-
公开(公告)号：US11267564B2
公开(公告)日：2022-03-08
申请号：US16659829
申请日：2019-10-22
Applicant: Bell Textron Inc.
Inventor： Martin Landry , Mathieu Beland , Maxime Lapalme
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：US11267561B2
公开(公告)日：2022-03-08
申请号：US16664675
申请日：2019-10-25
Applicant: Bell Textron Inc.
Inventor： David Heverly , Frank Bradley Stamps , Jouyoung Jason Choi , Michael R. Smith , Thomas C. Parham
Abstract: A vibration attenuator for a rotor of an aircraft has a track housing adapted for rotation relative to the rotor and configured for rotation at a second angular velocity greater than a first angular velocity of the rotor. A track is located within the track housing and has a reaction surface, a pair of weights being configured for movement within the track and in contact with the reaction surface. A stop assembly has a pair of stops spaced 180 degrees apart, the stops separating the weights from each other, and each weight being allowed to travel within the track between the stops. A motor rotates the track housing relative to the rotor. The weights are free to travel relative to each other between a minimum-force configuration, in which the weights are positioned 180 degrees apart, and a maximum-force configuration, in which both weights are adjacent one of the stops.
-
公开(公告)号：US20220063797A1
公开(公告)日：2022-03-03
申请号：US17004919
申请日：2020-08-27
Applicant: Bell Textron Inc.
Inventor： Bryan Kenneth Baskin
Abstract: An elastomeric bearing assembly has a centrifugal force bearing axially captured relative to a sliding interface. The sliding interface has one or more low friction regions and one or more high friction regions. One or more piezo actuators are configured to force one or more corresponding high friction regions against the centrifugal force bearing when actuated. The sliding interface may have a circular shape, wherein the one or more low friction regions and the one or more high friction regions are alternating concentric segments of the sliding interface. The one or more high friction regions are recessed on the sliding interface relative to the one or more low friction regions.
-
公开(公告)号：US11248743B2
公开(公告)日：2022-02-15
申请号：US16155208
申请日：2018-10-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Joshua A. Emrich , Patrick Paquin , Eric C. Terry , Brent Scannell , Thomas Mast
Abstract: In some examples, a drain pan comprises a composite material forming a reservoir and a drain. The composite material comprises a polymeric resin and a reinforcing fiber. The reservoir is to catch a liquid from an engine and to support a step load. The drain is to drain the liquid from the reservoir. In some examples, a method comprises attaching a drain pan to an aircraft proximate an engine. The drain pan comprises a composite material forming a reservoir and a drain. The method further comprises catching a liquid from the engine in the reservoir of the drain pan and draining the liquid from the reservoir through the drain. In addition, the method comprises supporting a step load on the reservoir of the drain pan.
-
公开(公告)号：US11248552B2
公开(公告)日：2022-02-15
申请号：US16508673
申请日：2019-07-11
Applicant: Bell Textron Inc.
Inventor： William Gons , Brett Partington
Abstract: Embodiments are directed to boosting aircraft engine performance for takeoff and critical mission segments by reducing airflow used for cooling exhaust gases. The airflow is reduced by stopping an accessory blower or by closing an external air vent. Eliminating the cooling airflow to the exhaust has the effect of lowering the backpressure on the engine, which thereby increases maximum engine power.
-
Patent Agency Ranking
公开(公告)号：US11242798B2
公开(公告)日：2022-02-08
申请号：US16294266
申请日：2019-03-06
Applicant: Bell Textron Inc.
Inventor： David Haynes , Thomas Dewey Parsons , Shahryar Fotovati
Abstract: An aircraft includes a fuselage and an engine housed in the fuselage. A ram-air engine inlet is formed on an exterior of the fuselage. The ram-air engine inlet is defined, at least in part, by a cowling door. The cowling door is moveable between a closed position and an open position. An intake duct fluidly couples the ram-air engine inlet to the engine. A filter is disposed across the intake duct. A bypass duct is formed in the ram-air engine inlet aft of the intake duct. The bypass duct is operable to be selectively opened and closed.
-
公开(公告)号：US11235860B2
公开(公告)日：2022-02-01
申请号：US16388993
申请日：2019-04-19
Applicant: Bell Helicopter Textron Inc.
Inventor： Shyhpyng Jack Shue
IPC: B64D5/00 , G06Q10/08 , B64C13/22 , B64C29/00 , G05D1/00 , B64D45/00 , G05D1/08 , B64C13/04 , B64C13/20
Abstract: In some embodiments, a control manager is disposed between the rotor system and the flight control inceptor. The control manager is configured to receive control commands wirelessly from a ground control station, translate the control commands into one or more axes associated with the flight control inceptor, and transmit the translated control commands to the rotor system in place of the instructions received from the pilot via the flight control inceptor.
-
公开(公告)号：US11235856B2
公开(公告)日：2022-02-01
申请号：US16661740
申请日：2019-10-23
Applicant: Bell Textron Inc.
Inventor： Pascal Flynn-Robitaille
Abstract: An aircraft includes a wing and a rotor pod mounted to the wing. The rotor pod includes a body having a forward end and an aft end. A propeller is mounted to the body of the rotor pod at the forward end. A control surface is mounted to the body of the rotor pod between the forward and aft ends and extends outwardly from the body. The control surface is displaceable relative to the body between a first control configuration and a second control configuration to control an attitude of the aircraft. The control surface in the first control configuration is closer to the propeller than the control surface in the second control configuration.
-
公开(公告)号：US11214363B2
公开(公告)日：2022-01-04
申请号：US17068767
申请日：2020-10-12
Applicant: Bell Textron Inc.
Inventor： Timothy Kent Ledbetter , Thomas Parham , Dalton T. Hampton , Frank Stamps , Zachary Edwin Dailey , Robert L. Milliken
Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.
-
公开(公告)号：US11214360B2
公开(公告)日：2022-01-04
申请号：US16589201
申请日：2019-10-01
Applicant: Bell Textron Inc.
Inventor： Mark Loring Isaac , Kent Edwards Donaldson
Abstract: A landing gear assembly for an aircraft includes a landing member and an actuation mechanism coupled to the landing member. The actuation mechanism is configured to selectively actuate the landing member into a first landing position and a second landing position. The landing member is configured to support the aircraft in either the first landing position or the second landing position.
-
-
-
-
-
-
-
-
-
Search Results
3495
records
(took 0.081 seconds)
