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公开(公告)号：US20240083581A1
公开(公告)日：2024-03-14
申请号：US17942670
申请日：2022-09-12
Applicant: Textron Innovations Inc.
Inventor： Albert G. Brand , Robert P. Wardlaw
CPC classification number: B64D1/22 , G05D1/106 , B64C29/0008
Abstract: Load management system and methods are described for aircraft, including tailsitters. A load management system can comprise a pole coupled the fuselage and free to rotate and swing. The pole can comprise a cargo hook and a distal end that can be releasably coupled to a cargo cable or cargo. The pole can be coupled near its distal end to a retractable cable that is deployed from a position aft of the pole. During landing, takeoff, and when otherwise in hover mode, the retractable cable can be retracted—holding the pole along or near the fuselage. During transition to, or during, flight mode, the retractable cable can be deployed which can harmonize the cargo's center of gravity with the needs of the tailsitter aircraft.
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公开(公告)号：US10752352B2
公开(公告)日：2020-08-25
申请号：US15834340
申请日：2017-12-07
Applicant: Textron Innovations Inc.
Inventor： Albert G. Brand , Mark Loring Isaac , Frank Bradley Stamps , Russell Lee Mueller
Abstract: A dual rotor propulsion system for a tiltrotor aircraft having VTOL and forward flight modes. The dual rotor propulsion system includes an engine operable to provide an input torque to a transmission that, responsive thereto, generates an output torque. A first output shaft is coupled to the transmission and is operable to receive a first portion of the output torque. A first rotor assembly is coupled to and rotatable with the first output shaft. A second output shaft is coupled to the transmission and is operable to receive a second portion of the output torque. A second rotor assembly is coupled to and rotatable with the second output shaft. In operation, the first and second rotor assemblies rotate coaxially, the first rotor assembly is a different diameter than the second rotor assembly and the first rotor assembly is stoppable and foldable in the forward flight mode.
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Patent Agency Ranking
公开(公告)号：US20220227488A1
公开(公告)日：2022-07-21
申请号：US17151718
申请日：2021-01-19
Applicant: TEXTRON INNOVATIONS INC.
Inventor： Albert G. Brand , Bradley P. Regnier , Matthew J. Hill
Abstract: Embodiments are directed to a flight control system for a helicopter comprises a pilot interface configured to receive a control input, at least one electronically controlled actuator, and a computing device configured to translate the control input to an actuator command, wherein the computing device is further configured to apply yaw rate limits to the actuator command to avoid loss of tail rotor effectiveness. The yaw rate limits are associated with a vortex ring state (VRS) envelope for a tail rotor of the helicopter. The electronically controlled actuator comprises a tail rotor actuator. The control input is a pedal input.
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公开(公告)号：US11273911B2
公开(公告)日：2022-03-15
申请号：US16546082
申请日：2019-08-20
Applicant: Textron Innovations Inc.
Inventor： Albert G. Brand , Scott David Poster
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.
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公开(公告)号：US20240190251A1
公开(公告)日：2024-06-13
申请号：US18063308
申请日：2022-12-08
Applicant: Textron Innovations Inc.
Inventor： Yue Fan , Tjepke Herringa , Albert G. Brand
CPC classification number: B60L3/0046 , B60L53/80 , B64D1/12 , B60L2200/10
Abstract: An ejectable battery system for an aircraft is presented. In one embodiment, the present disclosure provides for a battery pack that can be ejected from the aircraft in the event of a thermal runaway, aircraft malfunction, or impending crash. After ejection the battery can remain attached to the aircraft through a retaining tether. A shock absorber in-line with the tether can decrease tether loads. The present disclosure provides an ejectable battery system capable of detecting a battery pack thermal runaway, aircraft malfunction, or impending crash, opening an aircraft battery hatch, ejecting the battery pack from the aircraft, and retaining the battery pack outside of the aircraft via a tether.
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公开(公告)号：US20230278701A1
公开(公告)日：2023-09-07
申请号：US17687625
申请日：2022-03-05
Applicant: Textron Innovations Inc.
Inventor： Albert G. Brand , Michael Pujol , Casey T. Johnson , Marko Vuga
IPC: B64C25/36
CPC classification number: B64C25/36 , B64C2025/325
Abstract: A landing wheel assembly for a rotorcraft having a light on gear phase during takeoff and landing includes a tire and an anti-roll oscillation rim. The tire has first and second side walls and forms a center aperture. The anti-roll oscillation rim includes a center disc disposed in the aperture of the tire, a first side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the first side wall of the tire and a second side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the second side wall of the tire. The first and second side wall support plates support the first and second side walls, respectively, to stiffen the tire in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the rotorcraft.
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公开(公告)号：US12110100B2
公开(公告)日：2024-10-08
申请号：US17687625
申请日：2022-03-05
Applicant: Textron Innovations Inc.
Inventor： Albert G. Brand , Michael Pujol , Casey T. Johnson , Marko Vuga
CPC classification number: B64C25/36 , B64C2025/325
Abstract: A landing wheel assembly for a rotorcraft having a light on gear phase during takeoff and landing includes a tire and an anti-roll oscillation rim. The tire has first and second side walls and forms a center aperture. The anti-roll oscillation rim includes a center disc disposed in the aperture of the tire, a first side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the first side wall of the tire and a second side wall support plate protruding from the center disc and extending at least 25 percent of the vertical length of the second side wall of the tire. The first and second side wall support plates support the first and second side walls, respectively, to stiffen the tire in the light on gear phase of takeoff and landing, thereby reducing roll oscillations of the rotorcraft.
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