公开(公告)号：US20210053676A1

公开(公告)日：2021-02-25

申请号：US16546082

申请日：2019-08-20

Applicant: Bell Textron Inc.

Inventor： Albert G. Brand ,  Scott David Poster

IPC: B64C39/02 ,  B64F3/02 ,  B64C29/00

Abstract: An electric power tethering system for an aircraft having a vertical takeoff and landing flight mode including a takeoff phase and/or a hover phase includes a surface power source and a power tether having a surface end configured to couple to the surface power source and an aircraft end configured to couple to the aircraft. The power tether is configured to transmit power from the surface power source to the aircraft in the takeoff phase and/or the hover phase. The power tether is detachable to decouple the surface power source from the aircraft in response to a power tether release event during flight.

公开(公告)号：US20210053674A1

公开(公告)日：2021-02-25

申请号：US16545422

申请日：2019-08-20

Applicant: Bell Textron Inc

Inventor： Timothy Brian Carr ,  William Anthony Amante ,  Brian John Cox

IPC: B64C25/52 ,  B64C27/04 ,  B29C70/52 ,  B29C70/54

Abstract: Various implementations directed to composite skid members are provided. In one implementation, an aircraft landing gear assembly may include two skid members configured to contact the ground, where each skid member includes composite material manufactured using a pultrusion process. The aircraft landing gear assembly may also include a plurality of cross members configured to couple to a fuselage of an aircraft and configured to interconnect the two skid members.

公开(公告)号：US20210050911A1

公开(公告)日：2021-02-18

申请号：US16541960

申请日：2019-08-15

Applicant: Bell Textron Inc.

Inventor： Mark David Stoufflet

IPC: H04B7/185 ,  B64C39/02 ,  H01Q1/28

Abstract: One embodiment is an apparatus comprising an aircraft and an aerial network communications system associated with the aircraft. The network communications system may comprise an antenna physically connected to an outside surface of the aircraft; and a transceiver electrically connected to the antenna. The aerial network communications system receives signals from and transmits signals to an unmanned aerial vehicle (“UAV”) via a communications network comprising a control station and a plurality of airborne network nodes.

公开(公告)号：US20210039774A1

公开(公告)日：2021-02-11

申请号：US16532347

申请日：2019-08-05

Applicant: Bell Textron Inc.

Inventor： Mark Loring Isaac ,  James Everett Kooiman ,  Charles David Hogue

IPC: B64C25/12 ,  B64C25/20 ,  B64C25/34

Abstract: A retractable landing gear system configured to contour an aircraft fuselage includes a landing wheel having an axle, a wheel rotation strut assembly coupling the landing wheel to the aircraft fuselage and an actuation strut assembly configured to move the wheel rotation strut assembly between various positions including a deployed position and a stowed position. The axle of the landing wheel is pivotably coupled to a distal end of the wheel rotation strut assembly and configured to pivot relative to the wheel rotation strut assembly as the actuation strut assembly moves the wheel rotation strut assembly between the deployed and stowed positions such that the landing wheel generally contours the aircraft fuselage when the wheel rotation strut assembly is in the stowed position.

公开(公告)号：US20210016889A1

公开(公告)日：2021-01-21

申请号：US16516788

申请日：2019-07-19

Applicant: Bell Textron Inc.

Inventor： Michael Remington Zarate

IPC: B64D37/06

Abstract: A fuel system for an aircraft. The fuel system includes a fuel tank configured to contain liquid fuel. A non-extendable fluid line is coupled between an airframe member of the aircraft and the fuel tank. A sleeve assembly is coupled between the fluid line and an upper surface of the fuel tank. The sleeve assembly includes a sealing sleeve and an extension sleeve. The sealing sleeve is positioned around the fluid line forming a fluid tight seal therewith and having a non-sliding relationship therewith. The extension sleeve is positioned around the fluid line with a first portion of the extension sleeve having a sliding relationship with the fluid line such that increasing the distance between the upper surface of the fuel tank and the airframe member causes the extension sleeve to increase in length as the fluid line slides relative to the first portion of the extension sleeve.

公开(公告)号：USD906851S1

公开(公告)日：2021-01-05

申请号：US29706742

申请日：2019-09-23

Applicant: Bell Textron Inc.

Designer： Min Young Yoo

公开(公告)号：US10829237B2

公开(公告)日：2020-11-10

申请号：US15906108

申请日：2018-02-27

Applicant: Bell Textron Inc.

Inventor： James Everett Kooiman ,  George Ryan Decker ,  Michael Rinehart ,  Jeffrey Matthew Williams

IPC: B01D46/00 ,  B64D33/02 ,  F02C7/052 ,  B64C29/00

Abstract: An inlet barrier filter system for a tiltrotor aircraft comprising a filter duct extending from a filter to a filter outlet, a ram air duct extending from a ram air inlet to an engine where the filter duct connects to the ram air duct at the filter outlet, and a closure member movable between a first position blocking the ram air duct and a second position blocking the filter outlet. In use, the inlet barrier filter system provides for two mutually exclusive air flow paths, one for introducing ram air to the engine while closing off the filter and another air flow path for introducing filtered air to the engine while closing off the ram air duct.

公开(公告)号：US20200346743A1

公开(公告)日：2020-11-05

申请号：US16400002

申请日：2019-04-30

Applicant: Bell Textron Inc.

Inventor： Guy Bernard

IPC: B64C25/62 ,  B64C29/00

Abstract: An energy absorbing landing system for an aircraft having a fuselage includes landing legs rotatably coupled to the fuselage configured to outwardly rotate when receiving a landing load having a magnitude. The energy absorbing landing system also includes an energy absorption unit coupled to the fuselage and cables coupling the energy absorption unit to the landing legs. The energy absorption unit is configured to selectively apply a resistance to the outward rotation of the landing legs via the cables based on the magnitude of the landing load, thereby absorbing the landing load when the aircraft lands.

公开(公告)号：US20200216170A1

公开(公告)日：2020-07-09

申请号：US16733806

申请日：2020-01-03

Applicant: Bell Textron Inc.

Inventor： Steven Loveland ,  Paul Charles Griffiths ,  Allen Brittain

IPC: B64C25/34 ,  B64C25/06 ,  B64C25/52

Abstract: An aircraft landing gear assembly has a longitudinally elongated frame coupled to a lower portion of a fuselage of an aircraft, the frame being capable of supporting at least a portion of the weight of the aircraft. A fairing encloses substantially all of the frame. An optional integrated step can be carried by the frame, and a longitudinally elongated aperture would be formed in the fairing adjacent the step. The step allows a user to place a foot into the aperture and onto the step. An optional door can cover the aperture, and an optional secondary step can be carried by the door.

公开(公告)号：US20200216164A1

公开(公告)日：2020-07-09

申请号：US16733798

申请日：2020-01-03

Applicant: Bell Textron Inc.

Inventor： James Gibson ,  Carey Cannon

IPC: B64C13/04

Abstract: A control device for an aircraft has a control stick configured to be operated by hand of a user. The control stick is pivotable about a longitudinal axis, a lateral axis, and a yawing axis extending through the control stick. Motion of the stick about the longitudinal axis is configured to cause roll motion of the aircraft, motion of the stick about the lateral axis is configured to cause pitch motion of the aircraft, and motion of the stick about the yawing axis is configured to cause yaw motion of the aircraft. Rotation of a thumbwheel carried by the control stick changes a magnitude of a thrust vector of the aircraft.