公开(公告)号：US20210197962A1

公开(公告)日：2021-07-01

申请号：US16790304

申请日：2020-02-13

Applicant: Bell Textron Inc.

Inventor： Albert Gerard Brand ,  Ronald Lorenz Kisor

IPC: B64C27/00 ,  B64C27/57 ,  B64D43/02

Abstract: A system and method for protecting a rotorcraft from entering a vortex ring state, the method including monitoring a vertical speed of a rotorcraft, comparing the vertical speed to a vertical speed safety threshold, and performing vortex ring state (VRS) avoidance in response to the vertical speed exceeding the vertical speed safety threshold. The performing the VRS avoidance includes determining a power margin available from one or more engines of the rotorcraft, limiting the vertical speed of the rotorcraft in response to the power margin exceeding a threshold, and increasing a forward airspeed of the rotorcraft in response to the power margin not exceeding the threshold.

公开(公告)号：US20210197956A1

公开(公告)日：2021-07-01

申请号：US16732083

申请日：2019-12-31

Applicant: Bell Textron Inc.

Inventor： Karl Schroeder ,  Jonathan Knoll ,  George Matthew Thompson

IPC: B64C11/02 ,  B64C11/00 ,  B64C27/52 ,  B64C27/20 ,  B64C29/00 ,  B64C3/38

Abstract: A ducted-rotor aircraft includes a fuselage and first and second ducts that are coupled to the fuselage. Each duct includes a duct ring, a rotor having a plurality of blades, a hub that positions the rotor such that the blades define a blade plane of rotation within the duct ring, and a plurality of stators that are coupled to the hub at respective locations aft of the blade plane of rotation. Each of the plurality of stators defines a leading edge that is slanted toward the blade plane of rotation. The leading edges of the stators are slanted to follow a contour defined by the blades. The leading edges may also be slanted to maintain a distance of at least one blade inboard chord length between the leading edges of the stators and respective trailing edges of the blades.

公开(公告)号：US20210163128A1

公开(公告)日：2021-06-03

申请号：US16862276

申请日：2020-04-29

Applicant: Bell Textron Inc.

Inventor： Frank Bradley Stamps ,  Thomas C. Parham, Jr.

IPC: B64C29/00 ,  B64C27/605 ,  B64C27/57 ,  B64C27/64 ,  B64C27/68 ,  F01D5/10

Abstract: A system is provided for controlling the pitch of blades of a rotor, the system comprising an actuator for each blade, each actuator being configured for selective control of the pitch of an associated blade about a pitch axis. Sensors are configured for determining aerodynamic forces acting on the rotor, and a flight control system is configured to receive signals from the sensors and for operating the actuators in response to the signals to achieve a desired pitch-flap coupling value.

公开(公告)号：USD920216S1

公开(公告)日：2021-05-25

申请号：US29719446

申请日：2020-01-03

Applicant: Bell Textron Inc.

Designer： Joseph Richard Carpenter ,  Steve Michael Loveland ,  Allen Brittain

公开(公告)号：US20210147043A1

公开(公告)日：2021-05-20

申请号：US16683521

申请日：2019-11-14

Applicant: Bell Textron Inc.

Inventor： Jeffrey Paul NISSEN ,  Troy Cyril SCHANK ,  Peter Charles ROBICHAUX ,  Jason Paul HURST ,  Todd Christopher WORDEN

IPC: B63B35/50 ,  B63B35/00 ,  B64F1/28

Abstract: An exemplary autonomous seabased resupply system includes an unmanned blob positioned in a water body, the blob containing fuel, a pump on the blob configured to pump the fuel through a conduit to a craft, and a ballast system operable to change a vertical position of the blob in the water body.

公开(公告)号：US20210139161A1

公开(公告)日：2021-05-13

申请号：US17095634

申请日：2020-11-11

Applicant: Bell Textron Inc.

