公开(公告)号：US10697795B2

公开(公告)日：2020-06-30

申请号：US15894871

申请日：2018-02-12

Applicant: Bell Textron Inc.

Inventor： Erik John Oltheten ,  Aaron Thomas Halverson

IPC: G01C23/00 ,  G01S19/40 ,  G01C21/08 ,  G01C21/16 ,  B64D43/00 ,  G01C25/00 ,  G01C19/42

Abstract: A navigation system for vehicles, such as rotorcraft, includes a directional gyroscope having a magnetic heading correction mode, a nonmagnetic manual heading correction mode and a nonmagnetic automatic heading correction mode. A magnetic field sensor is operably coupled to the directional gyroscope and is operable to generate magnetic north-based signals. A heading correction input is operably coupled to the directional gyroscope and is operable to generate manual signals upon actuation thereof. A global positioning system sensor is operably coupled to the directional gyroscope and is operable to generate track-based signals. In the magnetic heading correction mode, the directional gyroscope receives the magnetic north-based signals for heading corrections. In the nonmagnetic manual heading correction mode, the directional gyroscope receives the manual signals for heading corrections. In the nonmagnetic automatic heading correction mode, the directional gyroscope periodically receives the track-based signals for heading corrections.

公开(公告)号：US12246484B2

公开(公告)日：2025-03-11

申请号：US17680955

申请日：2022-02-25

Applicant: Bell Textron Inc.

Inventor： Maxime Lapalme ,  Nicola Pedneault Plourde ,  Jocelyn Lirette

IPC: B29C64/118 ,  B29L31/34 ,  B33Y10/00 ,  B33Y80/00 ,  H01B13/00

Abstract: A method of producing an article of manufacture includes printing a break-wire conductive-material pattern via an additive-manufacturing process and applying the break-wire conductive-material pattern to a surface of a component. A shape of the break-wire conductive-material pattern fits the surface of the component.

公开(公告)号：US12240346B2

公开(公告)日：2025-03-04

申请号：US17561900

申请日：2021-12-24

Applicant: Bell Textron Inc.

Inventor： Albert Mazzei ,  Michael R. Hull ,  Yue Fan

IPC: B60L53/30 ,  B60L53/66 ,  B64U50/19

Abstract: There is disclosed in one example, one or more tangible, non-transitory computer-readable storage media having stored thereon machine-executable instructions to: receive battery data from at least one sensor connected to a battery bank of an electric vertical takeoff and landing (eVTOL) aircraft, wherein the battery bank comprises a plurality of batteries; compute from the battery data an available flight time remaining for the eVTOL aircraft; compute a nominal flight time remaining, wherein the nominal flight time remaining excludes a reserve flight time; and display the nominal flight time remaining to a pilot in a human-readable format.

公开(公告)号：US12221206B2

公开(公告)日：2025-02-11

申请号：US18342123

申请日：2023-06-27

Applicant: Bell Textron Inc.

Inventor： Mark Loring Isaac

IPC: B64C25/34 ,  B64C25/50

Abstract: An aircraft landing gear shimmy damping device for aircraft landing gear with castering may include a centering cam engaged in a curvic slot in an internal diameter of an aircraft landing gear wheel spindle when the landing gear wheel is aligned with forward ground travel of the aircraft, engaging a landing gear wheel shimmy dampener. The centering cam may be pushed out of the curvic slot when the aircraft begins to turn, disengaging the landing gear wheel shimmy dampener, and may slide back into the curvic slot and (re)engage the shimmy dampener, when the landing gear wheel is realigned with forward ground travel of the aircraft.

公开(公告)号：US12179307B2

公开(公告)日：2024-12-31

申请号：US17063989

申请日：2020-10-06

Applicant: Bell Textron Inc.

Inventor： Michael Scott Lee Larson ,  Roland L. Walker, Jr. ,  Mark Philip Vance ,  James Joseph Meyer ,  Edward P. Michaels, Jr.

IPC: B24B1/04 ,  B24B31/00 ,  B24B31/02 ,  B24B31/06 ,  B24B31/108 ,  B24B35/00

Abstract: A masking tool system includes a first masking body and a second masking body. The first masking body includes a bore passing through a portion of the first masking body and a first sealing element disposed on a first end of the first masking body. The second masking body includes a bore passing through the second masking body and a second sealing element disposed on a first end of the second masking body. The system may also include a rod configured to pass through the bores of the first and second masking bodies and to secure the first and second masking bodies to a metallic article placed therebetween. A diagonal length of the masking tool system induces a wobbling rotation during processing.

公开(公告)号：US12162583B2

公开(公告)日：2024-12-10

申请号：US17094608

申请日：2020-11-10

Applicant: Bell Textron Inc.

