公开(公告)号：US10823289B2

公开(公告)日：2020-11-03

申请号：US15816516

申请日：2017-11-17

Applicant: Bell Helicopter Textron Inc.

Inventor： Keith David Weaver ,  David Angell ,  Nicholas Plagianos ,  Thomas Mast

IPC: B64D33/04 ,  F16J15/08 ,  F01N13/18 ,  B64C27/06

Abstract: A duct interface system and method includes a duct having a first end and a second end; a first receptacle for the first end of the duct and/or a second receptacle for the second end of the duct; and one or more first seals between the first end of the duct and the first receptacle and/or one or more second seals between the second end of the duct and the second receptacle.

公开(公告)号：US10822954B2

公开(公告)日：2020-11-03

申请号：US16170414

申请日：2018-10-25

Applicant: Bell Helicopter Textron Inc.

Inventor： Paul K. Oldroyd ,  Drew Sutton ,  Andrew Maresh ,  Christopher Foskey

IPC: B64C27/473 ,  F01D5/14

Abstract: A rotorcraft rotor blade assembly includes a stub spar extending less than a full span of the rotor blade assembly. An upper skin portion extends substantially the full span of the rotor blade assembly. A lower skin portion extends substantially the full span of the rotor blade assembly. The stub spar is positioned between the upper skin portion and the lower skin portion.

公开(公告)号：US10822108B2

公开(公告)日：2020-11-03

申请号：US15913789

申请日：2018-03-06

Applicant: Bell Helicopter Textron Inc.

Inventor： Jeremy Robert Chavez ,  James R. Williamson ,  Levi Bilbrey

IPC: B64D43/00 ,  A42B3/30 ,  G06F3/01 ,  G01C23/00 ,  G08G5/00 ,  B64C13/18 ,  B64C13/22 ,  A42B3/04 ,  A42B3/22 ,  G06T19/00 ,  G02B27/01 ,  B64D11/06 ,  B64C13/04 ,  B64C1/06 ,  B64C1/18 ,  B64C1/40 ,  B64C13/10 ,  B64D11/00 ,  G06F3/044

Abstract: The present disclosure achieves technical advantages as an aircraft having an augmented reality flight control system integrated with and operable from the pilot seat and an associated pilot headgear unit, wherein the flight control system is supplemented by flight-assisting artificial intelligence and geo-location systems. The present disclosure includes an augmented reality flight control system incorporating real-world objects with virtual elements to provide relevant data to a pilot during aircraft flight. A translucent substrate is disposed in the pilot's field of view such that the pilot can see therethrough, and observe virtual elements displayed on the substrate. The system includes a headgear that is worn by the pilot. A flight assistance module is configured to receive data related to the aircraft and provide predictive assistance to the pilot during flight based on the received data based in part on a pilot profile having preferences related to the pilot.

公开(公告)号：US10807694B2

公开(公告)日：2020-10-20

申请号：US16001477

申请日：2018-06-06

Applicant: Bell Helicopter Textron Inc.

Inventor： Joshua Allan Edler ,  Tomy Turcotte ,  Jean Pierre Paradis ,  Steve Pothier

IPC: B64C1/14 ,  B64C1/00

Abstract: In some examples, a track comprises a plurality of members coupled to one another. The plurality of members comprises a first member, a second member, and a third member. The first member is operable to couple the track to an aircraft. The second member forms a first rail. The third member forms a second rail. In addition, the third member comprises at least a portion of an outer mold line of the aircraft. Moreover, the third member is operable to support a step load. The first rail and the second rail are operable to guide movement of an aircraft component along the track.

公开(公告)号：US20200324884A1

公开(公告)日：2020-10-15

申请号：US16382052

申请日：2019-04-11

Applicant: Bell Helicopter Textron Inc.

Inventor： Matthew Michael Wilcox ,  Aaron Alexander Acee

IPC: B64C27/12 ,  B64D35/02 ,  B64D35/04 ,  B60L7/18 ,  F16D3/06

Abstract: An exemplary rotorcraft includes a propulsion system including a prime mover and a drive shaft coupled to the prime mover, the drive shaft including a coupling separating the drive shaft into an input shaft and an output shaft, the coupling operable between an engaged position rotationally coupling the input shaft and the output shaft and a disengaged position rotationally disengaging the output shaft from the input shaft, a main rotor coupled to the prime mover, a secondary rotor attached to the output shaft, and a motor coupled to the output shaft.

公开(公告)号：US10801624B2

公开(公告)日：2020-10-13

申请号：US15703381

申请日：2017-09-13

Applicant: Bell Helicopter Textron Inc.

