017-12-15

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Matthew Carl VanBuskirk ,  Andrew G. Baines ,  Keith Alan Stanney

IPC: B64D27/26 ,  B64C27/26 ,  F16C17/26 ,  F16C17/02 ,  B64C3/32 ,  B64D35/00 ,  B64C29/00 ,  F16H57/02

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64C27/22 ,  B64C27/26 ,  B64C29/0033 ,  B64D35/00 ,  B64D2027/266 ,  B64F5/40 ,  F16C17/02 ,  F16C17/26 ,  F16H2057/02043 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to the input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a journal bearing that provides a stiff coupling with the pylon assembly.

公开(公告)号：US20180099757A1

公开(公告)日：2018-04-12

申请号：US15792686

申请日：2017-10-24

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeffrey Matthew Williams ,  George Ryan Decker ,  James Everett Kooiman ,  Andrew G. Baines ,  Daniel J. Sweigard

IPC: B64D27/26 ,  B64D35/00 ,  B64C3/32 ,  B64C27/26 ,  B64C29/00 ,  F16C17/02 ,  F16C17/26

CPC classification number: B64D27/26 ,  B64C3/32 ,  B64C27/22 ,  B64C27/26 ,  B64C29/0033 ,  B64D35/00 ,  B64D2027/266 ,  B64F5/40 ,  F16C17/022 ,  F16C17/26 ,  F16H2057/02043 ,  Y10T29/49318 ,  Y10T74/1966

Abstract: A propulsion system for a tiltrotor aircraft includes an engine supported by the airframe and a fixed gearbox operably coupled to the engine. Inboard and outboard pedestals are supported by the airframe and positioned above the wing. A pylon assembly is rotatably coupled between the inboard and outboard pedestals. The pylon assembly includes a spindle gearbox having an input gear, a mast operably coupled to the input gear and a proprotor assembly operable to rotate with the mast. The spindle gearbox is rotatable about a conversion axis to selectively operate the tiltrotor aircraft between helicopter and airplane modes. A common shaft, rotatable about the conversion axis, is configured to transfer torque from an output gear of the fixed gearbox to an input gear of the spindle gearbox. Each of the inboard and outboard pedestals includes a spherical bearing providing a self-aligning coupling with the pylon assembly.

公开(公告)号：US09939391B1

公开(公告)日：2018-04-10

申请号：US15380408

申请日：2016-12-15

Applicant: Bell Helicopter Textron Inc.

Inventor： Edward A. Hohman

IPC: G01B11/00 ,  G01N21/956 ,  G01N21/88

CPC classification number: G01N21/95607 ,  G01N21/8806 ,  G01N21/8851

Abstract: A method of inspecting a component using a film overlay including providing the component, the component having a first surface, a core, and a second surface; positioning a film overlay having a reference indicia and a structural indicia on the first surface of the component; aligning the reference indicia on the film overlay with a reference feature on the component; positioning a testing probe on a top surface of the film overlay so the probe is aligned with the structural indicia; and transmitting a signal from the probe through the film overlay, the first surface, the core, and the second surface.

公开(公告)号：US20180095005A1

公开(公告)日：2018-04-05

申请号：US15285569

申请日：2016-10-05

Applicant: Bell Helicopter Textron Inc.

Inventor： Michael Christopher Burnett ,  Kyle Thomas Cravener

IPC: G01M13/04 ,  F16C41/00 ,  G01J5/08 ,  G01J5/02

CPC classification number: G01M13/04 ,  B64C27/35 ,  F16C41/00 ,  F16C2233/00 ,  F16C2326/43 ,  G01J5/0022

Abstract: The present invention includes an apparatus and method for measuring hysteretic heating or stress of one or more bearings of a craft comprising: one or more non-contact temperature sensors attached to the craft and directed toward the one or more bearings; and a computer connected to the one or more non-contact temperature sensors that measure the temperature, the stress, or both of the one or more bearings before, during, or after operation of the craft, wherein the one or more non-contact temperature sensors measure a change in temperature in the one or more bearings to monitor for heating or stress of the bearings.

公开(公告)号：US20180086444A1

公开(公告)日：2018-03-29

申请号：US15702912

申请日：2017-09-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Scott David Poster ,  Walter Riley ,  Gary Cope ,  Charles Hubert Speller, JR.