Inventor： Michael Dean Dearman

IPC: B64C39/08 ,  B64C29/02 ,  B64U10/20 ,  B64U30/10 ,  B64U30/20 ,  B64U50/13 ,  B64U50/15 ,  B64U101/15

Abstract: An anti-aircraft system is described and includes an unmanned aerial vehicle (UAV) comprising a body; a wing connected to the body; and propulsion systems associated with the wing, wherein the propulsion systems comprise pylons releasably connected to opposite ends of the wing such that the propulsion systems may be selectively released from the wing during flight of the UAV.

公开(公告)号：US12090708B2

公开(公告)日：2024-09-17

申请号：US17552466

申请日：2021-12-16

Applicant: Bell Textron Inc.

Inventor： Philip C. Sears ,  Samuel L. Bryk ,  Bradyn C. Crider

IPC: B29C65/00 ,  B29C65/48 ,  B29C65/50 ,  B29C65/34 ,  B29L31/30

CPC classification number: B29C65/4815 ,  B29C65/4835 ,  B29C65/5057 ,  B29C66/1122 ,  B29C66/71 ,  B29C65/34 ,  B29C65/3456 ,  B29C65/3468 ,  B29L2031/3088

Abstract: Systems and methods are described for applying a self-heating structural adhesive to components of aircraft or other structures. A conductive scrim can be placed in between layers of adhesive for use in joining two components together. Leads can be provided to apply an electrical current to the scrim, which can raise the temperature of the system and cure the adhesives, creating a strong bond with a conductive layer there between.

公开(公告)号：US12084196B2

公开(公告)日：2024-09-10

申请号：US17404251

申请日：2021-08-17

Applicant: Bell Textron Inc.

Inventor： Yue Fan ,  Michael R. Hull

IPC: B64D45/00 ,  G01R31/382 ,  G05D1/00 ,  B60L58/12 ,  B60L58/16 ,  B64C29/02

CPC classification number: B64D45/00 ,  G01R31/382 ,  G05D1/102 ,  B60L58/12 ,  B60L58/16 ,  B60L2200/10 ,  B64C29/02 ,  B64D2045/0085

Abstract: In an example, a computing apparatus includes a hardware platform, having a processor and a memory, and instructions encoded within the memory to instruct the processor to receive a peak power demand for a landing maneuver of a VTOL aircraft powered at least partly by a battery, receive flight profile data for a flight profile of the VTOL aircraft, and configuration data for the VTOL aircraft, estimate power consumption of the flight profile in context of the configuration, and estimate a peak power capacity available for the landing maneuver, and provide an error notice if the peak power capacity does not meet the peak power demand.

公开(公告)号：US11975851B2

公开(公告)日：2024-05-07

申请号：US17225018

申请日：2021-04-07

Applicant: Bell Textron Inc.

Inventor： Troy C. Schank

IPC: B64D27/10 ,  B64C27/28 ,  B64C29/00 ,  B64D27/24 ,  B64D37/30 ,  B64D41/00 ,  F02C6/14 ,  B64D27/02

CPC classification number: B64D27/10 ,  B64C27/28 ,  B64C29/0016 ,  B64C29/0083 ,  B64D27/24 ,  B64D37/30 ,  B64D41/00 ,  F02C6/14 ,  B64D27/026

Abstract: A hybrid power system for a vertical takeoff and landing (“VTOL”) aircraft including a first power source operable to provide a power output for at least a forward flight mode; and a second power source configured to provide a high specific power output for an altitude adjustment flight mode, the second power source including an auxiliary gas generator coupled to a turbine and a drive system. In other aspects, there is provided a VTOL aircraft and methods for providing power to a VTOL aircraft.

公开(公告)号：US11891167B2

公开(公告)日：2024-02-06

申请号：US17503736

申请日：2021-10-18

Applicant: Bell Textron Inc.

Inventor： Bryan Kenneth Baskin ,  Kyle Thomas Cravener ,  Andrew Ryan Maresh

IPC: B64C27/32 ,  B64C29/00

CPC classification number: B64C27/322 ,  B64C29/0033

Abstract: A teeter flap lock for an aircraft may include at least one pair of diametrically positioned teeter flap lock plates extending from a rotor teetering hinge, spaced apart from a rotor mast of the aircraft. A teeter flap lock block is positioned about the rotor mast and is configured to fit between the teeter flap lock plates and the rotor mast. The teeter flap lock block fits between and contacts the teeter flap lock plates in an engaged position, and is movable between the engaged position and a disengaged position relative to the teeter flap lock plates. The teeter flap lock enables flapping of rotors coupled to the rotor mast via the teetering hinge when the teeter flap lock block is in the disengaged position and disables flapping of the rotors when the teeter flap lock block is in the engaged position.