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公开(公告)号：US11183077B2
公开(公告)日：2021-11-23
申请号：US15936894
申请日：2018-03-27
Applicant: Bell Helicopter Textron Inc.
Inventor： Jeffrey Paul Nissen , Daniel Brent McCall , Joshua Peter Riccobono
Abstract: Systems and methods include providing a virtual reality (“VR”) flight teleport system that includes a master aircraft and a plurality of remote slave aircraft connected through a network. A flight emulator in the master aircraft allows a user in the master aircraft to “teleport” into a remote slave vehicle in order to observe and/or assume control of the remote slave aircraft. Motion of, orientation of, and/or forces acting on the remote stave vehicle are emulated to the user of the master vehicle through a pilot control interface, a motion-control seat, and a head-mounted display to provide real-time feedback to the user of the master aircraft. Inputs made via the pilot control interface of the flight emulator system in the master aircraft are transferred through the network into the flight control system of the remote slave vehicle to control operation of the remote slave vehicle.
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公开(公告)号：US11181209B2
公开(公告)日：2021-11-23
申请号：US16004376
申请日：2018-06-09
Applicant: Bell Helicopter Textron Inc.
Inventor： Brandon Anthony Magalhaes , Todd Kenneth Wise
Abstract: A fluid swivel includes at least two separate fluid paths extending therethrough, configured to convey fluid across a hinge. The fluid swivel includes a first end configured to be coupled to a first pair of lines on a first side of the hinge, a second end configured to be coupled to a second pair of lines on a second side of the hinge, a joint between the first end and the second end, a first pair of tubes extending from the first end to the joint, and a second pair of tubes extending from the joint to the second end, wherein the first and second tubes lie in a plane that is generally perpendicular to an axis of rotation of the joint.
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公开(公告)号：US20210354814A1
公开(公告)日：2021-11-18
申请号：US17229831
申请日：2021-04-13
Applicant: Bell Helicopter Textron Inc.
Inventor： George Matthew Thompson , Jonathan Andrew Knoll , Robert Glenn Vaughn , William Anthony Amante
IPC: B64C27/473
Abstract: A rotor system is provided in one example embodiment and may include a rotor duct; at least one rotor blade, wherein the at least one rotor blade comprises a tip end; and a multi-material tip extension affixed at the tip end of the at least one rotor blade, wherein the multi-material tip extension comprises an inboard portion fabricated from a first material and an outboard portion fabricated from a second material, wherein the second material is different than the first material.
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公开(公告)号：US11142447B2
公开(公告)日：2021-10-12
申请号：US16214784
申请日：2018-12-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Joseph Dean Rainville
Abstract: A system and a method for mobilized autonomous hydrogen refueling of vertical lift aircraft using a framed landing pad with sensors, an onboard hydrogen storage tank, an onboard refueling arm configured to couple the hydrogen storage tank to the aircraft and an onboard controller configured to control a flow of fuel from the hydrogen storage tank to the aircraft.
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公开(公告)号：US11136135B2
公开(公告)日：2021-10-05
申请号：US15477889
申请日：2017-04-03
Applicant: Bell Helicopter Textron Inc.
Inventor： Daniel Robert Lewis , Alan Soo Love
Abstract: A regime recognition system for an aircraft has a regime engine configured to identify a sub-regime performance of the aircraft only after having identified a top tier or top level regime performance that can include the sub-regime performance.
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Patent Agency Ranking
公开(公告)号：US11136115B2
公开(公告)日：2021-10-05
申请号：US16013201
申请日：2018-06-20
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos Alexander Fenny , Jouyoung Jason Choi
Abstract: An aircraft comprises a fuselage, one or more support structures connected to the fuselage, one or more engines or motors disposed within or attached to the one or more support structures or the fuselage, and a distributed propulsion system. The distributed propulsion system comprising two or more propellers symmetrically distributed in an array along the one or more support structures with respect to a center of gravity of the aircraft and operably connected to the one or more engines or motors, wherein each propeller has a rotation direction within a tilted plane of rotation, and a summation of horizontal force vectors created by the tilted plane of rotation of all the propellers is substantially zero when all the propellers are creating a substantially equal thrust magnitude. Movement of the aircraft is controlled by selectively increasing or decreasing a thrust of at least one of the two or more propellers.
