公开(公告)号：US20210094679A1

公开(公告)日：2021-04-01

申请号：US16588843

申请日：2019-09-30

Applicant: Bell Textron Inc.

Inventor： Colton Gilliland ,  Tyson Henry ,  Russell Mueller

IPC: B64C27/32 ,  F01D25/16 ,  F16H1/28

Abstract: Embodiments are directed to a rotor mast for an aircraft comprising a shaft portion, a carrier portion having a plate and a web, and frame segments that separate the web from the plate at a fixed distance. The shaft portion, the plate, the web, and the frame segments are as single component. A plurality of first holes are formed in the plate, and a plurality of second holes are formed in the web. Pairs of the first and second holes are aligned. Posts are mounted between each pair of first and second holes. Pinion gears are mounted on the posts. Roller bearings are mounted between the posts and pinion gears. An open region of the web is configured to allow a sun gear to mesh with the pinion gears.

公开(公告)号：US20210094677A1

公开(公告)日：2021-04-01

申请号：US16587967

申请日：2019-09-30

Applicant: Bell Textron Inc.

Inventor： Tyler Wayne Baldwin ,  Jared Mark Paulson ,  Colin John Thomas ,  Paul Branson Sherrill ,  Bryan Huber

IPC: B64C27/00 ,  F01D5/02 ,  B64C27/473

Abstract: A balance weight assembly for a rotor blade of a rotorcraft. The balance weight assembly includes a balance weight pocket formed by a balance weight tray and a cover. The balance weight tray has an upper surface including a lip region extending outwardly from a projected region with an outboard boss. A balance weight receiving cavity is recessed from the upper surface and contains a plurality of balance weights. The projected region is disposed within an opening in a hollow blade spar such that the outboard boss of the balance weight tray has a contact relationship with an outboard surface of the opening. The cover is coupled to the balance weight tray such that the lip region of the balance weight tray and at least a portion of the cover have a clamping relationship with the blade spar, thereby coupling the balance weight pocket to the blade spar.

公开(公告)号：US20210089057A1

公开(公告)日：2021-03-25

申请号：US17111261

申请日：2020-12-03

Applicant: Bell Textron Inc.

Inventor： Michael Kevin MCNAIR ,  Andrew Vincent LOUIS

IPC: G05D1/10 ,  G05D1/06 ,  B64D45/04

Abstract: In one embodiment, a method is performed by a computer system in an aircraft. The method includes receiving an advance indication of a take-off or landing event to be executed by the aircraft in proximity to a landing area such that the landing area includes an arrangement of a plurality of emitters of electromagnetic radiation. The method further includes, responsive to the receiving, detecting, via a sensor in communication with the computer system, emission states of at least some of the plurality of emitters. In addition, the method includes transforming the detected emission states into an instruction set for the take-off or landing event. The method also includes initiating monitoring of the aircraft relative to the instruction set as the aircraft executes the take-off or landing event in proximity to the landing area.

公开(公告)号：US20210070461A1

公开(公告)日：2021-03-11

申请号：US16563908

申请日：2019-09-08

Applicant: Bell Textron Inc.

Inventor： Steven Ray Ivans ,  David Alan Hawthorne ,  Brad Robert Henson ,  David Frank Haynes ,  David Lawrence Miller

IPC: B64D33/02 ,  B64D27/14

Abstract: A rotorcraft has a fuselage, an engine disposed substantially laterally centrally relative to the fuselage, and an air intake system (AIS). The AIS has a first duct configured to provide streamline air flow, a second duct configured to provide streamline air flow, and a combining section configured to receive streamline air flow from each of the first duct and the second duct. The combining section is further configured to output streamline air flow.

公开(公告)号：US20210064061A1

公开(公告)日：2021-03-04

申请号：US16555655

申请日：2019-08-29

Applicant: Bell Textron Inc.

Inventor： Derek William HEARD ,  Richard Theodore PERRYMAN ,  Nathan Craig CLARK ,  Joshua Andrew EMRICH ,  Yann LAVALLEE ,  Ralph Michael GANNARELLI

IPC: G05D1/08 ,  B64C17/08

Abstract: A method of adjusting a center of gravity (CG) of an aircraft includes: inputting at least one load parameter into a flight computer, determining, via a processer of the flight computer, the CG of the aircraft. Responsive to a determination by the processor that the CG is outside of a CG envelope, moving at least a first movable ballast of a plurality of movable ballasts from a first ballast dock to a second ballast dock to move the CG toward the CG envelope. Each of the first and second ballast docks may include a housing and a first ballast tray secured within the housing and comprising a plurality of channels.

