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.

公开(公告)号：US20180372210A1

公开(公告)日：2018-12-27

申请号：US15633509

申请日：2017-06-26

Applicant: Bell Helicopter Textron Inc.

Inventor： Scott David Poster

IPC: F16H57/04 ,  F16K17/04 ,  F16K1/32 ,  F16K27/02 ,  F16K37/00 ,  F16H57/02 ,  B64C27/14

Abstract: A pressure sensitive bypass valve for protecting the components of a fluid distribution system. The bypass valve includes a poppet designed to prevent fluid bypass in the event of spring failure, rather than from over-pressurization.

公开(公告)号：US20180362177A1

公开(公告)日：2018-12-20

申请号：US15627412

申请日：2017-06-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Brent Scannell ,  Thomas Mast

IPC: B64D33/02 ,  B64C27/12 ,  B64C1/10 ,  B64C29/00

CPC classification number: B64D33/02 ,  B64C1/10 ,  B64C27/12 ,  B64C29/0033 ,  B64D2045/009

Abstract: In one embodiment, there is described an inlet plenum assembly for a rotary aircraft, including: an inlet plenum defined on a first side by an inlet plenum wall and on a second side by a forward firewall assembly; the inlet plenum wall having a mechanical interface for receiving a reduction gearbox (RGB) to provide reduction gearing to the drive shaft; and the forward firewall assembly having an inlet aperture configured to receive a drive shaft to rotatably couple to an engine; wherein the forward firewall assembly includes a forward firewall upper and a forward firewall lower, the forward firewall upper configured to removably seat to the forward firewall lower.

公开(公告)号：US20180362154A1

公开(公告)日：2018-12-20

申请号：US15627373

申请日：2017-06-19

Applicant: Bell Helicopter Textron Inc.

Inventor： Matthew E. Louis ,  Michael John Ryan ,  Daniel B. Robertson ,  Frank B. Stamps

IPC: B64C27/48 ,  B64C27/26 ,  B64C27/28 ,  B64C27/37

CPC classification number: B64C27/30 ,  B64C11/28 ,  B64C2201/108 ,  B64C2201/165

Abstract: In one embodiment, an apparatus comprises a shaft, a rotor, and a cam surface. The shaft comprises a spiral spline along a length of the shaft. The rotor comprises a blade extending from the rotor and a tubular hole extending into the rotor. The tubular hole comprises a spiral groove configured to mate with the spiral spline on the shaft. Relative rotation between the spiral spline and the spiral groove causes the rotor to linearly move along the shaft. The cam surface comprising a recession. The blade nesting in the recession to constrains rotation of the rotor about the shaft and allows linear movement of the rotor along the shaft.

公开(公告)号：US20180356179A1

公开(公告)日：2018-12-13

申请号：US15617889

申请日：2017-06-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Robert Wesley Matson ,  David Kimble Huber

IPC: F41B11/73 ,  F41B11/62

CPC classification number: F41B11/73 ,  F41B11/62

Abstract: An air cannon has a barrel and a sabot sized to fit within the barrel and configured to engage a projectile located within the barrel forward of the sabot. A flexible cord connects the sabot to a fixed location relative to the barrel. Forward motion of the sabot is decelerated by the cord after the sabot exits the forward end of the barrel, and the sabot is retained by the cord near the forward end of the barrel.

公开(公告)号：US20180354645A1

公开(公告)日：2018-12-13

申请号：US15617804

申请日：2017-06-08

Applicant: Bell Helicopter Textron Inc.

Inventor： Joe Leachman ,  Thomas B. Priest

IPC: B64D43/00 ,  G01C23/00

CPC classification number: B64D43/00 ,  G01C23/00 ,  G08G5/0021

Abstract: A combined controller with a panel that has a face and a back, a case attached to the back of the panel. The face of the panel includes a plurality of first primary flight display inputs configured to receive physical inputs for the control of a first primary flight display; a plurality of second primary flight display inputs configured to receive physical inputs for the control of a second primary flight display; and a plurality of flight control inputs configured to receive physical inputs for the control of automated flight behavior.

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

IPC: B64C29/00 ,  B64C27/54 ,  B64C11/46

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.

公开(公告)号：US20180339769A1

公开(公告)日：2018-11-29

申请号：US15606257

申请日：2017-05-26

Applicant: Bell Helicopter Textron Inc.

Inventor： John Richard McCullough ,  Paul K. Oldroyd

IPC: B64C27/54 ,  B64C29/00

CPC classification number: B64C27/605 ,  B64C27/54 ,  B64C29/0016 ,  B64C29/0033 ,  B64C2201/086 ,  B64C2201/108

Abstract: A rotor assembly for an aircraft operable to generate a variable thrust output at a constant rotational speed. The rotor assembly includes a mast rotatable at the constant speed about a mast axis. A rotor hub is coupled to and rotatable with the mast. The rotor hub includes a plurality of spindle grips extending generally radially outwardly. Each of the spindle grips is coupled to one of a plurality of rotor blades and is operable to rotate therewith about a pitch change axis. A collective pitch control mechanism is coupled to and rotatable with the rotor hub. The collective pitch control mechanism is operably associated with each spindle grip such that actuation of the collective pitch control mechanism rotates each spindle grip about the respective pitch change axis to collectively control the pitch of the rotor blades, thereby generating the variable thrust output.

公开(公告)号：US20180339761A1

公开(公告)日：2018-11-29

申请号：US15606213

申请日：2017-05-26

Applicant: Bell Helicopter Textron Inc.

Inventor： John Richard McCullough ,  Paul K. Oldroyd

IPC: B64C3/10 ,  B64C3/32 ,  B64C29/00

CPC classification number: B64C29/0033 ,  B64C3/10 ,  B64C3/32 ,  B64C5/10 ,  B64C11/46 ,  B64C2201/108

Abstract: An aircraft has a vertical takeoff and landing fight mode and a forward flight mode. The aircraft includes an airframe with first and second M-wings each having a pair of leading apexes with swept forward and swept back portions extending therefrom at a swept angle. A propulsion system includes a plurality of propulsion assemblies each attached to the airframe proximate one of the leading apexes. Each of the propulsion assemblies includes a rotor assembly having a tilting degree of freedom. A flight control system is operable to control the propulsion assemblies including tilting the rotor assemblies to generate variable thrust vectors that have a maximum angle that is generally congruent with the swept angles of the M-wings.

公开(公告)号：US20180299103A1

公开(公告)日：2018-10-18

申请号：US15951274

申请日：2018-04-12

Applicant: Bell Helicopter Textron Inc.

Inventor： Francis Turgeon

IPC: F21V14/02 ,  F21S8/00 ,  B64D47/02

Abstract: The present invention includes a first frame attached to an aerial vehicle or a mounting plate attached to the aerial vehicle, and a second frame attached to an aimable device moveably connected to the aerial vehicle or the mounting plate. The first frame and the second frame are configured to collectively provide a hard stop that prevents the aimable device from pointing at the aerial vehicle.