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公开(公告)号：US11097836B2
公开(公告)日：2021-08-24
申请号：US16360803
申请日：2019-03-21
Applicant: Bell Helicopter Textron Inc.
Inventor： Michael Reaugh Smith , Jouyoung Jason Choi , Joseph Richard Carpenter , Steve Michael Loveland
IPC: B64C27/00
Abstract: In some examples, an aircraft comprises an airframe, a rotor system coupled to the airframe, and a vibration attenuation system. The rotor system is operable to exert a vibratory force on the airframe. The vibration attenuation system comprises two or more batteries and elastic devices. The two or more batteries are operable to supply power to the rotor system. The elastic devices coupled to the two or more batteries and the airframe. The elastic devices are configured to attenuate the vibratory force based on facilitating oscillation of the two or more batteries. In other examples, a method comprises coupling elastic devices to two or more batteries and an airframe of an aircraft. The elastic devices receiving a vibratory force via the airframe and attenuate the vibratory force based on facilitating oscillation of the two or more batteries.
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公开(公告)号：US11091278B2
公开(公告)日：2021-08-17
申请号：US15949633
申请日：2018-04-10
Applicant: Bell Helicopter Textron Inc.
Inventor： Sebastien Duval , Marc Ouellet
Abstract: A hook system has a mount that includes a first sidewall comprising a concave profile on a longitudinal end of the first sidewall, a second sidewall laterally offset in a fixed location relative to the first sidewall and defining a channel therebetween, the second sidewall having a second concave profile on a longitudinal end of the second sidewall. The hook system also has a first pin structure extending between the first sidewall and the second sidewall and a connector. The connector has a third concave profile, the third concave profile being configured to receive the first pin structure therein. The hook system also includes a second pin structure extending through the connector, wherein each of the first concave profile and the second concave profile are configured to receive the second pin structure therein. The connector is configured to be at least partially received within the channel.
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公开(公告)号：US11059561B2
公开(公告)日：2021-07-13
申请号：US15870977
申请日：2018-01-14
Applicant: Bell Helicopter Textron Inc.
Inventor： James Everett Kooiman , David G. Carlson , George Ryan Decker , Jeffrey Matthew Williams , Douglas K. Wolfe
Abstract: A torque box rib includes an upper rib cap configured to be coupled to an upper skin of a wing, a lower rib cap configured to be coupled to a lower skin of the wing, a forward post configured to be coupled to a forward spar of the wing, an aft post configured to be coupled to an aft spar of the wing, and a rib web configured to be coupled to the upper rib cap, the lower rib cap, the forward post, and the aft post.
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公开(公告)号：US11028944B2
公开(公告)日：2021-06-08
申请号：US15994518
申请日：2018-05-31
Applicant: Bell Helicopter Textron Inc.
Inventor： Brent Scannell , Thomas Mast , Jon Damon Bennett , Joshua Allan Edler , Jean Pierre Paradis , Keith C. Pedersen
Abstract: One example of a duct support for a rotorcraft includes a stabilizing mechanism configured to transfer a weight of a duct to an airframe of the rotorcraft, where the duct undergoes thermal expansion. The stabilizing mechanism includes a first stabilizing member attached to the duct, a second stabilizing member attached to the rotorcraft, and a coupling mechanism where the coupling mechanism is configured to couple the first stabilizing member to the second stabilizing member and accommodate thermal expansion of the duct by allowing for movement of the first stabilizing member relative to the second stabilizing member. In an example, the duct is an exhaust duct of an engine of the rotorcraft and heat from the engine cause the exhaust duct to undergo the thermal expansion.
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