IPC: B64C27/14 ,  B64D35/00 ,  F16H57/02 ,  F16H57/04 ,  F16H1/28 ,  F16D3/00

CPC classification number: B64C27/14 ,  B60T1/062 ,  B64C27/12 ,  B64D35/00 ,  F16C2326/43 ,  F16D3/00 ,  F16D55/00 ,  F16H1/28 ,  F16H57/02 ,  F16H57/0413 ,  F16H57/0416 ,  F16H57/0417 ,  F16H2057/02026 ,  F16H2057/02043

Abstract: The present invention includes an aircraft drive system comprising a main rotor gearbox comprising a first and a second input; a first drive system comprising a first engine reduction gearbox connecting a first engine to the first input of the main rotor gearbox at a reduced shaft speed; and a second drive system independent from and redundant with the first drive system, the second drive system comprising a second engine reduction gearbox connecting a second engine to the second input of the main rotor gearbox at the reduced shaft speed.

公开(公告)号：US20180079500A1

公开(公告)日：2018-03-22

申请号：US15269825

申请日：2016-09-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Christopher Edward Foskey

IPC: B64C29/00 ,  B64C3/56 ,  B64C11/28 ,  B64C7/02 ,  B64C5/10 ,  B64C5/02

CPC classification number: B64C29/0033 ,  B64C3/56 ,  B64C5/02 ,  B64C5/10 ,  B64C7/02 ,  B64C11/28

Abstract: A tiltrotor aircraft having a VTOL flight mode, a forward flight mode and a storage mode includes a fuselage having a wing rotatably mounted thereto. The wing has an orientation generally perpendicular to the fuselage, in the flight modes, and an orientation generally parallel to the fuselage, in the storage mode. First and second pylon assemblies are positioned proximate outboard ends of the wing. First and second mast assemblies are respectively rotatable relative to the first and second pylon assemblies and have generally vertical orientations, in the VTOL flight mode, and generally horizontal orientations, in the forward flight mode and the storage mode. First and second proprotor assemblies are respectively rotatable relative to the first and second mast assemblies. Each proprotor assembly includes a plurality of rotor blades and has a radially extended orientation, in the flight modes, and a stowed orientation, in the storage mode.

公开(公告)号：US20180057162A1

公开(公告)日：2018-03-01

申请号：US15251128

申请日：2016-08-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga ,  Frank Bradley Stamps

IPC: B64C29/02 ,  B64C27/24 ,  B64C27/54 ,  B64C27/50 ,  B64C25/52

CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C25/52 ,  B64C27/24 ,  B64C27/50 ,  B64C27/54

Abstract: A tail sitter aircraft includes a fuselage having a forward portion and an aft portion. The forward portion of the fuselage includes first and second rotor stations. A first rotor assembly is positioned proximate the first rotor station. A second rotor assembly is positioned proximate the second rotor station. A tailboom assembly extends from the aft portion of the fuselage. The tailboom assembly includes a plurality of landing members. In a vertical takeoff and landing mode of the aircraft, the first and second rotor assemblies rotate about the fuselage to provide vertical thrust. In a forward flight mode of the aircraft, the first rotor assembly rotates about the fuselage to provide forward thrust and the second rotor assembly is non-rotatable about the fuselage forming wings to provide lift.

公开(公告)号：US20180057160A1

公开(公告)日：2018-03-01

申请号：US15253449

申请日：2016-08-31

Applicant: Bell Helicopter Textron Inc.

Inventor： Daniel Bryan Robertson ,  Kirk Landon Groninga

IPC: B64C29/00 ,  B64C39/00 ,  B64C29/02 ,  B64C39/12 ,  B64C23/02

CPC classification number: B64C29/0033 ,  B64C23/02 ,  B64C29/02 ,  B64C39/005 ,  B64C39/006 ,  B64C39/12

Abstract: A tri-wing aircraft includes a fuselage having a longitudinally extending fuselage axis. Three wings extend generally radially outwardly from the fuselage axis and are circumferentially distributed generally uniformly about the fuselage at approximately 120-degree intervals. The wings have airfoil cross-sections including first and second surfaces having chordwise channels therebetween. A distributed propulsion system includes a plurality of propulsion assemblies. Each propulsion assembly includes a variable thrust cross-flow fan disposed within one of the chordwise channels of one of the wings. At least two variable thrust cross-flow fans are disposed within the chordwise channels of each of the wings. A flight control system is operably associated with the distributed propulsion system such that the flight control system and the distributed propulsion system are operable to generate a triaxial dynamic thrust matrix.