Inventor： Jeffrey Paul Nissen ,  Troy Cyril Schank ,  Brent Chadwick Ross ,  Steven Ray Ivans

IPC: B64D39/04 ,  B64D39/02 ,  B64D7/00

Abstract: An aerial resupply system (ARS) including a supply aircraft. The supply aircraft includes at least one of supply fuel, an ordinance, and data. The supply aircraft also includes a retractable boom system (RBS) configured for selective stowage within a fuselage of the supply aircraft and configured to supply at least one of supply fuel, the ordinance, and data to a location external to the fuselage.

公开(公告)号：US20210139157A1

公开(公告)日：2021-05-13

申请号：US16679000

申请日：2019-11-08

Applicant: Bell Textron Inc.

Inventor： George Matthew Thompson ,  Paul Sherrill ,  Jonathan Knoll

IPC: B64D35/04 ,  B64C11/00 ,  B64C11/46 ,  B64D27/24

Abstract: A rotor assembly including a rotor mast, a rotor hub coupled to the rotor mast, a plurality of rotor blades coupled to the rotor hub, a control tube extending through the rotor mast, a crosshead coupled to the control tube, and a mechanism configured to drive the rotor mast in rotation. Wherein the mechanism is longitudinally positioned between a top portion and a bottom portion of the control tube and translation of the control tube relative to the rotor mast causes rotation of the rotor blades about their pitch-change axes. While the crosshead is installed, the crosshead is prevented from angular rotation about the mast axis. A pin of a rotor blade assembly is captured between opposing tabs of the crosshead and movable relative to the opposing tabs in response to translation of the crosshead along the mast axis

公开(公告)号：US20210116016A1

公开(公告)日：2021-04-22

申请号：US16657331

申请日：2019-10-18

Applicant: Bell Textron Inc.

Inventor： Douglas Robert MUELLER

IPC: F16H57/04 ,  F16N29/02 ,  B64D35/00

Abstract: A lubrication system includes a primary lubrication system for a gearbox of the aircraft, the primary lubrication system comprising a first lubricant tank, and an emergency lubrication system for the gearbox. The emergency lubrication system includes a second lubricant tank coupled to a gearbox of an aircraft, a passive thermostat coupled between the second lubricant tank and the gearbox via a lubricant line, a conductor coupled between the passive thermostat and the gearbox and configured to conduct heat from the gearbox to the passive thermostat, and wherein the passive thermostat is configured to open in response to the conductor being exposed to a temperature that exceeds a threshold temperature.

公开(公告)号：US20210114720A1

公开(公告)日：2021-04-22

申请号：US16659829

申请日：2019-10-22

Applicant: Bell Textron Inc.

Inventor： Martin LANDRY ,  Mathieu BELAND ,  Maxime LAPALME

IPC: B64C27/28 ,  B64C27/52 ,  B64C29/00 ,  B64C27/20

Abstract: An aircraft includes a fuselage, and a wing extending from the fuselage along a spanwise axis. A section of the wing is rotatable about the spanwise axis. A ducted fan is mounted to the section of the wing. The ducted fan has a hub configured to be drivingly engaged by an engine. The hub is rotatable about a fan axis. Blades protrude from the hub between roots mounted to the hub and tips radially spaced from the hub. A duct circumferentially extends about the fan axis and is mounted to the tips of the blades to rotate with the blades about the fan axis. The section of the wing and the ducted fan are rotatable about the spanwise axis between a hover mode in which the fan axis is substantially perpendicular to a ground, and an aircraft mode in which the fan axis is substantially parallel to the ground.

公开(公告)号：US20210107638A1

公开(公告)日：2021-04-15

申请号：US16599471

申请日：2019-10-11

Applicant: Bell Textron Inc.

Inventor： Kyle Thomas CRAVENER ,  Andrew MARESH

IPC: B64C29/00 ,  B64C11/20

Abstract: An exemplary blade lock for a tiltrotor aircraft to enable and disable a folding degree of freedom and a pitching degree of freedom of a rotor blade assembly includes a link pivotally connected to a lever and a bellcrank, where the link is in a center position when the lever is in a locked position disabling the folding degree of freedom and the lever is secured in the locked position when the link is positioned in an over-center position.