公开(公告)号：US20210061490A1

公开(公告)日：2021-03-04

申请号：US16557842

申请日：2019-08-30

Applicant: Bell Textron Inc.

Inventor： William Kyle Heironimus

IPC: B64F5/40

Abstract: Various implementations directed to a ground support equipment unit for use with electric aircraft are provided. In one implementation, a ground support equipment (GSE) unit may include a GSE thermal loop coupled to one or more channels of a battery pack onboard an aircraft, where the GSE thermal loop is configured to allow fluid from the one or more channels to circulate therein. The GSE unit may also include a GSE thermal system coupled to the GSE thermal loop, where the GSE thermal system is configured to regulate a battery temperature of the battery pack.

公开(公告)号：US20210061448A1

公开(公告)日：2021-03-04

申请号：US16899295

申请日：2020-06-11

Applicant: Bell Textron Inc.

Inventor： Derek William HEARD ,  Richard Theodore PERRYMAN ,  Nathan Craig CLARK ,  Joshua Andrew EMRICH ,  Yann LAVALLEE ,  Ralph Michael GANNARELLI

IPC: B64C17/08

Abstract: A movable ballast system for an aircraft includes first and second ballast docks secured to the aircraft. The first ballast dock includes a first housing and a first ballast tray and a first stop plate secured within the first housing. The first ballast tray includes a plurality of channels. The second ballast dock is positioned aft of a CG of the aircraft and includes a second housing and a second ballast tray and a second stop plate secured within the second housing. The second ballast tray includes a plurality of channels. The movable ballast system includes a plurality of movable ballasts, each movable ballast of the plurality of movable ballasts being configured to fit within at least one channel of each of the plurality of channels of the first and second ballast trays.

公开(公告)号：US20210061440A1

公开(公告)日：2021-03-04

申请号：US16558071

申请日：2019-08-31

Applicant: Bell Textron Inc.

Inventor： George Ryan Decker ,  Andrew G. Baines ,  Frank Douglas Sauer

IPC: B64C5/10 ,  B64C1/26 ,  B64C5/02

Abstract: A compliant tail structure for a rotorcraft having rotating components and a fuselage. The tail structure includes a tail assembly having first and second oppositely disposed tail members. A tail joint connects the tail assembly to an aft portion of the fuselage. The tail joint includes at least four tail mounts configured to establish a nodding axis for the tail assembly. At least two of the tail mounts are resilient tail mounts that are configured to establish a nodding degree of freedom for the tail assembly relative to the fuselage about the nodding axis, thereby detuning dynamic fuselage responses from excitation frequencies generated by the rotating components.

公开(公告)号：US20210060872A1

公开(公告)日：2021-03-04

申请号：US16554598

申请日：2019-08-28

Applicant: Bell Textron Inc.

Inventor： Sylvain TESSIER

IPC: B29C70/34 ,  B29C70/54

Abstract: A method of forming a composite member, includes: applying pressure and heat with a compaction tool to a portion of an uncured composite member to decrease a thickness of the portion, the heat applied with the compaction tool being at a temperature less than a curing temperature of the uncured composite member; and curing the uncured composite member after applying pressure and heat.

公开(公告)号：US20210047029A1

公开(公告)日：2021-02-18

申请号：US16541561

申请日：2019-08-15

Applicant: Bell Textron Inc.

Inventor： Keith Alan Stanney ,  Steven Ray Ivans ,  Brent Chadwick Ross ,  Troy Bushmire

IPC: B64C27/28 ,  B64C29/02

Abstract: Embodiments are directed to a rotorcraft comprising a body having a longitudinal axis, a wing coupled to the body, a single tiltrotor assembly pivotally coupled to the body, and the tiltrotor assembly configured to move between a position generally perpendicular to the longitudinal axis during a vertical flight mode and a position generally parallel to the longitudinal axis during a horizontal flight mode. The rotorcraft may further comprise an anti-torque system configured to counteract torque generated by the tiltrotor assembly during vertical flight. The rotorcraft may further comprise a center of gravity compensation system configured to manage a rotorcraft center of gravity during movement of the tiltrotor assembly between the vertical flight mode and the horizontal flight mode.