Inventor： Scott David Poster

IPC: F16J15/00 ,  F16J15/453 ,  F16C33/80 ,  F16J15/3224 ,  B64C27/12 ,  F16J15/3232 ,  F16J15/3248 ,  F16J15/3284 ,  F16J15/54 ,  B64D35/00

Abstract: The present invention includes a helicopter rotor seal assembly comprising: a rotor mast having a longitudinal axis and an outer surface; a sleeve aligned longitudinally with the axis and surrounding a portion of the rotor mast, the sleeve having an outer surface, and an inner surface; an annular horizontal seal between the inner surface of the sleeve and the outer surface of the rotor mast; and an upper annular rotor mast seal affixed to the outer surface of the rotor mast and extending outwardly sufficient to cover the annular horizontal seal.

公开(公告)号：US10800526B2

公开(公告)日：2020-10-13

申请号：US15591705

申请日：2017-05-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Alan Carl Ewing ,  Antonio Cardenas Munguia

IPC: B64D7/00 ,  B64D7/06 ,  B64D37/04 ,  B64D37/12

Abstract: An adapter is disclosed for use with an aircraft including wingtip stations defining mounting surfaces. The adapter is configured and dimensioned for connection to the wingtip stations on either wing of the aircraft to facilitate the connection of a weapons rack to the aircraft. The adapter includes a backing plate, and a body connected to the backing plate that is configured and dimensioned to support the weapons rack. The backing plate is configured and dimensioned in correspondence with the mounting surfaces defined by the wingtip stations. The body includes a base extending outwardly from the backing plate along a first axis, and a support member extending outwardly from the base along a second axis. In one particular embodiment of the adapter, the first and second axes define an angle of 45° therebetween.

公开(公告)号：US10793285B2

公开(公告)日：2020-10-06

申请号：US15895619

申请日：2018-02-13

Applicant: Bell Helicopter Textron Inc.

Inventor： James Everett Kooiman ,  Greg Alan Whittaker ,  Bryan Keith Sugg

IPC: B64D37/04 ,  B64C1/06 ,  B64C39/02

Abstract: One embodiment is a system comprising fuel tank comprising a pressure vessel for storing fuel for a vehicle, the fuel tank disposed within a fuselage of the vehicle and extending a majority of a length of the fuselage, wherein a center of gravity of the fuel tank is substantially aligned with a center of gravity of the fuselage. The fuel tank may be disposed within the fuselage such that the fuel tank bears at least a portion of a load borne by the fuselage. Alternatively, the fuel tank may be disposed within the fuselage such that the fuel tank is isolated from loads borne by the fuselage. In certain embodiments, the fuel tank comprises a filament wound pressure vessel.

公开(公告)号：US10781863B2

公开(公告)日：2020-09-22

申请号：US15972170

申请日：2018-05-06

Applicant: Bell Helicopter Textron Inc.

Inventor： Colton Gilliland ,  Mark Alan Przybyla

IPC: F16D11/10 ,  B64D35/04 ,  B64C3/56 ,  B64C29/00 ,  F16D11/00 ,  F16D1/10

Abstract: A locking mechanism for locking a driveshaft in cooperative engagement with an apparatus includes a drive portion coupled to the driveshaft and a driven portion coupled to the apparatus. The drive portion of the locking mechanism includes a housing with a first engagement portion, a ball cage with a plurality locking balls contained at least partially therein, and a chock biased away from the housing by a chock spring. The chock includes an outer wall configured to push the locking balls outward in a locked position and allow inward movement in an unlocked position. Movement of the chock, and therefore locking, is controlled by an actuator rod extending through a center of the locking mechanism. The driven portion includes a second engagement portion configured to cooperatively engage and receive torque from the first engagement portion, and a locking groove configured to receive a portion of each of the plurality of locking balls therein.

公开(公告)号：US10766631B2

公开(公告)日：2020-09-08

申请号：US15167886

申请日：2016-05-27

Applicant: Bell Helicopter Textron Inc.

Inventor： Joshua Robert O'Neil ,  Martin Peryea ,  Andrew Jordan Birkenheuer

IPC: B64F5/00 ,  B64D43/00 ,  B64F5/60 ,  B64D45/00 ,  B64D33/02

Abstract: A method of conducting an engine power assurance check includes performing a first engine power assurance check wherein the first engine power assurance check is judged as passing or failing based on power performance values calculated assuming the presence of a substantially clogged or blocked inlet barrier filter and in response to a fail result of the first engine power assurance check, performing a second engine power assurance check wherein the second power assurance check is judged as passing or failing based on power performance values calculated assuming at least one of no inlet barrier filter being installed and an open bypass of an installed inlet barrier filter.